Aeronautical NASA SP-7037 (121) Engineering April 1980 A Continuing NASA Bib I og raphy with Indexes

National Aeronautics and C44 Space Administration I ) : & C6 p1 Aeronautic! Engineenng Ae ering Aeronautical Enguneerir igineering Aeronautical Engiri a1 Engineering Aeronautical I iautical Engineering Aeronau Aeronautical Engineering Mr ?ring Aeronautical Engineerin gineering Aeronautical Engin al Engineering Aeronautical E autical Engineering Aeronaul eronautical Fngineering Mn ring Aeronautical Engineerinç ACCESSION NUMBER RANGES

Accession numbers cited in this Supplement fall ithin the following ranges.

STAR (N-10000 Series) N80-14017 N80-16022

IAA (A-10000 Series) A80-17361 A8O-21040

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-1031(121)

AERONAUTICAL ENGINEERING

A Continuing Bibliography

Supplement 121

A selection of annotated references to unclas- sified reports and journal articles that were introduced into the NASA scientific and tech- nical information - system and announced in March 1980 in • Scientific and Technical Aerospace Reports (STAR) • International Aerospace Abstracts (IAA).

Scientific and Technical Information Branch 1 980 PsJI'iS/ Nationat Aeronautics and Space Administration Washington, DC INTRODUCTION

Under the terms of an interagency agreement with the Federal Aviation Administration this publication has been prepared by the National Aeronautics and Space Administration for the joint use of both agencies and the scientific and technical community cncerned 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 A eronautical Engiiieering -- A Continuing Bibliograph y ( NASA SP-7037) lists 411 reports, journal articles, and other documents originally announced in March 1980 in Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (IAA). The coverage includes documents on the engineering and theoretical aspects of design, construction, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and associated components, equipment, and systems. It also includes research and development in aerodynamics, aeronautics, and ground support equipment for aeronautical vehicles. Each entry in the bibliography consists of a standard bibliographic citation accompanied in most cases by an abstract. The listing of the entries is arranged in two major sections, IAA Entries and STAR E,,tries, in that order. The citations, and abstracts when available, are reproduced exactly as they appeared originally in IAA and STAR, including the original accession numbers from the respective announcement journals. This procedure, which saves time and money, accounts for the slight variation in citation appearances. Three indexes -- subject, personal author, and contract number -- are included. An annual cumulative index will be published. AVAILABILITY OF CITED PUBLICATIONS

IAA ENTRIES (A80-10000 Series)

All publications abstracted in this Section are available from the Technical Information Service. American Institute of Aeronautics and Astronautics. Inc. (AIAA). as follows: Paper copies of accessions are available at $7.00 per document up to a maximum of 40 pages. The charge for each additional page is $0.25. Microfiche of documents announced in IAA are available at the rate of $3.00 per microfiche on demand, and at the rate of $1.25 per microfiche for standing orders for all /AA microfiche. The price for the /AA microfiche by category is available at the rate of $1.50 per microfiche plus a $1.00 service charge per category per issue. Microfiche of all the current AIAA Meeting Papers are available on a standing order basis at the rate of $1.50 per microfiche.

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

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

STAR ENTRIES (N80-10000 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 us available from a source other than those listed, the publisher and his address will be displayed on the availability line or in combination with the corporate source line.

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

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

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

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

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 $3.50 price, for those documents identified by a symbol.)

1) A microfiche is a transparent sheet of turn. 105 by 148 mm in size, containing as many as 60 to 98 pages of information reduced to micro images (not to exceed 26: 1 reduction)

iv Avail: NASA Public Document Rooms. Documents so indicated may be examined at or purchased horn the National Aeronautics and Space Administration. Public Documents Room (Room 126). 600 Independence Ave.. S.W.. Washington. D.C. 20546. or public document rodrns located at each of the NASA research centers, the NASA Space Technology Laboratories, and the NASA Pasadena Office at the Jet Propulsion Laboratory.

Avail: DOE Depository Libraries. Organizations in U.S. cities and abroad that maintain collections of Department of Energy reports. usually in microfiche form, are listed in Energy Research Abstracts. Services available from the DOE and its depositories are described in a booklet, DOE Technical Information Center - Its Functions and Services (TID-4660). which may be obtained without charge from the DOE 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) and microfilm. 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.

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

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

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

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

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

v GENERAL AVAILABILITY

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

SUBSCRIPTION AVAILABILITY

This publication is available on subscription from the National Technical Information Service (NTIS). The annual subscription rate for the monthly supplementsis$50.00domestic;$100.00 foreign. All questions relating to the subscriptions should be referred to NTIS, Attn: Subscrip- tions. 5285 Port Royal Road. Springfield Virginia 22161.

vi ADDRESSES OF ORGANIZATIONS

American Institute of Aeronautics Pendragon House. Inc. and Astronautics 899 Broadway Avenue Technical Information Service Redwood City, California 94063 555 West 57th Street. 12th Floor New York. New York 10019 Superintendent of Documents British Library Lending Division. U.S. Government Printing Office Boston Spa. Wetherby. Yorkshire. Washington. D.C. 20402 England

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vii NTIS PRICE SCHEDULES

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(Effectine January 1. 1980>

Pun. Pig. Rang. Noeth Am.flcw Foesign Cod, Pun. Pñ(. - *01 Microf,che S 3,50 $ 5.25 *02 001025 5.00 10.00 *03 026-050 6.00 12.00 *04 051-075 7.00 1400 *05 076-100 800 16.00 *06 101-125 9.00 18.00

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*22 501-525 2500 5000 *23 526-550 - 26.00 - 52.00 *24 ' 551-575 2700 5400 *25 576-600 28.00 56 00 *99 601-up -- 1/ -- 2/

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Eli 24.50 49,50 E12 2750 5550 E13 3050 61,50 E14 33.50 67.50 E15 - 36.50 7350

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TABLE OF CONTENTS

IAAEntries ...... 87

STAREntries ...... 111

Subject Index ...... A-i Personal Author Index ...... B-i

Contract Number Index ...... C-i

TYPICAL CITATION AND ABSTRACT FROM STAR

NASA SPONSORED DOCUMENT AVAILABLE ON MICROFICHE NASA ACCESSIOJ-' N80-1014.8# Northwestern Univ.. Evanston. III. Transportation NUMBER ______Center, .- FACTORS AFFECTING THE RETIREMENT OF COM- CORPORATE MERCIAL TRANSPORT JET AIRCRAFT SOURCE - Frank A. Spencer Aug. 1979296 p refs (Grant N5G-2 149) TITLE (NASA.CR.152308) Avail: NTIS HC A13/MF AOl PUBLICATION CSCLO1C The historical background of the technology and economics I DATE AUTHOR of aircraft replacement and retirement in the prejet era is reviewed J in order to determine whether useful insights can be obtained applicable to the jet era Significant differences between the AVAILABILITY CONTRACT two periods are noted. New factors are identified and examined. SOURCE on GRANT Topics discussed include concern over current policies regarding deregulation, regulatory reform, and retroactive noise regulations. financing and compliance legislation: aging: economic environment COSATI REPORT and inflation, technological progress: fuel efficiency and cost: NUMBER and a financial perspective of replacement decisions. A.R.H CODE

TYPICAL CITATION AND ABSTRACT FROM IAA

AVAILABLE ON MICROFICHE Effect of flow swirling on heat trantfer in the AIAA ACC!2.J'0 A80-10196 /# NUMBER cylindric:iI part of the prenozzle volume of a model chamber (Vliianie zakrutki potoka na teplootdachu v ttilindricheskoi chasti ______predsoplovogo ob'ema modeInoi kamery). F. I. Sharafutdinov, A. I. AUTHORS TITLE Mironov, and V. K. Shchukin (Kazanskii Aviatsionnyi Institut, .,______Kazan, USSR . /nzhenernoFizichegkii Zhurna/, vol. 37, Oct. 1979, AUTHOR'S TITLE OF i_601ef5 In Russian. AFFILIATION _ PERIODICAL Experimental results are presented on the hydrodynamics and heat transfer in swirling flow in a short orificed tube with PUBLICATION straight'blade turbilizers. Data are correlated by the local simulation DATE method, employing the maximum axial component of wall gas velocity and the torque momentum/axial momentum ratio as the turbilizer outlet. B.J.

ix AERONAUTICAL

E N G IN E ER IN G A Continuing Bibliography (Suppl. 121)

APRIL 1980 image, and correlating each reference subarea against the sensed image, producing a correlation function for each subarea. There must be at least three subareas; typically six subareas are selected. The IAA ENTRIES correlation functions are p rocessed to determine a consistent set of local maxima which are in gross agreement as to the relative displacement of the two images. Then, using this set of local maxima and the known subarea locations, a least-squared-error estimate of an affine transformation between the two images is computed. The transformation is applied to the update point in the reference image A80. 17402 Wire obstacle warning system IINOWSI - A to find the corresponding point in the sensed image. The technique real-time airborne sensor for automatic detection and recognition of allows selection of subareas with the most favorable content for wirelike objects. P. Kleehammer, J. Hunt (Fairchild Camera ana correlation. Optimum subarea dimensions exist and depend upon the Instrument Corp., Syosset, N.Y.), and A. Kleider (U.S. Army, Fort amount of distortion expected. The variance of the update point Monmouth, N.J.). In: Smart sensors; Proceedings of the Seminar, position is shown, to be inversely proportional to the number of Washington, D.C., April 17, 18, 1979. Belling- subareas. (Author) ham, Wash., Society of Photo-Optical Instrumentation Engineers, 1979, p. 167-174. Grant No. DAAB07-77-C-2167. A sensor has been designed to provide real-time detection and A80-17521 Discontinuous registration of industrial radio- recognition of 3mm wires at a range of 300 meters during nighttime graphs using profile analysis and piecewise correlation techniques. D. helicopter flight operations. An Army-sponsored program to demon- L. Davies, P. H. Smith, and J. F. Liutermoza (United Technologies strate such automatic wire detection and warning for Nap-of. the- Corp., Pratt and Whitney Aircraft Group, East Hartford, Conn.(. In: Earth (NOE) helicopter missions is currently in progress. Wire or Digital processing of aerial images; Proceedings of the Seminar, wire-like objects are electro-optically detected and then recognized Huntsville, Ala., May 22-24, 1979. Bellingham, by a pattern recognition technique. The recognition algorithm is Wash., Society of Photo-Optical Instrumentation Engineers, 1979, p. accomplished within 50 msec of the first wire detection indication. A 63-72. 9 ref s. flyable exploratory development WOWS model, consisting of a Two methods of measuring internal machine part clearances by scanning laser transmitter, electro-optical receiver, real-time pro- digital processing of industrial radiographs are presented. The first cessor and display unit is described. (Author) technique requires mathematical modeling of the expected optical density of a radiograph as a function of machine part motion. Part separations are estimated on the basis of individual image scan lines, A80-17517 Map-matching techniques for terminal with the final part separation estimate produced by fitting a guidance using Fourier phase information. C. 0. Kuglin, A. F. polynomial to the individual estimates and correcting for imaging Blumenthal, and J. J. Pearson (Lockheed Research Laboratories, Palo and processing degradations simulated by a mathematical model. The Alto, Calif.). In: Digital processing of aerial images; Proceedings of second method applies image registration where radiographs are the Seminar, Huntsville, Ala., May 22 .24, 1979. correlated in a piecewise fashion to allow inference of relative Bellingham, Wash., Society of Photo-Optical Instrumentation Engi. motion of machine parts in a time varying series of images. Each neers, 1979, p. 21-29. DARPA-sponsored research; Grant No. image is divided into segments which are cross-correlated with DAAK4O-76-C-1 193. subsequent images to identify machine part motion in image space. The application of Lockheed's phase correlation image matching Since the magnitude of a correlation peak is a function of the technique to missile guidance has been systematically investigated similarity between an image segment and a subsequent image, it can during the past several years. An effective approach to the scene be used to infer the presence of relative motion of features within distortion problem has been developed and verified for a variety of each image segment thus identifying feature boundaries. A.T. sensor types by computer simulation. The method involves the computation of a full bandwidth Fourier phase difference matrix for the reference and sensed scenes so be matched, followed by the A80-17534 Performance evaluation of image correlation application of the inverse Fourier transform to the phase matrix techniques. J. M. Geros and A. J. Witsmeer (Boeing Aerospace Co., modified by a series of bandwidth-reducing filters to produce a set of Seattle, Wash.). In: Digital processing of aerial images; Proceedings of trial correlation functions. The 'best' matchpoint is then selected the Seminar, Huntsville, Ala., May 22-24, 1979. using parameters derived from each correlation function. A novel Bellingham, Wash., Society of Photo-Optical Instrumentation Engi- method for onboard reference map storage has been developed using neers, 1979, p. 197-205. Contract No. F33615-76-C-1300. quantized Fourier phase angles. (Author) A technique capable of improving the navigation system accuracy of operational systems using low-altitude correlation update A80. 17518 Guidance system position update by multiple information is desired. The technique makes use of the unique subarea correlation. T. K. Lo and G. Gerson (Hughes Aircraft Co., signature of the land mass passing beneath the vehicle to establish its Advanced Missile Systems Div., Canoga Park, Calif.). In: Digital position history and update its inertial navigation system. The processing of aerial images; Proceedings of the Seminar, Huntsville, generic types of sensors available to provide external mapping data Ala., May 22-24, 1979. Bellingham, Wash., for low-altitude correlation, the correlation performance measures Society of Photo-Optical Instrumentation Engineers, 1979, p. 30-40. developed for system analyses and the simulation studies performed Contract No. F30602-77-C-0049. to validate these performance measures are described. This paper will Correlation is a common and powerful method for updating emphasize the ability to and the importance of developing analytical inertial guidance systems. Performance of correlation methods techniques in predicting the behavior of correlation update or image degrades in the presence of geometric distortion between the images matching systems both in terms of fix accuracy and probability of being correlated, or when the image structure is strongly asymmetric. correct correlation or acquisition. This type of analysis vaiidated first The Multiple Subarea Correlation (MSC) technique has been devel- by simulation and later by flight test results provides a solid basis on oped to reduce performance losses due to these effects. The MSC which to develop the system and bring it into operational utility with technique consists of selecting a set of subareas from the reference a high degree of confidence. (Author)

87

A80-17553

A80.17553 Development aspects of a dynamically tuned (TsAG/, Uchenye Zapiski, vol. 9, no. 2, 1978.) Fluid Mechanics - gyro for strapdown - AHRS. H. Sohst )Litton Technische Werke, Soviet Research, vol. 8, Jan-Feb. 1979, p. 122-132. 9 refs. Freiburg im Breisgau, West Germany). In: Symposium on Gyroscope Translation. Technology, Bochum, West Germany, September 18. 19. 1978, The paper examines the effect of relative area of the flow core Proceedings. Düsseldorf, Deutsche Gesellschaft on the performance of. a hypersonic wind tunnel. Results of für Ortung und Navigation, 1979. 17 p. investigations of the performance of hypersonic wind tunnels, such The paper gives an overview of fundamental considerations as the pressure recovery coefficient in the diffuser and test-section regarding the development of dynamically tuned strapdown gyros. blockage ratio, are usually plotted as a function of the Mach number Especially guidelines and areas of significant efforts are reviewed M and Reynolds number Re. However, the results of study of flows which have important impact to the development of the K-273 in hypersonic nozzles are reduced to the dependence of the Mach strapdown gyro at LITEF. Design goal and technical resources are number in the flow core, or of the boundary layer displacement described. Emphasis is put on practical development aspects. Since thickness on similitude parameters. Expressions are derived for the the object of consideration is still in a process of development this relative wind tunnel operation time and the Reynolds number based paper has to be looked upon as an interim report. lAuthor) on the maximum velocity, friction viscosity, and stagnation density. It is concluded that the relative pressure recovery of diffusers, the relative time of wind-tunnel operation, and the blocking of the test section by models, controlled by the operating regime and the startup regime of the wind tunnel are governed by the relative area of A80-17558 A strapdown inertial reference system for the flow core and pertinent similitude ratios describing the flow of commercial airline use in navigation and flight control. P. J. gas in the nozzle. Donoghue and L. B. Cotter (Teledyne Systems Co., Northridge, A.T. Calif.). In: Symposium on Gyroscope Technology, Bochum, West Germany, September 18, 19, 1978, Proceedings. ( Düsseldorf, Deutsche Gesellschaft für Ortung und Navigation, 1979. 19 p. A80-17675 # - Effect of naphthenic aromatic hydrocarbons This paper describes a strapdown inertial reference system (IRS) on the oxidizability of hydrogenated jet fuel (Vliianie nafteno- for use on next generation commercial airlines utilizing equipment aromaticheskikh uglevodov na okisliaemost' gidroochishchennogo complying with the new AR INC 704 standards. The system is topliva RT). V. M. Veselianskaia, E. D. Radchenko, B. A. Englin, and derived from state-of-the-art inertial technology utilizing hardware A. A. Kir'ianova (Vsvsoiuznyi Nauchno- lssledosatel'skii lnstitut already developed and flight tested specifically for this application. Neftianoi Promyshlennosti, Moscow, USSR). Khimiia I Tekhno/ogiia lAuthor) Topliv I Masel, no. 12, 1979, p. 27-31. 10 refs. In Russian.

A80-17559 An integrated strapdown guidance and control system for launch vehicle application. C. W. Kirk and P. J. Donoghue (Teledyne Systems Co., Northridge, Calif.). In: Symposium on A80-17696 // Application of a higher order panel method to Gyroscope Technology, Bochum, West Germany, September 18, 19, realistic supersonic configurations. E. N. Tinoco, F. T. Johnson 1978, Proceedings. Düsseldorf, Deutsche Gesell- (Boeing Aerospace Co., Seattle, Wash.), and L. M. Freeman (Missis- schaft für Ortung und Navigation, 1979. 28 p. sippi State University, University, Miss.). (American Institute of This paper presents an application of strapdown technology and Aeronautics and Astronautics, Aerospace Sciences Meeting, 17th, integrated systems concepts to a guidance and control system New Orleans, La., Jan. 15-17, 1979, Paper 79-0274.) Journal of designed for a launch vehicle. The complete vehicle alignment, Aircraft, vol. 17, Jan. 1980, p. 38-44.21 refs. guidance, launch sequencing, timing, ignition commands, control and A higher-order panel method has been developed for the analysis telemetry are provided by the strapdown system which can be of linearized subsonic and supersonic flow over configurations of adapted to other applications by simple software or custom I/O general shape. This method overcomes many of the slender body changes. (Author) limitations of present day programs in the analysis of supersonic configurations. The capabilities of this method are demonstrated through its application to the analysis of realistic supersonic cruise configurations. Comparisons are shown with experimental data and A80-1 7671 Concerning the information efficiency of aero- with results from other methods in current use. These comparisons dynamic experiments. G. L. Grodzovskii (Tsentral'nyi Aero- demonstrate the unique capabilities of a major new software system gidrodinamicheskii lnstitut, Moscow, USSR). (TsAG/, Uchenye called PAN AIR soon to be available as a general boundary value Zapiski, vol. 9, no. 2, 1978, 36-43.) Fluid Mechanics . Soviet p. problem solver. (Author) Research, vol. 8, Jan..Feb. 1979, p. 103-1 11. 11 refs. Translation. The paper formalizes two concepts: (1) information efficiency A80-17697 # Analytical investigation of aerodynamic of th y measuring system, and (2) the information efficiency of the characteristics of highly swept wings with separated flow. C. S. experiment. The determination methodology for these efficiencies Reddy (Old Dominion University, Norfolk, Va.).Journal of Aircraft, for ,typical problems of aerodynamic experimentation is presented. vol. 17, Jan. 1980, p. 58, 59. 9 refs. Contract No. NAS1-14193-48. The relationship between the minimum duration of the optimal Many modern aircraft designed for supersonic speeds employ experiment, the effective coefficient of noise er. Is, permissible highly swept-back and low-aspect-ratio wings with sharp or thin relative error and she required degree of detail in the unknown edges. Flow separation occurs near the leading and tip edges of such functional relationship is established for the optimal experiment. wings at moderate to high angles of attack. Attempts have been made This is accomplished by employing efficient optimal estimates of over the years to develop analytical methods for predicting the single measurements of parameters and D-G optimal polynomial aerodynamic characteristics of such aircraft. Before any method can experimental designs for determination of the functional relation- really be useful, it must be tested against a standard set of data to ship. M.E.P. determine its capabilities and limitations. The present work under- takes such an investigation. Three methods are considered: the free-vortex-sheet method IWeber et al., 1975), the vortex-lattice method with suction analogy (Lamar and Gloss, 1975), and the A80-17673 Effect of the relative area of the flow core on quasi-vortex lattice method of Mehrotra (1977). Both flat and the performance of a hypersonic wind tunnel. V. Ia. Bezmenos cambered wings of different configurations, for which experimental )Tsentral'nyi Aerogidrodinamicheskii Institut, Moscow, USSR). data-are available, are studied and comparisons made. S.D.

88 A80-1 7723

A80-17698 # Coiment on 'Handling quality criterion for The governing equations of motion of a helicopter rotor coupled heading control'. C. R. Chalk (Calspan Corp., Buffalo, N.Y.). Journal to a rigid body fuselage are derived. A consistent formulation is used of Aircraft, vol. 17, Jan. 1980, p. 60-63; Author's Reply, p.63,64. 9 so derive nonlinear periodic coefficient equations of motion which refs. can be used to study coupled rotor/fuselage dynamics in forward flight. The methodology of rotor/fuselage coupling is clearly de- A80. 17699 # Effects of the aerodynamic cross-coupling and scribed and the importance of an ordering stheme in deriving lateral acceleration derivatives on airplane dynamic characteristics. D. consistent nonlinear equations of motion is reviewed. The final G. Mitchell and 0. E. Johnston (Systems Technology, Inc., equations which are presented in partial differential form can be used Hawthorne, Calif.). American Institute of Aeronautics and Astro- to model coupled rotor/fuselage aeroelastic response or stability nau tics, Aerospace Sciences Meeting, 18th, Pasadena, Calif., Jan. problems. lAuthorl 14. 16, 1980, Paper 80.0170. 13 p. 14 refs. Contracts No. F33615 . 76.C .3072; No. F33615.78.C-3604. A80-17718 Rotational noise of helicopter rotors. Y. A study has been performed to evaluate the contributions of the Nakamura and A. Azuma (Tokyo, University, Tokyo, Japan). static aerodynamic cross-coupling and lateral acceleration derivatives Vertica, vol. 3, no. 3 .4, 1979, p.293-316.48 refs. on the denominator and numerator roots which affect lateral The rotational noise of helicopter rotors is analyzed by means of closed-loop control. Time vector analysis is shown to enhance the direct integration of distributed sources on an influential surface physical insight to the contribution of each aerodynamic and or surfaces. The ound pressure generated by a moving source as kinematic term of the coupled 6 DOF math model and facilitate formulated by Ffowcs Williams and Hawkings 11969, 1963) is simplification so that tractable, literal transfer function approximate decomposed into the components of thickness noise, far field thrust factors can be developed. Time vectors are also applied to 3 DOF noise, near field thrust noise, far field drag noise and near field drag models with and without lateral acceleration derivatives to illustrate noise. An analytical prediction of rotor noise characteristics is their contribution. The method provides insight to the influence of obtained for the insegrand, integral region and observer time the static and acceleration derivatives on key dynamic modes. derivative portions of solutions to the Wave equation. Noise (Author) characteristics such as directivity and wave form are expressed in terms of rotor parameters by numerical calculations. Parametric A80. 17700 fi Estimation of the accuracy of dynamic flight. studies are used to determine the effects of rotor speed, advance determined coefficients. R. E. Maine and K. W. Iliff (NASA. Flight ratio, blade number, chord length, rotor diameter, airfoil section, Research Center, Edwards, Calif.). American Institute of Aeronautics load distribution and directivity on noise levels, and means of and Astronautics, Aerospace Sciences Meeting, 18th. Pasadena, reducing rotor noise are proposed on the basis of the computations. Ca/if, Jan. 14-16, 1980, Paper 80-0171. 18 p.26 ref 5. The analysis also indicates that the predominant source of noise is This paper discusses means of assessing the accuracy of the thickness noise, and it is thus proposed as one of the probable maximum likelihood parameter estimates obtained from dynamic causes of blade slap. A.L.W. flight data. The commonly used analytical predictors of accuracy are compared from both statistical and simplified geometric standpoints. Emphasizing practical considerations, such as modeling error, the accuracy predictions are evaluated with real and simulated data. A80-17720 Airport noise, location rent, and the market Improved computations of the Cramer. Rao bound to correct large for residential amenities. J. P. Nelson lPennsylvania State University, discrepancies caused by colored noise and modeling error are University Park, Pa,). Journal of Environmental Economics and presented. This corrected Cramer-Ran bound is the best available Management, vol. 6, Dec. 1979, p. 320-331.23 refs. analytical predictor of accuracy. Engineering judgemens, aided by The presentstudy reports on the influence of aircraft noise on such analytical tools, is the final arbiter of accuracy estimation. housing prices in the vicinity of six major U.S. airports, including San )Author( Francisco, St. Louis, Cleveland, New Orleans, San Diego, and Buffalo. The sampling procedures attempt so control for the effect of accessibility on location rent, and hence, housing prices. Regres- sion results are reported for the individual samples and for a pooled A80. 17716 Analysis of rotor .fuselage coupling and its sample consisting of 845 observations. The regression coefficients for effect on rotororaft stability and response. J. G. Yen and T. T. aircraft noise are stable about their weighted mean and are McLarty (Bell Helicopter Textron, Fort Worth, Tex.(. Vertica, vol. 3, comparable so coefficient estimates from the pooled sample. Dummy no. 3-4, 1979, p.205.219. 13 refs. variables and partitioned regressions are used to test for remaining The mode displacement, force integration, impedance and (Author) matrix displacement methods for the analysis of the dynamics of accessibility effects. coupled helicopter rotor-fuselage systems are evaluated. The mode displacement method allows a completely coupled rotor.fuselage system to be analyzed by replacing rotor inertial couplings in the fuselage equations with stiffness couplings, and good results for rotor A80-17723 The loads at landing impact IDie Lasten des loads can be obtained. The force integration method is used to Landestosses). K. Kanig (Vereinigse Flugtechnische Werke-Fokker compute hub shears and moments by integrating dynamic and GmbH, Bremen, West Germanyl. (Deutsche Gese/lschaft für Luft- aerodynamic forces along each rotor blade, however this approach und Raumfahrt, Sitzung über Aeroe/astik und Strukturdynamik, requires more computer time. Fuselage or rotor impedance, a useful lmmenstaad, West Germany, July 14, 1978.) Zeitschrift für F/ug- wissenschaften und We/traumforschung, vol. concept in vibration analysis, is used to analyze rotor natural 3, Nov-Dec. 1979, p. 344-360. 9 reft. In German. frequencies and rotor loads, and to calculate she vibration charac- The paper describes a comprehensive calculation method for teristics of a multi-bladed helicopter successfully and economically. determining landing gear loads. Several aircraft of the younger The matrix displacement method systematically automates the generation and of varying designs are used to exemplify the influence coupling of rotating and nonrotating component equations, however of system parameters and initial conditions. Attention is given to requires longer computation time and exhibits poor numerical aircraft structure with emphasis on spring struts, shock absorbers, accuracy. A.L.W. vertical impact shock, horizontal landing speed, and various roll, A80. 1 7717 Formulation of coupled rotor/fuselage equa- pitch, and yaw angles. A cost analysis is made to determine she tions of motion. W. Warmbrodt (NASA, Ames Research Center, overall cost of examining aircraft data by employing a digital Moffett Field, Calif.) and P. Friedmann (California, University, Los computer program. It was found that the use of a program is Angeles. Calif.). Vertica, vol. 3, no. 3-4, 1979, p. 245-271. 19 refs. comparable to five man hours of engineering and that the computers Grant No. NsG-1578. in aviation are basically cost effective. C.F.W.

89 A80-17724

A80'17724 On the influence of steady state temperature A. M. M. Todd (Princeton University, Princeton, N.J.). In: Plasma and pressure distortion on the flow characteristics in an installed physics and controlled nuclear fusion research 1978; Proceedings of multistage Jet engine compressor (Zum Einfluss stationärer the Seventh International Conference, lnnsbruck, Austria, August Temperatur- und Druckstörungen auf die Strömungsverhältnisse in 23-30, 1978. Volume 3. Vienna, International einem installierten, vielstufigen Strahltriebwerk-Verdichter). H. Atomic Energy Agency, 1979, p . 249-264; Discussion, p. 264. 24 Künkler )lndustrieanlagen-Betriebsgesellschaft mbH, Ottobrunn, refs, Contracts No. EY-76-C-02-3073; No. E(11-1)-3237. West Germany) and H. Tonskotter (Aachen, Rheinisch-Westfâlische The ideal and resistive MHD stability properties of a class of Technische Hochschule, Aachen, West Germany). Zeitschrift für toroidal plasma configurations )'spheromaks') having internal Flugwissensc ha! ten und Weltraumforschung, vol. 3, Nov-Dec. 1 979, toroidal and poloidal fields and external poloidal fields are con- p. 360-378. 6 refs. In German, Deutsche Forschungsgemeinschaft sidered, The reactor advantage of the spheromak is two-fold: (1) the Contract No. SFB-83. maximum field strength at the external coils is about half the field at The investigation presented here was aimed at the experimental the plasma centre, rather than twice, as in a tokamak, and (2) a determination of the local variation of flow fields due to steady state roughly spherical blanket can be used, rather than a blanket that circular distortion in a multistage jet engine compressor taking into links the plasma topologically. Taylor's criterion, which ensures account the operating conditions and restraints of the complete stability against both ideal and resistive modes, has been applied to turbine engine interaction. A qualitative analysis was made in force-free spheromaks of unity aspect ratio. In the presence of a advance on the effects of the disturbances on the flow characteristics loosely fitting external conducting shell, oblate spheromaks are considering the interaction between the disturbed and undisturbed stable against all modes except short-wave surface kinks (which are compressor flow. With this prediction and by use of computer aided an artifact of the idealized current density profile). The Mercier test methods it was possible to significantly reduce the complexity of criterion gives a beta-limit below 1%; however, at aspect ratio greater the tests and the test equipment facilities, lAuthorl than or almost equal to 1, the beta-limit for representative spheromak models rises into the range 2-4%. (Author) A80. 17730 Gas turbine carcase and accessory vibration Problems of measurement and analysis. D. S. Pearson, A. H. E. Holme, and P. 8. Watts )Rolls . Royce, Ltd., London, England). (Society of Environmental Engineers, Symposium on Environmental Engineering Today, London, England, May 9-11, 1979.) Society of A80-17900 On the dynamics of compressor surge. A. Environmental Engineers, Journal, vol. 18-4, Dec. 1979, p. 15-22. Tondl {Statni Vyzkumny Ustav Konstrukce Stroju, Bechovice, Measuring system requirements, pitfalls in data analysis and Czechoslovakia). International Journal of Non-Linear Mechanics, vol. severity assessment, and the role of laboratory simulation are 14, no.4, 1979, p. 259-266. 5 refs. presented in terms of gas turbine engine vibration testing. Distortion Investigations concerned with the stability of stationary states in piezoelectric accelerometers due to a charge generated by and the possibility of self-excited oscillation Isurge) occurring in temperature gradients or strain is described, and electrical noise and systems with a centrifugal compressor (or a centrifugal pumpl lead, overload resulting from frequencies of 15 to 10,000 Hz, and peak for a simplified model, to an analysis of a set of two first-order accelerations from 0.3 to 1000 g during vibrational monitoring, are differential equations. The paper presents such an analysis for the considered. Spectral analysis is discussed, as are frequency, coherence case when the machine characteristic can be expressed by a and transmission path analysis as means of presenting data in visual continuous unique curve as well as for that when the characteristic is form, while modal analysis techniques appear capsble of visually neither a unique nor even a smooth curve. It is shown which of the coordinating previously unrelated engine data. It is suggested that singular points is the saddle point and in the case of the latter type of severity criteria be revised to assess 3-plane resolved true motion, the characteristic, which point can be taken for the saddle; this approach combined effect of simultaneous excitation at a range of frequencies, is believed to make practical analyses more straightforward. (Author) and the cumulative effect of individual vibration phenomena. J.P.B.

A80-17737 # Preparing aircraft propulsion for a new era in energy and the environment. W. L. Stewart, 0. L. Nored, J. S. Gr obman, C. E. Feiler, and D. A. Pesrash (NASA, Lewis Research A80-17958 # Determination of the stress intensity factor of Center, Cleveland, Ohiol.AstronauticsandAeronautics, vol. 18, Jan. composite structural members (1< opredeleniiu koeffitsienta in- 1980, p. 18-31, 37. 22 refs. tensivnosti napriazhenii v elementakh konstruktsii iz kom- Improving fuel efficiency, new sources of jet fuel, and noise and pozitsionnogo materiala), V. I. Grishin and B. M. Medvedev emission control are subjects of NASA's aeronautics program. (Tsentral'nyi Aerogidrodinamicheskii Institut, Zhukovsky, USSR). Projects aimed at attaining a 5% fuel savings for existing engines and ProblemyProchnosti, Oct. 1979, p.61-64.6 refs. In Russian. a 13-22% savings for the next generation of turbofan engines using The paper deals with the numerical determination of the stress advanced components, and establishing a basis for turboprop- intensity factor of boron- and graphite-fiber plastics, of the type used powered commercial air transports with 30-40% savings over conven- in the aircraft industry, by the finite element method. The accuracy tional turbofan aircraft at comparable speeds and altitudes, are of this approach is analyzed. A simple relation is proposed for discussed. Fuel sources are considered in terms of reduced hydrogen evaluating the stress intensity factor in terms of the stress concentra- and higher aromatic contents and resultant higher liner temperatures, tion factor of a plate with a hole and two lateral cracks. and attention is given so lean burning, improved fuel atomization, V.P. higher freezing-point fuel, and deriving jet fuel from shale oil or coal. Noise sources including the fan, turbine, combustion process, and flow over internal struts, and attenuation using acoustic treatment, A80'17965 # Evaluation of the intensity of beat'induced are discussed, while near-term reduction of polluting gaseous vibrations (Otsenka intensivnosti vibratsii pri bieniiakh). M. K. emissions at both low and high power, and far-term defining of the Sidorenko IKuibyshevskii Aviatsionnyi Institut, Kuibyshev, USSR). minimum gaseous-pollutant levels possible from turbine engines are Problemy Prochnosti, Oct. 1979, p. 112-114. In Russian. also under study. J.P.B. Beats in multiple-rotor gas-turbine engines may arise when the rotors rotate at roughly the same frequency or in the aerodynamic excitation of higher-order mode shapes of blade vibrations. In the present paper, beat-induced vibration standards are critically A80-1 7876 Low-aspect-ratio limit of the toroidal reactor- analyzed. It is proposed to evaluate the beat intensity on the basis of The spheromak. M. N. Bussac, M. N. Rosenbluth (Institute for a generalized transfer function of oscillatory systems, which makes Advanced Study, Princeton, N.J.), H. P. Furth, M. Okabayashi, and allowance for the ratio of the beat component frequencies. V.P.

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A80-17998 An analytica' method of testing pavement A80-18062 • Comparative resistance of Beta-SI3N4 solid strength (Analytische Uberprufung der Tragfahigkeit von Flug- solutions to molten silicon attack. R. H. Wills, I. Sekeicioglu, J. S. betriebsflächen). G. Beecken (Deutsche Shell AG, Hamburg, West Ogden, C. A. Alexander, and D. E. Niesz )Battelle Columbus Germany), R. C. Koole (Koninklijke/ShelI-Laboratorium, Amster- Laboratories, Columbus. Ohio). American Ceramic Society Sullerin, dam, Netherlands), and W. Visser (Pavement Consultancy Services, vol. 58, Dec. 1979, p. 1198. Contract No. NAS7-100. Rotterdam, Netherlands). Airport Forum, vol. 9, Dec. 1979, p. 23-27, 30-33. In English and German. The article presents a fully developed analytical method of designing airport pavements, measuring the residual bearing capacity A80-18186 Flight certification of the Cessna TU2O6G of existing surfaces, and designing the reinforcements needed. amphibious floatplane. R. K. Rice (Cessna Aircraft Co.. Wichita, Measurements, which are subsequently evaluated with the aid of a Kan.). Society of Flight Test Engineers, Journal, vol. 2, Jan. 1980, p. computer program, are made with falling weight devices which make 2-15. allowance for the complex stress pattern produced by the various A flight test program to develop and certify the 1979 Cessna different aircraft types. The results can also be presented in the form TU2O6G turbocharged amphibian is discussed. The test program of LCN values, a particular advantage of the method described here consisted basically of two parts: certification and performance. and one important reason why the analytical method may be Development testing showed that certain modifications were re- expected to gain further ground at the expense of empirical methods. quired, e.g., engine cowl inlet and cowl exit areas had to be increased (Author) to provide additional cooling air flow, the static system had to be modified to obtain satisfactory speed calibrations. A spin test, A80-17999 Marseilles . Metamorphosis of an airport. included into the test program, showed that the longest recovery Airport Forum, vol. 9, Dec. 1979, p. 51-55. In English and German. from a one-turn spin was three-fourths of a turn and occurred with The article surveys the program of enlargement and moderniza- abnormal use of controls during recovery. Performance tests showed tion at the Marseilles-Marignane airport which began in 1972. It is a significant improvement of rate of climb over the U206G noted that passenger traffic at the airport has been growing at the floatplane, cruise speeds and specific range were significantly lower rate of 5.3% a year, and cargo traffic at 7.5% annually. Attention is for the amphibian than the TU2O6G landplane, and takeoff and given to the principal requirements laid down for the planners and landing distances of the amphibian were similar to the Iandplane architects under the expansion program such as no interference with model for land operation but lengthened somewhat on water. The airport operations, and a final design flexible to ensure easy results of the test program were applied to a similar model, the adaptation to future needs. Topics covered include organization of. TU2O6G floatplane, which, combined with the test programs of 206 the terminal, the new control tower, runway extension and finally floatplane models, allowed certification for two new models at the M.E.P. future plans. Cost of only one flight test program. V.L.

A80-18000 Centralized ground power systems conserve energy. R. L. Frantz (Hobart Brothers Co., Troy, Ohio). Airport Forum, vol. 9, Dec. 1979, p. 63, 64, 66-68, 70. In English and German. A80-18235 • // Experimental and computational study of It is noted that fixed 400 Hz systems for supplying aircraft with transonic flow about swept wings. A. Bertelrud, M. V. Bergmann, ground power are increasingly being installed in new airport facilities. and T. J. Coakley (NASA, Ames Research Center, Moffett Field, The article examines how economical the lasest installations with Calif.). American Institute of Aeronautics and Astronautics, Aero- centralized electricity generation can be. Discussion covers the space Sciences Meeting, 18th, Pasadena, Calif., Jan. 14-16, 1980, advent of centralized power supplies, a typical system, the planning Paper 80-0005. 17 p. 12 ref s. of a central system, cost aspects, and some present installations. It is An experimental investigation of NACA 0010 and 10% circular concluded that in view of the new aircraft ordered for the eighties arc wing models, swept at 45 deg, spanning a channel, and at zero and the urgent need to conserve energy, ground power supply should angle of attack is described. Measurements include chordwise and he seriously considered by airport and airline operators. M.E.P. spanwise surface pressure distributions and oil-flow patterns for a range of transonic Mach numbers and Reynolds numbers. Calcula- tions using a new three-dimensional Navier-Stokes code and a two-equation turbulence model are included for the circular-arc wing A80-18022 Adaptive allocation of decitionmaking respon- flow. Reasonable agreement between measurements and computa- sibility between human and computer in multitask situations. V-V. tions is obtained. (Author) Chu (Perceptronics, Inc., Woodland Hills, Calif.) and W. B. Rouse )lllinois, University, Urbana, Ill.). IEEE Transactions on Systems, Man, and Cybernetics, vol. SMC-9, Dec. 1979, p. 769-778. 15 refs. Grant No. NsG-2119. As human and computer come to have overlapping decision- making abilities, a dynamic or adaptive allocation of responsibilities may be the best mode of human-computer interaction, It is suggested A80. 18238 # Reynolds number and compressibility effects that the computer serve as a backup decisionmaker, accepting on dynamic stall of a NACA 0012 airfoil. N. L. Sankar and V. Tassa responsibility when human workload becomes excessive and relin- (Lockheed-Georgia Co., Marietta, Ga.). American Institute of quishing responsibility when workload becomes acceptable. A Aeronautics and Astronautics, Aerospace Sciences Meeting, 18th, queueing theory fornulation of multitask decisionmaking is used and Pasadena, Calif., Jan. 14-16, 1980, Paper 80-00 10. 15 p. 24 refs. a threshold policy for turning the computer on/off is proposed. This The unsteady two-dimensional Navier-Stokes equations are policy minimizes event-waiting cost subject to human workload solved for laminar compressible flow around a NACA 0012 airfoil. constraints. An experiment was conducted with a balanced design of The governing equations are cast in a strong conservation form in a several subject runs within a computer-aided multitask flight manage- body-fitted coordinate system, and solved using an alternating ment situation with different task demand levels. It was found that direction implicit procedure. Test cases are presented to establish the computer aiding enhanced subsystem performance as well as sub- reliability and accuracy of the procedure, including a case dealing jective ratings. The queueing model appears to be an adequate with the static stall of a Joukowski 9% airfoil. The present technique representation of the multitask decisionmaking situation, and to be is applied to the dynamic stall of a NACA 0012 airfoil, for several capable of predicting system performance in terms of average waiting combinations of Mach number, Reynolds number, and reduced time and server occupancy. Server occupancy was further found to frequency. The numerical results are compared with incompressible correlate highly with the subjective effort ratings. (Author) Navier-Stokes Solutions and water tunnel experiments. (Author)

91 A80- 18245

A80-18245 # Estimation of noise source strengths in a gas Sciences Meeting, 18th, Pasadena, Calif., Jan. 14-16, 1980, Paper turbine combustor. M. Muthukrishnan, W. C. Strahie, and D. H. 80-0050. lOp. 6 refs, Neale (Georgia Institute of Technology, Atlanta, Ga.). American Two techniques applicable to the design of motion simulator Institute of A eronau tics and Astronautics, Aerospace Sciences controllers have been developed. The first, a linear optimal controller Meeting, 78th, Pasadena, Calif., Jan. 14. 16, 1980, Paper 80-0034. 5 synthesized with a quadratic performance index, provides all of the p. 8 refs. U.S. Department of Transportation Contract No. FA. response characteristics previously obtained by classical designs, and 77WA-4077. consists only of constant gain feedforward and feedback loops Experiments were conducted to determine the cause(s) of gas around the actuators. The resulting closed-loop system is, therefore, turbine combustor noise and to quantify the portion of noise relatively- simple as no additional filters or compensators are radiated from a combustor which is linearly, causally related to required. The second technique involves the use of accelerometers combustor events. Using multiple coherence analysis on results and rate gyros, located at the pilot station, to close outer feedback obtained with a combustor terminated by a choked nozzle-diffuser loops around the simulator. This causes the fidelity to be dependent combination it was found that a) a two source model is adequate on the feedback (sensors) rather than the simulator, and results in a with the two sources being direct combustion noise and entropy lower sensitivity so parameter variations and nonlinearities. These noise, b) entropy noise is only important at low frequencies, but is techniques, when applied to a planar model of the Vertical Motion highly coherent with combustion noise, c) with a choked nozzle Simulator, which had the synergistic, overcontrolled, and nonlinear termination the noise is higher frequency than previously demon. properties of the actual system, provided a controller with the strated and d) some other uncertain source, external to the desired response characteristics. (Author) combustor, contaminated the results. (Authorl

A80-18248 • # Structural parameters that influence the noise reduction characteristics of typical general aviation materials. J. Roskam and F. Grosveld (Kansas, University, Lawrence, Kan.l. A80-18253 Computer simulation of engine systems, L. H. American Institute of Aeronautics and Astronautics, Aerospace Fishbach (NASA, Lewis Research Center, Flight Performance Sec- Sciences Meeting, 18th, Pasadena, Calif., Jan. 14-16, 1980, Paper tion, Cleveland, Ohio). American Institute of Aeronautics and 80-0038. 11 p. 7 ref s. NASA-supported research. Astronautics, Aerospace Sciences Meeting, 18th, Pasadena Ca/if., Effect of panel curvature and oblique angle of sound incidence Jan. 14-16, 1980, Paper 80-0051. 15 p. 32 refs. on noise reduction characteristics of an aluminum panel are The paper discusses the availability throughout the government experimentally investigated. Panel curvature results show significant and industry of analytical methods for calculating both the steady Increase in stiffness with comparable decrease of sound transmission state and transient performance of an aircraft engine during an-entire through the panel in the frequency region below the panel/cavity flight regime. The historical development of some of the analytical resonance frequency. Noise reduction data have been achieved for tools capable of evaluating installation effects on engine performance aluminum panels with clamped, bonded and riveted edge conditions. is traced and their present status is described, C.F.W. These edge conditions are shown to influence noise reduction characteristics of aluminum panels. Experimentally measured noise A80-18254 # Multi-variable cycle optimization by gradient reduction characteristics of flat aluminum panels with uniaxial and methods, H. Brown (General Electric Co., Evendale, Ohio). American biaxial in-plane stresses are presented and discussed. Results indicate Institute of Aeronautics and Astronautics, Aerospace Sciences important improvement in noise reduction of these panels in the Meeting, 18th, Pasadena, Ca/if., Jan. 14-16, 1980, Paper 80-0052. 10 frequency range below the fundamental panel/cavity resonance p. frequency. (Author) Variable-cycle engine )VCE) concepts are being explored as a potential approach for advanced military or commercial supersonic propulsion. This paper represents a progress report on a continuing program for she development of a multivariable cycle optimization capability which can be applied to the problem of VCE control A80-18251 // An improved sensing element for skin-friction schedule development. The discussion covers conventional nonlinear balance measurements. J. M. Allen (NASA, Langley Research Center, optimization techniques, the cycle calculation process and its Su p ersonic Aerodynamic Branch, Hampton, Va.). American Institute potential effect on the optimization process, two possible approaches of Aeronautics and Astronautics, Aerospace Sciences Meeting, 18th, to cycle optimization, and examples of their application to VCE Pasadena, Ca/if., Jan. 14- 16, 1980, Paper 80-0049. 6 p. 5 refs. control schedule development. Both approaches use internal un- A nulling, parallel-linkage sensing element has been developed balanced cycle calculations for generating partial derivatives, fre- for a skin-friction balance in order to minimize the introduction of quent derivative updates, and a constrained gradient approach to the extraneous forces. Advantages of the present element over the optimization process. The first approach employs a numerical conventional single-pivot sensing element include its insensitivity to integration external to the cycle balance process, while the second element misalignment and off-center normal forces. Wind tunnel approach incorporates the optimization within the internal cycle tests of the effects of gap size and element misalignment on balance. S.D. parallel-linkage balance measurements indicate the greater sensitivity of the device to misalignment at small gap sizes and large lip sizes, as A80-18255 ft Regression techniques applied to parametric well as its relative insensitivity to off-center normal forces, It is turbine engine simulations, J. R. Ruble (USAF, Aero Propulsion concluded that a parallel-linkage device with a small lip is virtually Laboratory, Wright-Patterson AFB, Ohio), R. A. Sulkoske, and R. E. Insensitive to gap size and element misalignment, representing an Clark (General Motors Corp., Detroit Diesel Allison Div., Indianap- improvement in skin-friction-measuring characteristics. A.L.W. olis, Ind.). American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 18th, Pasadena, Calif., Jan. 14-16, 1980, Paper 80-0053. 9 p. 5 refs. Parametric gas turbine engine computer simulations are used in overall aircraft/mission analysis to develop optimum trends relative to system design variables. Regression analysis curve-fitting was A80. 18252, # Controllers for sircraft motion simulators, W. applied to several areas of a base-line parametric engine simulation, R. Sturgeon (Systems Analysis and Control, Flidgecrest, Calif.). and procedures were evaluated individually and collectively. These American Institute of Aeronautics and Astronautics, Aerospace areas included thermodynamic properties, matrix coefficient pre-

92 A80- 18277

diction, component characteristics, and the ideal compression Institute of Aeronautics and Astronautics, Aerospace Sciences process. Some areas of study are shown to be of general benefit to Meeting, 18th, Pasadena. Calif., Jan. 14-16, 1980, Paper 80-0108. 16 industry while others have more narrow application or could not be p. 25 refs. considered cost-effective changes. The collective evaluation The aerodynamic optimization of current engines under various demonstrated a 46% cost reduction. (Author) flight conditions involves the simultaneous computation of several streams. The paper demonstrates the necessity of studying sransonic flows with a method capable of explaining the free streamlines, of introducing a plug in the supersonic region, and of being incor- A80-18260 # A comparison of first and second order tech- porated into the overall computational program. An analysis likely to niques for computing optimal horizontal gliding trajectories. W. E. meet all these requirements is proposed, and preliminary results are Williamson, Jr. (Sandia Laboratories, Albuquerque, N. Mex.(. presented. The development of a combined computer program has American Institute of Aeronautics and Astronautics. Aerospace proven to be very useful. S.D. Sciences Meeting. 18th, Pasadena, Calif. - Jan. 14-16, 1980, Paper 80-0061. 5 p. Research supported by the U.S. Department of Energy. The problem of numerically computing maximum endurance A80-18272 /! Propulsion/airframe integration considerations subsonic gliding trajectories which remain in a horizontal plane and for high altitude hypersonic cruise vehicles. J. P. Weidner (NASA, return to the original starting point is considered. The control is Langley Research Center, High-Speed Aerodynamics Div., Hampton, parameterized and numeical solutions for two different types of Va.). A inerican Institute of A eronau tics and A stronau tics, A ero space parameterization are shown. Piecewise continuous polynomial Sciences Meeting, 18th, Pasadena, Calif., Jan. 14-16, 1980, Paper control approximations are shown to produce consittent results for 80.0111. 9 p. 6 refs. the trajectories which should be close approximations for the true A study has been conducted to determine the implications of optimal solution. C.F.W. sop-mounted inlet nacelles on propulsion performance and cruise range. The top-mounted nacelle would be less visible from ground- based radar below and ahead of the aircraft. For this study, the nacelle is integrated with a high altitude Mach 5 turbojet/ramjet- powered airplane concept requiring a large nacelle. Results of the 18261 # Conformal mapping analysis of multielement A80. study suggest nacelle instatlation advantages and improved inlet mass airfoils with boundary-layer corrections. N. D. Halsey (Douglas flow ratio for the top-mounted nacelle, but at the expense of a American Institute of Aeronautics Aircraft Co., Long Beach, Calif.). higher installed drag at transonic and supersonic speeds. (Author) and Astronautics, Aerospace Sciences Meeting, 18th, Pasadena, Calif., Jan. 14-16, 1980, Paper 80-0069. 8 p. 12 ref s. Research sponsored by the McDonnell Douglas Independent Research and Development Program. -A conformal mapping technique for the potential-flow analysis of multielement airfoils is extended to include first-order viscous A80-18276 The criticality of engine exhaust simulations effects. Boundary layers are simulated by modification of either the on VSTOL model-measured ground effects. J. R. Lummus (General airfoil coordinates (displacement method) or the boundary condi- Dynamics Corp., Aerospace Technology Dept., Fort Worth, Tex.). tions (blowing method). In the displacement method, multiple American Institute of Aeronautics and Astronautics, Aerospace bodies with open trailing edges are transformed to multiple (closed( Sciences Meeting, 18th, Pasadena, Calif., Jan. 14-16, 1980, Paper circles. In the blowing method, the multiple circles are analyzed with 80-0230. lop. 16 refs. Navy-supported research. nonzero specified normal velocity components. These extentions To improve the accuracy of current prediction methodologies demonstrate that conformal mapping techniques can be applied to and to gain physical understanding of she flow mechanisms involved, many problems formerly thought to fall in the exclusive realm of the an experimental investigation was conducted to determine she more general distributed singularity techniques. (Author( criticality of full-scale engine-nozzle exit conditions (nozzle exit turbulence, total pressure distribution, and pressure ratio over the ranges expected for full-scale aircraft engines), on the propulsion- induced aerodynamic forces for two-, three-, and four-nozzle A80.18268 # Acoustic radiation from axisymmetric ducts - configuration models wish flat plate blocking surfaces. The criticality A comparison of theory and experiment. W. L. Meyer, B. R. Daniel, of performing accurate full-scale engine exhaust simulations during and B. T. Zinn (Georgia Institute of Technology, Atlanta, Ga.(. model-measured VSTOL ground effects testing is demonstrated. If American Institute of Aeronautics and Astronautics, Aerospace the effects of nozzle exit conditions of the engines expected for use Sciences Meeting, 18th, Pasadena, Calif., Jan. 14-16, 1980, Paper on VSTOL aircraft are not considered, costly errors in aircraft sizing 80-0097. 9 p. 7 ref s. Contract No. F49620-77-C-0066. will result. S.D. A special integral representation of the exterior solutions of the Helmholtz equation is used to calculate the free field acoustic radiation patterns around two finite axisymmetric bodies; a straight pipe and a jet engine inlet. The radiation patterns around these bodies are then measured experimentally, with the free field being approximated through the use of an anechoic chamber. The inlet A80'18277 # Recent development of a jet'diffuser ejector. tested has a hard wall while the straight pipe is tested with both a M. Alperin and J. J. Wu (Flight Dynamics Research Corp., Van Nuys, hard and lined wall. The computed theoretical and the measured Calif.). American lnsritute of Aeronautics and Astronautics, Aero- experimental acoustic radiation patterns are found to be in good space Sciences Meeting, 18th, Pasadena, Calif.. Jan. 14-16, 1980, agreement. A discussion of possible sources of error, both theoretical Paper 80-0231. lOp. Navy-NASA-supported research. and experimental, is included. (Author) The paper considers thrust augmenting ejectors in which the processes of mixing and diffusion are partly carried out downstream of the ejector solid surfaces. A jet sheet surrounding she periphery of a widely diverging diffuser prevents separation and forms a gaseous, curved surface to provide effective diffuser ratio and additional length for mixing of primary and induced flows. Three-dimensional A80. 18271 # Engine aerodyrtamic installation by numerical simulation. L. Dutouquet and J. M. Hardy )SNECMA, Centre de potential flow methods achieved a large reduction in the length of Villaroche, Moissy Cramayel, Seine-et-Marne, France). American the associated solid surface; primary nozzle design further reduced

93 A80-18303

the volume required by the jet-diffuser ejectors, resulting in thrust burg, Va.). American /nstitute of Aeronautics and Astronautics, augmentation in excess of two, and an overall length of about 2 1/2 Aerospace Sciences Meeting, 18th, Pasadena, Ca/if., Jan. 14-16, times the throat width. AT. 1980, Paper 80-0309.8 p. 18 refs. Contract No. NAS1-13175-16. The technique of using a curved and rolling flow wind tunnel so extract pure rotary stability derivatives is presented. Descriptions of the curved flow and the rolling flow test sections of the Virginia A80-18303 # Thermal barrier coatings for aircraft gas tur- Tech Stability Wind Tunnel are given including methods for bines. R. A. Miller, S. R. Levine, and S. Stecura (NASA, Lewis obtaining the proper velocity profiles and correcting the data Research Center, Cleveland, Ohio). American Institute of Aero- acquired. Results of testing current fighter configurations in this nau tics and Astronautics, Aerospace Sciences Meeting, 18th, Pasa- facility are presented with particular attention given so comparing dena, Ca/if., Jan. 14-16 1980. Paper 80-0302. 6 p. 13 ref s. pure rotary derivatives with combined rotary and unsteady deriva- Improvements in gas turbine performance are approaching the tives obtained by standard oscillation tests. Also the effect of curved limits imposed by alloy properties and excessive cooling air require- and rolling flow on lateral static stability derivatives is examined. ments. Thin ceramic coatings can increase the difference between gas (Author) temperature and metal temperature by several hundred degrees. Thus, they are potentially a major step forward in surface protection. These coatings offer the potential to reduce fuel consumption by A80-18309 Investigation of leading-edge devices for drag permitting reduced coolant flow or higher turbine inlet temperature reduction of a 60-deg. delta wing at high angles of attack. D. M. Rao or to improve durability by reducing metal temperatures and (Old Dominion Univeisisy, Norfolk, Va.) and T. 0. Johnson, Jr. transient thermal stresses. At NASA Lewis, in-house and contractual American Institute of Aeronautics and Astronautics Aerospace programs are in place to bring this promising technology to engine Sciences Meeting, 18th, Pasadena, Ca/if., Jan. 14 . 16, 1980, Paper readiness in the early 1980's. Progress towards this goal is sum- 80-0310. lip. marized in this paper. (Author) This paper reports an experimental study of leading-edge flow manipulators for alleviating the lift-dependent drag due to break- down of attached flow on blunt leading edges of highly swept wings. The potential of conventional as well as novel devices (fences, A80-18304 # Sonic fatigue design data for bonded chordwise slots, pylon vortex generators and 'vortex-plate') was aluminum aircraft structures. M. J. Jacobson (Northrop Corp., explored in subsonic wind tunnel tests on a 60-deg delta wing model. Hawthorne, Calif.). American Institute of Aeronautics and Astro- In addition to balance measurements, leading-edge suction distri- nautics, Aserospace Sciences Meeting, 18th, Pasadena, Ca/if., Jan. butions were obtained to monitor the spanwise flow development 14-16, 1980, Paper 80-0303. 14 p. 12 refs. Contract No. and Its modification by the different types of devices. The results F33615-75-C-3144; No. F33615-75-C-3016. AF Project 14710130. indicate significant possibilities of drag reduction to high angles of A combined analytical/experimental program was conducted to attack through partial recovery of leading-edge thrust by means of determine sonic fatigue design properties of bonded structural the proposed devices and their combinations. In addition, improve- sections commonly used in aircraft and to formulate data and criteria ments in the longitudinal stability were also found. (Author) for the development of sonic fatigue designs of such structure. An objective of the program was to develop information applicable to aircraft fuselage panels using adhesive bonding in the primary structure, in lieu of mechanical fasteners such as are currently used. A80-18315 3 Studies of leading-edge thrust phenomena. H. The lives of the bonded panels were generally much greater than the W. Carlson and R. J. Mack (NASA. Langley Research Center, sonic fatigue lives of riveted 7075-T6 aluminum alloy panels of Supersonic Aerodynamics Branch, Hampton, Va.). American Insti- comparable size and thickness. Based on the test data and theoretical tute of Aeronautics and Astronautics, Aerospace Sciences Meeting, considerations, a sonic fatigue design chart was developed. It is 18th, Pasadena, Ca/if., Jan. 14-16, 1980, Paper 80-0325. 11 p. 14 expected that the approach in developing the sonic fatigue design refs. chart will remain applicable when different bonding systems and A study of practical limitations on achievement of theoretical surface preparations are considered. (Author) leading-edge thrust has been made and an empirical method for estimation of attainable thrust hat been developed. The method is based on a theoretical analysis of a set of two-dimensional airfoils to define thrust dependence on airfoil geometric characteristics and A80-18306 # Fatigue life prediction of a bonded splice arbitrarily defined limiting pressures, an examination of two- joint. C. T. Liu (U.S. Navy, Naval Air Station, Alameda, Calif.) and dimensional airfoil experimental data to provide an estimate of R. A. Heller (Virginia Polytechnic Institute and State University, limiting pressure dependence on local Mach number and Reynolds Blacksburg, Va.). American /nstitute of Aeronautics and Astronau- number, and employment of simple sweep theory to adapt the tics, Aerospace Sciences Meeting, 18th, Pasadena, Ca/if., Jan. 14-16, method so three-dimensional wings. Because the method takes into 1980, Paper 80-0305. 10 p. 15 refs. account the spanwise variation of airfoil section characteristics, an A linear cumulative damage model utilizing the actual state of opportunity is afforded for design by iteration to maximize the stiess ahead of a crack tip is used to predict the fatigue life of a attainable thrust and the attendant performance benefits. The double-overlapped splice joint. The joint is made of 7075-T6 applicability of the method was demonstrated by comparisons of aluminum and SAE 4130 steel. Two stress states, rc,rmal stress and theoretical and experimental aerodynamic characteristics for a series octahedral shear stress, are considered and calculated from a finite of wing-body configurations. Generally, good predictions of the element method. The effect of the stress state on the fatigue life of attainable thrust and its influence on lift and drag characteristics the joint is investigated and cumulative damage calculations with two were obtained over a range of Mach numbers from 0.24 to 2.0. load levels are presented. (Author) (Author)

A80-1 8316 3 Development of a vortex-lift-design method and application to a slender maneuver-wing configuration. J. E. A80-18308 J Experimental determination of pure rotary Lamar (NASA, Langley Research Center, Hampton, Va.), R. T. stability derivatives using curved and rolling flow wind tunnel. F. H. Schemensky (General Dynamics Corp., Fort Worth, Tex.). and C. S. Lutze (Virginia Polytechnic Institute and State University, Blacks- Reddy (Old Dominion University, Norfolk, Va.). American Institute

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of Aeronau tics and Astronautics. Aerospace Sciences Meeting, 18th, A8O-18328 3 Photon correlation laser velocimeter measure Pasadena. Calif., Jan. 14-16, 1980, Paper 8a0327. 12 p. 16 refs. ments in highly turbulent flow fields. C. D. Catalano, H. E. Wright A method has been developed to optimize the mean camber (USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, Ohio), surface of a cranked slender wing having leading-edge vortex flow at A. Cerrulo, and H. Rogers. American Institute of Aeronautics and transonic-maneuver conditions using the suction analogy. This type Astronautics, Aerospace Sciences Meeting, 18th, Pasadena Calif., of flow was assumed because it was anticipated that the slenderness Jan. 14-16, 1980, Paper 80-0344. 6 p. 6 refs. of the wing would preclude attached flow at the required lift A laser velocimeter using a photon correlation processing coefficient. A constraint was imposed in that the camber deflections scheme has been developed for use in obtaining reliable information were to be restricted by a realistic structural-box requirement. The in turbulent mixing regions. Quantities measured in this investigation resulting application yielded mean-camber shapes which produced include mean velocities and turbulent intensities. Measurements have effective suction levels equivalent to 77 percent of the full-planar been made in a rectangular nozzle free jet flow both with the laser leading-edge value at the design lift coefficient. (Author) velocimeter and with a hot wire anemometer. The Mach number at the exit plane of the nozzle was varied from 0.2 to 0.8. The laser velocimeter obtained mean velocity data was found to correspond quite closely to the information obtained by using the hot wire. The turbulent intensities were found to be much more difficult so A80-18317 /1 The rational design of an airfoil for a high measure using the laser velocimeter. Additionally, measurements performance jet trainer. S. A. Powers and D. F. Sattler (Vought have also been made in the inlet circular duct flow for an actual jet Corp., Dallas, Tex.). American Institute of Aeronautics and Astro- engine. The results pointed out she importance of particle dynamic nautics, Aerospace Sciences Meeting, 18th, Pasadena, Calif., Jan. analysis in establishing the credibility of laser velocimetry in specific 14-16. 1980, Paper 80-0328. 10 p.8 refs. flow fields. This paper discusses the preliminary design of an airfoil tailored (Author) to the design requirements of a high performance jet trainer. The airfoil design requirements are discussed, and the development of the pressure distribution model outlined. The use of an airfoil design program it discussed and the results presented. The indications are A80-18336 3 Hinged vehicle equations of motion. M. J. that the designed airfoil will have a majority of the desired Abzug. American Institute of Aeronautics and Astronautics, Aero- characteristics. (Author) space Sciences Meeting, 18th, Pasadena. Calif., Jan. 14-16, 1980, Paper 80-0364. 11 p. 5 refs. The six-degree-of-freedom equations of motion for flight ve hides having one or more hinged parts are derived from very general vector-dyadic equations that were originally written for space A80-18318 - Effects of non-planar strake-wing on the vehicles. The application of these equations is illustrated by the case vortex lift characteristics of a twin-jet fighter configuration, G. E. of an interceptor vehicle consisting of a body of revolution that has a Erickson (Northrop Corp., Hawthorne, Calif.(.A,nerican Institute of single two .degree-of-freedom hinge. Dynamic cross-coupling terms of Aeronautics and Astronautics, Aerospace Sciences Meeting, 18th, up to third order in the variables of motion are obtained. Pasadena, Calif., Jan. 14-16, 1980, Paper 80-0329. 10 p. Development of equations by the generalized method of this paper is A low-speed wind tunnel investigation using a 1/10-scale model considered preferable to ad hoc methods to minimize the possibility of a twin-jet fighter configuration to determine the effect on the of errors. (Author) aerodynamic characteristics of a nonplanar strake-wing arrangement is presented. The configuration has leading-edge vortex-generating surfaces mounted on and extending forwai-d of the side-mounted engine inlets and are closely-coupled with a conventional planar strake-wing combination. These additional lifting surfaces result in vortex-induced lift increments, drag polar improvement, and un- A80'18340 # Improved numerical simulation of high speed desirable pitch-up. Water tunnel flow studies of models indicate that inlets using the Navier-Stoket equations. D. D. Knight (Rutgers University, New Brunswick, N.J.). the inlet hood vortex favorably interacts with the wing-strake vortex, Amencan Institute of Aeronautics delaying strake vortex breakdown to higher angles of attack. The and Astronautics, Aerospace Sciences Meeting, 18th, Pasadena, lateral/directional stability levels are reduced but the turn perfor- Calif., Jan. 14-16, 1980, Paper 80-0383. 17 p. 42 refs. Contract No. mance is enhanced by implementation of the inlet hoods; the F3361 5-78-C-3008. stability reduction indicates the need for further improvement in she An improved numerical algorithm has been developed to inlet hood configuration. AT. calculate the flowfield in two-dimensional mixed-compression high speed inlets using the Navier-Stokes equations. The explicit finite- difference algorithm of MacCormack is utilized, together with a modified treatment of the viscous sublayer and transition wall region of the turbulent boundary layers. A variety of flows have been considered, including shock-turbulent boundary layer interaction on A80. 18319 3 An inverse transonic wing design method, P. a flat plate and three different configurations of a simulated high A. Henne (Douglas Aircraft Co., Long Beach, Calif.). American speed inlet. The computed- results compare favorably with the Institute of Aeronautics and Astronau tics, Aerospace Sciences experimental data. Meeting, 18th, Pasadena, Calif., Jan. 14-16, 1980, Paper 80-0330. 11 (Author) p. 21 refs. An inverse, transonic flow method for the design of three- dimensional wings has been developed. The flow method is based on a three-dimensional, finite difference solution of the full-potential equation. The inverse scheme utilizes a Dirichlet boundary condition A80. 18346 II Practical method of fatigue crack growth in conjunction with surface transpiration to affect geometry defi- analysis for damage tolerance assessment of aluminum structure in nition. Such a scheme has previously been utilized in a two- fighter type aircraft. M. Levy, A, S. Kuo, and K. Grube (Fairchild dimensional method. This paper summarizes an analogous develop- Republic Co., Farmingdale, N.Y.). American Institute of Aeronautics ment for three dimensions. Basic steps and underlying assumptions and Astronautics, Aerospace Sciences Meeting, 18th, Pasadena, of the inverse scheme are described. Applications of the method so Calif., Jan. 14-16, 1980, Paper 80-0405. 11 p. 22 refs. both simple and complicated design problems are discussed and The relationship between crack growth rate under a variable- advantages of the method are identified. (Author) amplitude spectrum da/dF, and the stress intensity per unit stress,

95 A80-. 18351

alpha is found to be unique for similar loading spectra. Once this tail-on and tail .off; (21 propellers removed; (3) power on, The relationship, f of alpha, is established, the cycle-by-cycle integration methods used in arriving as theoretical predictions are essentially is not needed and simple integration of f of alpha can he applied to those outlined in the USAF Datcom (lifting line). In addition some obtain the crack growth curve. An illustration of the da/dF vs. alpha use was made df computerized lifting surface methods. Fairly good approach as recommended for the A-bA Damage Tolerance Reas- agreement was obtained for both pitch and drag, Lift predictions sessment is demonstrated, It includes two different stress spectra show some discrepancy in both angle of zero lift and maximum lift. applied on coupon tests with various geometry and loading configu- The increments due so power were well predicted, (Author) rations. The function f of alpha assumes the form used by the Forman equation for da/dN, normalized about some reference stress. This function is shown to fit best the data points generated by the coupon test. (Author) A80-18357 # Flow in cransonic compressors. J. L. Kerrebrock (MIT, Cambridge, Mass,). American /nstitute of Aero. nautics and Astronautics, Aerospace Sciences Meeting, 18th, Pasa. dena, Ca/if,, Jan. 14 . 16, 1980, Paper 80.0124. 22 p.50 ref s. A80-18351 /1 Determination of the spin and recovery Current knowledge of the aerodynamics of transonic compres. characteristics of a typical low .wing general aviation design. M. B. sors and prospects for significant improvement in their efficiency ate Tischler and J. B. Barlow (Maryland, University, College Park, Md,), reviewed. Attention is given to describing the role of the technology American Institute of Aeronautics and Astronautics, Aerospace and rts status, to discussing some recent progress toward understand. Sciences Meeting, 18th, Pasadena, Ca/if., Jan. 14-16, 1980, Paper mg the flow field, and to indicating the trends of future research 80-0169. 10 p. 17 refs. Research supported by the Minta Martin work, It is concluded that the exercise of pertinent experimental and Fund for Aeronautical Research; Grant No. NsG-1570. computational capabilities together in a rationalized design process The equilibrium spin technique implemented in a graphical form can result in improvements of 5% or more in transonic compressor for obtaining spin and recovery characteristics from rotary balance efficiency. S.D. data is outlined. Results of its application to recent rosary balance tests of the NASA Low-Wing General Aviation Aircraft are discussed. The present results, which are an extension of previously published findings, indicate the ability of the equilibrium method to accurately evaluate spin modes and recovery control effectiveness. A com- A80-18358 # Multiple tactical aircraft combat performance parison of the calculated results with available spin tunnel and full evaluation system. D, S. Hague )Aerophysics Research Corp., scale findings is presented. The technique is suitable for preliminary Bellevue, Wash.), American Institute of Aeronautics and Astro- design applications as determined from the available results and data nautr'cs, Aerospace Sciences Meeting, 18th, Pasadena, Ca/if,, Jan, base requirements. A full discussion of implementation considera- 14. 16, 1980, Paper 80.0189. 11 p. 13 refs, Contract No, tions and a summary of the results obtained from this method to F3361 5-78-C.3000. date are presented. (Author) The recently developed mutliple tactical aircraft combat per- formance evaluation system )MULTAC), designed to analyze the outcome of a close-in M-on . N air combat, is detailed. The trajectories of up so 20 aircraft engaged in an aerial combat are simultaneously integrated under the time varying angle-of. attack, bank angle and A80. 18352 Enhanced departure/spin recovery of fighter throttle history using the fourth-order Runge-Kutta algorithm. aircraft through control of the forebody vortex orientation. W. A. Encounter outcome is rated by the average survival probability using Moore, A. M. Skow, and 0. J. Lorincz (Northrop Corp., Aircraft either a Monte'Carlo model or a co-kill probability model. The Group, Hawthorne, Calif.). American Institute of Aeronar,tics and system is provided with a library of tactical aircraft and weapon Astronautics, Aerospace Sciences Meeting, 18th, Pasadena, Ca/if., characteristics encompassing current U.S. and Soviet tactical aircraft; Jan. 14-16, 1980, Paper 80-0173. 14 p.21 ref s. these characteristics are stored in an on'Iine computerized data base, A combined experimental and analytical study was undertaken An example of the MULTAC system application illuttrates a trade to develop active blowing concepts to control the asymmetric off between advanced technology and number of aircraft. In the orientation of the vortex system emanating from an aircraft series of encounters considered a 25 percent increment in lift forebody at high angles of attack. The objective of the study was to capability could offset a 3:2 but not a 2:.1 numerical advantage. V.L. utilize the side-force associated with asymmetric vortices, in a controlled manner, to enhance the capability' of a fighter to recover from a departure from controlled flight. Results from water tunnel and wind tunnel tests show a small amount of tangential blowing along the forebody can effectively alter the forebody vortex system anti generate large restoring yawing moments. Six degree-of-freedom digital simulation results show this concept can substantially enhance departure recovery characteristics of fighter aircraft having long, A80-18359 # Euler solutions for wing and wing-body com- slender forebodies. (Author) bination at supersonic speeds with leading-edge separation. G. H, Klopfer and J, N, Nielsen (Nielsen Engineering and Research, Inc., Mountain View, Calif.). American Institute of Aeronautica and Astronautics, Aerospace Sciences Meeting, 18th, Pasadena, Ca/if., Jan, 14-16, 1980, Paper 80-0126, 16 p. 14 reft. Navy'sponsored A80. 18356 # Correlation of predicted longitudinal aerody. research. namic characteristics with full-scale wind tunnel data on the ATLIT A computational procedure is presented for computing steady airplane. J. Roskam, C. P. G. van Dam, and M. Griswold (Kansas, supersonic flowfields surrounding wings and wing-body configura- University, Lawrence, Kan.), American Institute of Aeronautics and tions with sharp leading edges. The Euler equations are solved by Astronautics, Aerospace Sciences Meeting, 18th, Pasadena, Ca/if., MacCormack's scheme, The viscous effects, important near the sharp Jan. 14-16, 1980, Paper 80-0186. 7 p.8 refs. edges, are simulated by a Kutta condition. Results are presented for Current methods for predicting longitudinal aerodynamic char- two delta wings and a wing-body configuration at M aO. The acteristics of a light twin-engine airplane are compared with full-scale wing-body interference factor of a delta wing in the pretence of a wind tunnel results. Correlations are performed on the lift, drag, and circular body as an angle'of'attack of 10 deg and M = 3.0 is also pitching moment coefficients for the following configurations: ) 1) determined. (Author)

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A80-18367 • # Analysis of transonic flow about harmonically The Low-Cost Inertial Guidance System (LCIGS( is a modular oscillating airfoils and wings. W. H. Weatherill (Boeing Commercial strapdown irrplementation of attitude (gyrol and velocity (acceler- Airplane Co., Seattle, Wash.l and F. E. Ehlers (Boeing Computer ometer( axes which permits the interchangeable use of different Services Co., Seattle, Wash.l. American Institute of Aeronautics and manufacturer's instruments without affecting the system's electronic Astronautics, Aerospace Sciences Meeting, 18th, Pasadena, Calif., or mechanical interfaces or processing software. This design flexibil- Jan. 14-16, 1980, Paper 80-0149. 9 p. 12 ref s. Research supported ity is made possible by the use of microprocessors for processing and by the Boeing Commercial Airplane Co.; Contract No. NAS1.15128. control. The microprocessors are embedded in each module and five A finite difference method for analyzing the unsteady transonic are used: one per accelerometer triad, one each per gyro module, and flow about harmonically oscillating wings is discussed. The procedure one in the service module. The processors effect on-line digital is based on separating the velocity potential into steady and unsteady torquing control of the gyros, active instrument error model parts and linearizing the resulting partial differential equations for compensation, including modeling for temperature sensitivity effects, small disturbances. Initial solutions were obtained using relaxation temperature control, self-testing, etc. Adaptation of processing and procedures, but the solution range proved to be limited in terms of calibration algorithms to accommodate for instrument changes or Mach number and reduced frequency. Recent two.dimensional sensed environmental variations is achieved through the use of an results are presented which have been obtained with direct solution alterable read-only data base that may be updated by the LCIGS procedures in which the difference equations are solved 'all at once' support equipment as required at calibrations or upon an instrument and these provide reasonable correlation for practical values of Mach replacement. This data base is accessed by the microprocessors and number and reduced frequency. (Author( used to compute coefficient corrections for the processing algo- rithms. The system architecture is presented and the microprocessor software partitioning and functions are described. (Author(

A80-18375 # The effects of leading edge modifications on the post-stall characteristics of wings. A. E. Winkvlmann, J. 8. Barlow, J. K. Saini, J. D. Anderson, Jr., and E. Jones (Maryland, University, College Park, Md.(. American Institute of Aeronautics A80-18537 A statistical method applied to pilot behavior and Astronautics, Aerospace Sciences Meeting, 18th, Pasadena, analysis in multiloop systems. N. Goto )Kyushu University, Calif., Jan. 14-16, 1980. Paper 80-0199. 16 p. 18 refs. Research Fukuoka, Japan). Journal of Guidance and Control, vol. 3, Jan.Feb. supported by the Minta Martin Fund; Grant No. NsG-1570. 1980, p. 62-68. 22 refs. An investigation of the effects of leading edge modifications on A recently developed statistical method has been applied to the the post-stall characteristics of two rectangular planform wings in a analysis of pilot control behavior in multiloop systems. The method series of low speed wind tunnel tests is presented. Abrupt discon- utilizes the so-called autoregressive scheme, and produces analytical tinuities in the leading edge shape of the wings were produced by results in terms of root mean square values, power spectra. and pilot placing a nose glove over a portion of the span or by deflecting describing functions. The method is practical in that it manipulates Sections of a segmented leading edge flap. Six component balance operating records and it can check the validity of the assumed data, oil flow visualization photographs, and pressure distribution compensatory control system structure. To show the usage and measurements were ,btained, and tests made to study the develop- feasibility of the method, the data from a series of moving-base ment of flow separation at stall on small scale planform wing models. simulator experiments have been analyzed by the method. Emphasis Results of oil flow visualization tests at and beyond stall showed the of the experiment was placed on the lateral-directional control of an formation of counter-rotating swirl patterns on the upper surface of aircraft in the landing approach phase under the influence of the '2. D' and '3-D' wings, and results of a numerical lifting line turbulence. The variation of pilot control behavior with respect to technique applied to wings with leading edge modifications are two experimental variables, the Dutch-roll damping ratio and the included. AT. flight rules, is presented with the discussion as to the system structure and the limitations of the method. Since the application of the inrethod to the field of pilot behavior analysis is quite new, the described method and the presented results are considered to help better analyze and understand pilot behavior in multiloop systems. A80-18376 /) Streamwise development of the flow over a (Author( delta wing. P. M. Sforza and M. J. Sniorto (New York, Polytechnic Institute, Farmingdale, N.Y.). American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 18th, Pasadena, Ca/if, Jan. 14-16, 1980, Paper 80-0200.8 p. 10 refs. A80-18638 /J Constrained optimum trajectories with spec- An experimental investigation of the low speed flow over a ified range. El. Erzherger and i-I. Lee (NASA, Ames Research Center, highly swept delta wing with sharp leading edges is presented. Moffett Field, Calif.). Journal of Guidance and Control, vol. 3, Velocity measurements in the separated leading edge vortex which Jan-Feb. 1980, p. 78 .85. 7 refs. dominates the three-dimensional flow field are shown for several The characteristics of optimum fixed-range tralectories whose different chordwise stations, and serve to illustrate the streamwise structure is constrained to climb, steady cruise, and descent segments development of the vortex. This data is also used to determine the are derived by application of optimal control theory. The perfor- trajectory of the vortex over the delta and to calculate the mance function consists of the sum of fuel and time costs, referred circulation distribution in the flow, and these results are compared to to as direct operating costs (DOC(. The state variable is range-to-go those of previous studies. )Author( and the independent variable is energy. In this formulation a cruise segment always occurs at the optimum cruise energy for sufficiently large range. At short ranges (500 n. mi. and less) a cruise segment may also occur below the optimum cruise energy. The existence of such a cruise segment depends primarily on the fuel flow vs thrust A80-18534 /i Modular strapdown guidance unit with em- characteristics and on thrust constraints. If thrust is a free control bedded microprocessors. J. P. Gilmore (Charles Stark Draper variable along with airspeed, it is shown that such cruise segments Laboratory, Inc., Cambridge, Mass.). (American Institute of Aero- will not generally occur. If thrust is constrained to some maximum nautics and Astronautics, Guidance and Control Conference, Palo value in climb and to some minimum in descent, such cruise Alto, Calif., Aug. 7-9, 1979, Paper 78-1239.) Journal of Guidance segments generally will occur. The performance difference between and Control, vol. 3, Jan-Feb. 1980, p. 3-10. 5 refs. Contract No. free thrust and constrained thrust trajectories has been determined in F08635-76-C-0306. computer calculations for an example transport aircraft. (Author)

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A80-18722 # Automation and air traffic control, J. Good- Instrument landing systems (ILS) and precision approach radars win (Royal Signals and Radar Establishment, Malvern, Worcs., (PAR) will continue to serve as basic landing aids in civil and military England).Journal of Navigation, vol. 33, Jan. 1980, p. 18-22. aviation in the U.S. and in other countries around the world well into The present paper shows how a computer-based system may the 1980's. Advanced ILS use 100 percent solid state electronic ease the tasks of a controller so that considering the increased circuitry and allow for landings with zero ceiling and runway demands for air transport the best combination of man and visibility as low as 200m (700 feet) and is a 'protected' ICAO automation should assure safety and efficiency in air traffic control. navigation aid until 1995. PAR is a short-range primary radar landing Used as an example is the Computer Aided Approach Sequencing aid and while ILS can only be installed on a single runway, PAR has system (CAAS) designed with the aim of assisting air traffic the advantage of being movable and can be rotated from one landing controllers to bring aircraft through the final stages of approach to strip to another as needed. The new microwave landing system London's Heathrow Airport. A computer is used to process and )MLS) is being developed in the meantime and its prototype is now distribute air traffic data making it possible for the controller to being tested in the U.S. The U.S/Australian Time . Reference retrieve useful data that would otherwise be unobtainable, while Scanning Beam (TRSB( Microwave Landing System has been selected changes in data values can be relayed to him swiftly, so that his by ICAO as the advanced all-weather airport landing system to information can be more accurate and up-to-date. This improves replace ILS in the future. During the 1980s MLS will be brought efficiency while the basic air traffic control procedures and patterns nearer to practical realization but it is not yet known how long it will remain the same. Thus, the pattern recognition powers of the be until its final development. V.L. controller, vital to safety, have been preserved and combined with the exactitude of the computer. V.L.

A80-18864 II Technology of the Rolls-Royce RB211 engine. J. F.Coplin.Aircraft Engineering, A80. 18723 # The economics of air traffic control. A. vol. 51, Dec. 1979, p. 8-11. Hislop. Journal of Navigation, vol. 33, Jan. 1980, p. 23-29. Some of the proven advantages of the RB211 turbofan engine The economics of air traffic control (ATCI is becoming a critical are discussed. These advantages, which result from the basic design element of aircraft operating costs due to a number of reasons, and a series of improvements to the engine, include: low installed including the increase of fuel costs, rapid growth in air traffic, and fuel consumption and low installed drag, excellent retention of low the increase in air traffic control charges. A study into the long-term specific fuel consumption in airline service, good resistance to foreign development of air traffic control systems in Europe showed that object damage and demonstrated good record of integrity in service new ATC techniques, such as automatic collision-avoidance systems and capability for development to give both lower sfc and higher (CAS), computer aided approach-sequencing (CAAS) and time-slot thrust levels in the future. A range of advanced engineering programs systems, could considerably improve the operating economics of will contribute to the further development of the RB21 1: e.g. the aircraft. Some of these improvements are: reductions in airway quiet engine demonstrator )OED), advanced core engine technology distance between destinations, reductions in number of 'restricted' (ACET), the high-temperature demonstrator unit (HTDU), and the climb and descent profiles, regular achievement of optimum cruise life and methods design program. Prospects for the engine develop- altitude at correct stage, and reduction in number and cost of delays. ment in the 1980s and 1990s are outlined. The engine will have a Estimated savings per flight in pounds sterling and as percentage of better sfc (5 percent for the 1 980s and at least 20 percent for the direct operating costs are presented and examples of costs of the new 1990s), higher bypass ratio, higher operating temperature and better ATC system for general aviation are also given. V.L. component efficiencies. V.L.

A80-18865 # Some practical aspects of the calibration of air A80-18724 # ATC and the airborne traffic-situation display. data systems. Aircraft Engineering, vol. 51, Dec. 1979, 21-24. B. L. Ford (Royal Signals and Radar Establishment, Malvern, Worcs., p. Three calibration techniques of the air data system consisting England). Journal of Navigation, vol. 33, Jan. 1980, p. 64-74; basically of an air speed indicator, altimeter and machmeter are Discussion, p. 75-79. 12 refs. analyzed. These instruments derive their readings from measurements An airborne traffic-situation display (ATSD) is basically a of air pressures and correction is usually required for errors caused synthetic CRT display showing, in relative plan position, other by the interference of the pressure field around the aircraft. aircraft which are at the same flight level as one aircraft or which Calibration procedures Consist essentially in determining the system could penetrate that flight level. It is proposed that ATSD be used as static pressure error over a range of aircraft incidence. One a back-up for ground-based ATC equipment. If correctly integrated calibration technique, the Airborne Tracking method, is determining into the ATC system, the use of ATSD could result in more efficient the true pressure height of the aircraft by a ground based tracking operations, particularly landing and take-off, more efficient use of system (optical system, radar) and the simultaneous record of the airspace, minimization of communication problems, pilot assurance indicated height from the aircraft altimeter, with the static pressure and increased safety. Some recent air disasters are examined and it is error determined from the observed error in indicated altitude. The shown how they could have been avoided if the pilots had ATSD in Trailing Static method involves the use of a static tube trailed behind their cockpits. Annual savings in operating costs to the airspace users or below the aircraft. Once an aircraft has been calibrated by one of through the adoption of ATSD are estimated at over one thousand the absolute methods it can be used as a pacer aircraft for the million dollars for the mid '80s. The savings would result mainly calibration of the air data systems of other aircraft by a direct from reduced delays at terminals, reduced flight time and fuel comparison technique. Advantages and limitations of each of these consumption as well as prevention of carrier losses due to accidents. methods are discussed. V.L. V.L.

A80. 19051 # An overvoltage safety system for direct cur- A80.18725 What brings us down tomorrow - Landing rent aircraft generators (Ukiad zabezpieczenia nadnapieciowego guidance systems for the 1980s. R. Goodson. Interavia, vol. 35, Jan. lotnicaych pradnic pradu stafego). W. Januszewski and I. Siemirad- 1980, p. 58, 59. zki. Instytut Lotnictwa, Prace, no. 75, 1978, p. 29-42. In Polish.

98 A80- 19280

The paper proposes a safety system for protection of the aircraft A80-19129 H Weather detection using airport surveillance power Circuit against excessive voltage. The system characteristics are radar. D. D. Hayes (Texas Instruments, Inc., Dallas, Tex.). CATCA in accordance with the requirements of the BS.3G.100:3 and Journal, vol. 11, Fall 1979, p. 4-9. GOST-19705-74 standard specifications for direct current generators. The FAA's newest airport surveillance radar system, the ASR-8, An analysis of the current overvoltage safety systems, a diagrammatic is described and improvements in weather detection and display are representation of the proposed system, and a discussion of the proposed. Features of the ASR-8 which eliminate weather from the operating principle and the test results of a model device are display, thus enhancing aircraft display capability, are circular presented. AT. polarization, which reduces weather signals by up to a factor of 100, and moving target indication, which uses the Doppler frequency shift to cancel the returns from fixed objects. It is suggested that the function of weather detection be separated from that of aircraft detection, then optimized by signal processing techniques using A80. 19052 fi Experimental investigation of the character- microprocessors and minicomputers. While the ASR transmitter and istics of pneumatic transfer lines (Badania eksperymentalne charak- antenna will continue as the source of weather signals, a separate terystyk pneumatycznych linii preesylowych). B. Niedzialek. Insty- receiver and signal processor channel will use the precipitation signal tut Lotnictwa, Prace, no. 75, 1978, p. 43-64. In Polish. and tailor the sensitivity time control curve specifically to the The paper discusses the experimentally determined amplitude weather detection process. J.P.B. characteristics of air lines whose geometric dimensions are Lid of 30 to 500 and d = 1 to 5 mm, for the external pressure amplitude of A sub a = 1.5 to 7.5 kPa. The results obtained for ducts used for piston engine indicators are presented, arid correlation between the theoreti- cal and experimental amplitude characteristics is analyzed for small A80-19199 # Aircraft torque motors (Aviatsionnye pulsations. The effects of parameters such as A sub a and L/d on momentnye dvigateli). L. I. Stolov, B. N. Zykov, A: lu. Afanas'ev, duct characteristics are examined, and the generator of sinusoidal and Sh. S. Galeev. Moscow, Izdatel'stvo Mashinostroenie, 1979. 136 pressure pulsations used in tests is described. A.T. p. 54 refs. In Russian. The book deals with airborne dc and ac torque motors currently used for activating gyroscopic and servo systems, accelerometers, telescopes, star-trackers, etc. The classification, theory, design, and testing of torque motors with limited and unlimited delta-three A80-19053 # Investigation of the wear debris content in oil angles are examined. V.P. by measurements of the reluctance and eddy current loss in an electric circuit (Studia nad oznaczaniem zanieczyszczen metalicznych w oleju metoda pomiaru reluktancji I stratnosci obwodu elektrycznego). J. Formaniak. Instytut Lotnictwa, Prace, no. 76, 1979, p.3-37. 22 refs. In Polish. The paper surveys the current methods for detection arid evaluation of wear producing materials and presents results of A80. 19269 H A pre-design code for predicting engine ac- experiments in the determination of metallic impurities in oil by a quisition costs. J. Cyrus (U.S. Naval Material Command, Naval Air method based on the measurement of reluctance and the eddy Development Center, Warminster, Pa.) and E. Onat (Boeing Com- current losses in an electric circuit into which a sample of oil of mercial Airplane Co., Seattle, Wash.). American Institute of Aero- known contamination by metallic powder was introduced. The tests nautics and Astronautics, Aerospace Sciences Meeting, 18th, Pasa- were performed in freciuency ranges from 30 to 1000 kHz; the dena, Calif., Jan. 14-16, 1980, Paper 80-0055. 6 p. 7 refs. results were satisfactory for ferromagnetic materials and impurities A computer code has been developed to predict engine which are good electrical conductors. The variation in natural acquisition costs using thermodynamic and geometric inputs com- frequency of the circuit due to changes in coil inductance or in coil monly available during the preliminary design phase. With these losses was measured, showing that the variation in the 0-factor of the inputs the code selects component materials, estimates the weight of circuit with an oil core containing metallic particles is two orders of raw materials used within the engine, and estimates cost based on the magnitude higher than the change in natural frequency. A.T. raw material content and exotic material factor, or Maurer factor. At this time only a limited validation of the code has occurred. However, the results are encouraging in that the estimated costs for two production engines were within eight percent of the actual costs. (Author)

A80-19070 A numerical approach to subsonic viscous- inviscid interaction. K. Fujii and K. Karashima (Tokyo, University, Tokyo, Japan). Tokyo, University, Institute of Space and Aero- nautical Science, Report no. 575, vol. 44, Oct. 1979, p. 113-128. 17 refs. In this paper is presented a numerical approach to a subsonic viscous-inviscid interaction involving a boundary layer separation. The formulation is made in such a way that a linear equation for the A80-19280 H Installation effects on cycle selection for small stream function obtained through a small perturbation scheme for turbo-fan engines. B. F. Kerkam (Boeing Aerospace Co., Seattle, the inviscid flow and intergral forms of the boundary layer equations Wash.). American Institute of Aeronautics and Astronautics, Aero- for the viscous flow constitute a system of basic equations to be space Sciences Meeting, 18th, Pasadena, Calif., Jan. 14-16, 1980, solved simultaneously in a flow field. In order to demonstrate the Paper8o-0106. lO p. l4refs. applicability of she present approach, subsonic flows past a divergent This paper provides a brief description of inlet and nozzle wall are solved using an iterative scheme based on the SLOP method performance characteristics for small advanced subsonic air vehicles, and the effects of various parameters on the interaction phenomenon applies these characteristics to a turbofan engine cycle analysis, and are examined in detail. It is shown that the solution can be obtained draws conclusions on the manner in which the installation perfor- without any difficulty even at the separation point. The results mance affects engine cycle selection. The primary application of indicate that the present approach is capable of predicting the these air vehicles is for reconnaissance drone, target vehicle and viscous-inviscid interaction involving flow separation. (Author) cruise missile missions. (Author)

99 A80- 19287

A80-19287 ' A computer code to model swept wings in an systems through an experimental model program. Tests were carried adaptive wall transonic wind tunnel. J. E. Mercer, E. W. Geller, M. L. out with models representing a nominal engine airflow bypass ratio Johnson (Flow Research Co., Kent, Wash.), and A. Jameson (New of 0.67 to 2.45. Flow parameters were investigated for a range of York University, New York. N.Y.). American Institute of Aero- nozzle pressure ratios from 1.1 to 3.0 and primary exhaust to fan air nautics and Astronautics, Aerospace Sciences Meeting, 18th, temperature ratios from 1.0 to 2.7. A mixing effectiveness function Pasadena, Calif., Jan. 14-16, 1980. Paper 80-0156. 7 p. 6 refs. is identified in terms of pertinent flow and geometric parameters. Contract No. F40600-79-C-O01. Results are given for mixer nozzle pressure losses, mixing effective- A computer program has been developed to calculate inviscid ness, thrust pain, primary thrust recovery during simulated reverser transonic flow over a swept wing in a wind tunnel with specified fan thrust operation, a'nd ideal and actual turbofan engine perfor- normal flow at the walls. An approximately orthogonal computa- mance. An improvement of 1.6 percent in cruise fuel consumption is tional grid which conforms to the wing and the tunnel walls was indicated with a multi-lobe chute mixer nozzle and current- developed for application of the Jameson-Caughey finite volume technology bypass ratio 6.0 engine at a flight Mach number of 0.82 algorithm. The code solves the full potential equations in fully and 35,000 feet. V.P. conservative form using line relaxation. This program is to be used in place of the wind tunnel for preliminary studies of the adaptive wall concept for three dimensional configurations. It can also be used to assess the magnitude of wall interference in a conventional tunnel. A80. 19303 • # Large scale model tests of a new technology (Author) V/STOL concept, 0. C. Whittley )De Havilland Aircraft Co., Ltd., Downsview, Ontario, Canada) and 0. G. Koenig (NASA, Ames Research Center, Large Scale Aerodynamics Branch, Moffett Field, Calif.). American Institute of Aeronautics and Astronautics Aero- A80-1 9300 • # Engine component improvement program - space Sciences Meeting, 18th, Pasadena, Calif., Jan. 14- 16, 1980, Performance improvement. J. E. McAulay (NASA, Lewis Research Paper 80-0233. 9 p. Center, Performance Improvement Section, Cleveland, Ohio). An ejector design concept for V/STOL aircraft, featuring a American Institute of Aeronautics and Astronautics, Aerospace double-delta configuration with two large chordwise ejector slots Sciences Meeting, 18th, Pasadena, Ca/if., Jan. 14-16, 1980, Paper adjacent to the fuselage side' and a tailplane or canard for 80-0223. 10 p. 7 ref s. longitudinal control is examined. Large scale model tests of the The Engine Component Improvement )ECI) Program is NASA concept have shown that ejector systems are capable of significant sponsored and is specifically directed at reducing the fuel consump- thrust augmentation at realistic supply pressures and temperatures, tion of commercial aircraft in the near-term. As part of the ECI so that power plant size and weight can be reduced accordingly. A program, a Performance Improvement (P1) effort aimed at develop- thrust augmentation of as least 1.75 can be achieved for the isolated ing fuel saving and retention components for new production and elector, not making allowance for duct and nozzle losses. Substantial retrofit of JT9D, JT8D, and CF6 engines' is underway. This paper reductions in velocity, temperature and noise of the lifting jet are reviews the manner in which the P1 concepts were selected for assured due to mixing wishin the ejector - this lessens the severity of development and summarizes the current status of each of the 16 ground erosion and the thrust loss associated with reingestion. NASA' selected concepts. (Author) Consideration is also given to the effect of ground proximity, longitudinal aerodynamic characteristics, transition performance, and lateral stability. V.L.

A80. 19301 # Fuel conservation benefits and critical tech- nologies of recuperative and advanced conventional cycle turboshaft A80'l 9307 # Hybrid vortex method for lifting surfaces with engines. P. F. Piscopo, R. T. Lazarick (U.S. Navy, Naval Air free-vortex flow. 0. A. Kandil, L.-C. Chu (Old Dominion University, Propulsion Test Center, Trenton, N.J.), and J. D. Cyrus (U.S. Naval Norfolk, Va.), and E. C. Yates, Jr. (NASA, Langley Research Center, Material Command, Naval Air Development Center, Warminster, Pa.). Structures and Dynamics Div., Hampton, Va.). Amen'can Institute of American Institute of Aeronautics and Astronautics, Aerospace Aeronautics and Astronautics, Aerospace Sciences Meeting, 18th, Sciences Meeting, 18th, Pasadena, Ca/if., Jan. 14-16, 1980, Paper Pasadena, Ca/if., Jan. 14-16, 1980, Paper 80-0070. 16 p. 52 ref s. 80.0224. 10 p. Grant No. NsG-1560. The Navy's growing concern for energy efficient propulsion A Nonlinear Hybrid Vortex method )NHV-method( has been systems has kindled interest in both the recuperative and advanced developed for predicting the aerodynamic characteristics of wings conventional turboshaft engine cycles as potential candidates for exhibiting leading- and side-edge separations. This method alleviates re-engining its long range subsonic patrol aircraft. Studies were the drawbacks of the Nonlinear Discrete Vortex method (NDV- conducted to define the specific fuel consumption characteristics of method, also known as the multiple line vortex method.) The advanced conventional cycle turboshafts over a range of compressor NHV-method combines continuous-vorticity and vortex-line repre- pressure ratios from 10 to 30 and turbine rotor inlet temperatures sentations of the wing and its separated free shear layers. Continuous from 1900 F to 3300 F. Similar studies were conducted to examine vorticity is used in the near-field calculations, while discrete the same characteristics of recuperative cycle turboshafts over a vortex-lines are used in the far-field calculations. The wing and its range of compressor pressure ratios from 8 to 20 and turbine rotor free shear layers are divided into quadrilateral vortex panels having inlet temperatures from 2200 F to 3400 F. This paper presents the second-order vorticity distributions. The aerodynamic boundary results of these cycle studies and identifies the payoff and critical conditions and continuity of the vorticity distributions are satisfied technology areas for each system. (Author) at certain nodal points on the vortex panels. An iterative technique is used to satisfy these conditions in order to obtain the vorticity distribution and the wake shape. Distributed and total aerodynamic loads are then calculated. (Author)

A80-19302 # An experimental model investigation of turbo- fan engine internal exhaust gas mixer configurations, P. K. Shumpert (Lockheed-Georgia Co., Marietta, Gal, American Institute of Aero- nautics and Astronautics, Aerospace Sciences Meeting, 18th, Pasa- A80. 19308 # Assessment of analytic methods for the predic- dena, Ca/if., Jan. 14-16, 1980, Paper 80-0228. 12 p. 6 ref s. tion of aerodynamic characteristics of arbitrary bodies at supersonic The objective of the work described in the present paper was to speeds. E. J. Landrum and D. S. Miller (NASA, Langley Research improve the technology data base for internal exhaust gas mixer Center, Supersonic Aerodynamics Branch, Hampton, Va.). American

I.

A80- 19764

Institute of Aeronautics and Astronautics, Aerospace Sciences A80-19412 ' Thermal state of structural members of air- Meeting, 18th, Pasadena, Ca/if., Jan. 14-16, 1980, Paper 80-0071. 8 craft engines (Teplovoe sostaianie elementov konstruktsii aviatsion- p. 17 refs. nykh dvigatelei). S. Z. Kopelev and S. V. Gurov. Moscow, lzda- Trends toward the automation of the design process for tel'stvo Mashinostroenie, 1978. 208 p. 74 refs. In Russian. airplanes and missiles accentuate the need for analytic techniques for The book deals primarily with fhe cooling systems developed for the prediction of aerodynamic characteristics. A number of com- heavy-duty elements of aircraft gas-turbine engines and with methods puter codes have been developed or are under development which of calculating their thermal state. Theoretical and experimental show promise of significantly improving she estimation of aerody- methods of determining the value of fuel preheating in fuel supply namic characteristics for arbitrarily-shaped bodies at supersonic lines are described and illustrated by examples. Some mechanical and speeds. The programs considered range in complexity from a simple aerodynamic aspects of turbine blade cooling are examined. V.P. linearized solution employing slender body theory to an exact finite difference solution of the Euler equations. The results from five computer codes are compared with experimental data to determine the accuracy, range of applicability, ease of use, and computer time and cost of the programs. The results provide a useful guide for A80-19413 # The Omega radio navigation system (Radio- selecting the appropriate method for treating bodies at the various navigatsionnaia sistema 'Omega'). V. I. Bykov. Moscow, lzdatel'stvo Transport, 1978. 88 levels of an automated design process. (Author) p. 9 refs. In Russian. The principles of operation of a differential Omega system are outlined, and the influence of phase variations in around-the-world propagation of radio waves on the accuracy of the system is A80-19311 II Mach 3 hydrogen external/base burning. D. H. examined. The optimum implementation of the Omega system in Neale, Sr., J. E. Hubbartt, and W. C. Strahle (Georgia Institute of marine navigation is discussed, along with the influence of the Technology. Atlanta, Ga.). American Institute of Aeronautics and ionosphere on position finding. Attention is given to the calculation Astronautics, Aerospace Sciences Meeting, 18th, Pasadena, Ca/if., of corrections for compensating for the diurnal phase difference of Jan. 14-16, 1980, Paper 80-0280. 9 p. signals and corrections in the region of surface-wave propagation. Experimental studies of base pressure manipulation for an V.P. axisymmetric model at Mach 3 with simulated and actual external! base burning are described. Early work using contoured test section walls and cold gas base region injection is reviewed to demonstrate wake detail and length scale changes under the influence of simulated A80-19414 7 Designing light airplanes lProektirovanie external/base burning. Tests with actual combustion of radially and legkikh samoletov). A. A. Badiagin and F. A. Mukhamedov. Moscow, axially injected hydrogen are then reported. Outstanding perfor- lzdatel'stvo Mashinostroenie, 1978. 208 p. 40 refs. In Russian. mance values with significant base drag reduction is shown for The book deals with such aspects of light-airplane design as the injection and burning directly in the near-wake (base burning). development of light-weight, reliable and economical engines (includ- Current attempts at radial injection and burning in the free stream ing piston engines, and turboprop and turbofan engines); optimiza- lexternal burning) have not yet succeeded. These tests, however, tion of design solutions for greater efficiency and reliability; have defined an envelope within which external burning, if feasible, development of new wing profiles for high lift plus high L/D; will presently be achieved. )Author( decreasing fuselage drag; application of composites and plastics; and development of compact radio equipment and internal and external noise abatement systems. The principal design concepts are ex- amined, and methods of calculating airplane mass and the aero- A80-19316 # Optimization of turbine nozzle cooling by dynamic and flight characteristics in the preliminary design stage are combining impingement and film injection. M. R. Ayache ISNECMA, outlined. V.P. Moissy-Cramayel, Seine-et-Marne, France(, W. Tabakoff, and A. Hamed ICincinnati, University, Cincinnati, Ohio). American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 18th, Pasadena, Ca/if., Jan. 14-16, 1980, Paper 80-0299. 12 p. 15 refs. A80-19579 AEROPP - Message and data switching systems An analytical approach of endwall cooling optimization is for aeronautical operations. The Control/er, vol. 18, Dec. 1979, p. presented. The study is based on the use of existing computation 29-3 1. programs, describing a step-by-step procedure for solving the AEROPP I and AEROPP II, the two categories of integrated combined impingement and film injection cooling optimization. hardware/software message and data switching systems by Philips, Several configurations are considered and their results compared to employ the latest of the DS-714 switching installation. A typical determine the optimal one, corresponding to the maximum global DS-714 installation for an AEROPP system comprises two control thermal endwall cooling effectiveness. (Author) sections, generally referred to as processors X and Y, and an array of input/output equipment available for use by either processor. One of the two processors is normally handling traffic. while the other is in hot standby. The AEROPP system structure permits upgrading from the basic building block handling only the Aeronautical Fixed A80. 19374 1/ Aircraft aerodynamics - Dynamics of longi- Telecommunications Network )AFTN) traffic to a multiuser center tudinal and lateral motion (Aerodinamika samoleta . Dinamika providing a full range of aeronautical communications services, e.g., prodol'nogo i bokovogo dvizheniia). G. S. Giushgens and R. V. operational METEO )OPMET), automatic air/ground interchange, Studnev. Moscow, lzdatel'stvo Mashinostroenie, 1979. 352 p. 107 Common ICAO Data Interchange Network (CID IN), and automatic ref s. telex interface. A flexible range of communications multiplexers is The book deals with some aspects of the lateral-directional available to provide interface and control facilities for changing handling qualities of modern aircraft. A mathematical description of combinations of line types, transmission speeds, and operating the piloting process and of pilot actions in performing single-channel procedures as the center and the network evolve. V.L. stabilization tasks is given. The dynamics of directional motion, the equations of directional motion, and the stability and controllability at a constant flight velocity are studied, along with the lateral A80-19764 Code optimization for solving large 3D EMP characteristics in perturbeçl and unperturbed motion. The influence problems. R. Holland, L. Simpson, and A. H. Saint John (Mission of aircraft lateral motion parameters on the piloting characteristics is Research Corp., Albuquerque, N. Mex.). (IEEE. U.S. Defense discussed. V.P. Nuclear Agency, and Jet Propulsion Laboratory, Annual Conference

ii A80- 19868

on Nuclear and Space Radiation Effects, 16th, Santa Cruz, Calif., A80-20076 # Technologies conceived for the utilization of July 17-20, 1979.) IEEE Transactions on Nuclear Science, vol. ceramics in turboengines (Technologies concues pour l'utilisation des NS26, Dec. 1979, p. 4964-4969. 5 refs. Contract No. DNAOO1-78- céramiques dans let turboréacteurs). S. Boudigues (ONERA, C-0345. Châtillon-sous-Bagneux, Hauts-de-Seine, France) and G. Frasacci This paper describes techniques for implementing and opti- (Direction des Recherches, Etudes et Techniques, Paris, France). mizing large (50x50x50) three-dimensional finite-difference EMP (NA TO, AGARD. Meeting on Ceramics for Turbine Engine Appli- codes. A number of procedures for speeding execution and minimi- cations, Cologne, West Germany, Oct. 8-10, 1979.) ONERA, TP no. zing memory requirements are presented and evaluated. As an 1979-132, 1979. 14 p. In French. example, we illustrate numerical results obtained when a B52 is As compared to refractory alloys, ceramics used as heavy-duty modeled within a 50x43x59 mesh and illuminated by a nominal EMP elements in a turboengine provide higher operational tem peratures at simulation. (Author) much lower densities. They also are characterized by higher strength in compression than in tension. In the present paper two approaches to the problem of incorporating ceramic elements en turboengines are examined. One approach is based on adaptation of technologies A80-19868 # Damping capacity of plastic compressor blades developed for refractory alloys, the other on aerodynamics and (Dempfiruiushchaia sposobnost' lopatok kompressorov iz kompo- turbine-tech nology concepts adapted to ceramics. Several concepts zitsionnykh materialov). N. 0. Stepanenko (Kiubyshevskii Aviatsion- of integrating a turbine into a complete engine are proposed, and the nyi Institut, Kuibyshev, USSR). Problemy Prochnosti, Nov. 1979, p. aerodynamic loads, temperatures, stresses, as well as production 109. 114. 11 refs. In Russian. techniques and root designs, are determined for the blades. V.P. A resonance test stand was used to study the damping behavior of unidirectionally strengthened plastic blades and their dovetail roots at various normal modes. Particular attention was given to the energy dissipation in the blades. The energy dissipation coefficient is plotted for several types of excitation. The logarithmic decrement is studied as a function of the strain level for plane, flexural, and torsional mode shapes of vibration. V.P. A80-20083 # Separation due to shock wave-turbulent boundary layer interaction (Décotfement resultant d'une interaction onde de choc-couche limite turbulente). J. Delery and P. Le Diuzet (ONERA, Chftillon-sous-Bagneux, Hauts-de-Seine, France). (Associa- tion Aéronautique et Astronautique de France, Coioque d'Aéro- A80-19990 # Investigations of the optimal configuration of dynamique Appliquée, 16th, Lilly, France, Nov. 13-15, 1979.) high-stability quartz oscillators for aircraft and missiles (Recherches ONERA, TP no. 1979-146, 1979. 28 p. 25 refs. In French. Research tIe configuration optimale d'oscillateurs a quartz de haute stabilité supported by the Direction des Recherches, Etudes et Techniques. pour avions et missiles). J. Beaussier (ONERA, Chãtillon-sous- Holographic interferomesry and laser velocimesry have been Bagneux, Hauts-de-Seine, France). La Recherche Aérospatiale, Nov.- jointly used for analyzing the flow resulting from the interaction Dec. 1979, 375-386. 12 refs. In French. Research supported by p . between a shock wave and a turbulent boundary layer occurring in a the Direction des Recherches, Etudes et Techniques. two-dimensional transonic channel. The Mach number at the start of Work done by ONERA on the optimal configuration of compact interaction is 1.37, and the local Reynolds number, calculated with and easily startable quartz oscillators of stability close to that of the initial boundary layer thickness, is 85,000. The external flow has atomic clocks for use in the time-frequency systems of aircraft and first been carefully explored in order to trace a precise chart of the missiles is summarized. The stability requirements of a time- nondissipative flow field. Laser velocimetry made it possible to frequency standard are examined and the operating parameters of characterize the organization of the dissipative layer, which includes quartz oscillators and atomic clocks are compared. The corrfigura- a large separated zone. The following quantities have been measured: tiorrs of oscillators developed are then discussed, taking into longitudinal and vertical components of the mean motion, the consideration problems encountered with the resonator and the corresponding turbulence intensities and Reynolds stress. (Author) electronic circuits associated with it and the specifications, opera- tion, design and significance of the dual thermostats within the oscillators. The four 5-MHz and two 1 00-MHz oscillators realized are described, and results of test of long-, medium- and short-term frequency stability in nonperturbed environments and of accelera- tion and temperassire sensitivity in simulated aircraft and missile environments are reported. It is found that the 5-MHz oscillators exhibit greatvr stability while the 100-MHz oscillators are smaller, and quartz oscillator stabilities surpassing those of rubidium stan- dards are reported. A.L.W. A80-20086 A phenomenological model of the dynamic stall of a helicopter blade profile (Modéle phénoménologique de décrochage dynamique sur profil tIe pale d'hélicoptére). R. Dat, C. T. Tran, and D. Petos (ONERA, Chétillon-sous-Bagneux, Hauts-de- Seine, France). (Association Aéronautique et Astronautique de France, Colloque d'Aérody,iamique Appliquée, 16th, Lill y, France, Nov, 13-15, 1979.) ONERA, TP no. 1979-149, 1979.43 p. 7 refs. In French, A phenomenological model developed for the prediction of A80.20064 II A method of evaluation of gas turbine engines helicopter blade stall is presented. The model uses a system of (Ob odnom metode otsenki sostoianiia gazoturbinnogo dvigatelia). differential equations to relate the aerodynamic forces and the G. N. Mendrul. Prob/emy Tekhoicheskoi E/ektrodinamiki no. 69, variables determining the velocity of the blade profile in order to 1979, p. 99-102. In Russian. simulate the effects of flow history. Wind tunnel measurements of The paper presents a classification method described by multi- the profile in a stationary regime and oscillating as a small amplitude plicity of n-dimensional vectors in a definite type of condition - the are required for model identification, and she model is validated by test theory method. Engineering methodology of determining an lift and moment measurements on a helicopter blade profile at high object classification as an exact or inexact state is developed using a incidence. Preliminary results of she application of the model have learning theory. AT. been found to be encouraging. A.L.W.

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A80-20088 é Experimental study of confluence with separa- calculation in which the combustion chamber discharges directly into tion on an afterbody of revolution (Etude expérimentale de Ia a multi-stage turbine the down-stream noise was predominantly due confluence avec décollement sur un arriére-corps de revolution). J. L. to the interaction of the entropy with the turbine (i.e., 'indirect' Solignac. (Canadian Congress of Applied Mechanics, 7th, May rather than 'direct' combustion noise). (Author) 27-June ! 1979. Sherbrooke, Quebec, Canada.) ONERA, TP no. 1979-151, 1979.21 p.8 refs. In French. The confluence of internal and external flows at a trailing edge downstream of a separation region is investigated for an afterbody of A80-20153 Sound generation in a flow near a compliant revolution with a central jet. Aerodynamic data was obtained by wall. W. Mohring and S. Rahman (Max-Planck-lnstitut für means of pressure probes, hot-wire probes and laser velocimetry, as Strbmungsforschung, Gottingen, West Germany). Journal of Sound well as flow visualization at flow Reynolds numbers high enough to and Vibration, vol. 66, Oct. 22, 1979, p. 557-564. 11 refs. Research assure a turbulent boundary layer directly upstream of the separation supported by the Deutsche Forschungsgemeinschaft. points. The mean flow is found to include a separated flow region The generation of sound near an infinite compliant wall is defined by a streamline extending from the separation point to the studied, with account taken of a uniform mean flow. Stable and trailing edge, while turbulence is observed to be strongest in the unstable configurations are looked at. It is shown that a possible vicinity of the separation point and in the extreme downstream influence of the wall on the sound generation occurs only via a portions of the separation zone in the internal and external flow modification of the turbulence if hydrodynamic non-linearities are mixing regions. The internal mixing layer also appears to be the responsible for the levelling-off of the instabilities. Then no source of strong quasi-sinusoidal low frequency fluctuations which fundamentally more efficient sound sources are found. An increase are detectable in the potential regions of the central jet. A.L.W. of the radiated sound may be possible because of the mirror sources and because of their.possibly reduced compactness. (Author)

A80-20112 # Integrated circuit characteristics at 260 C for aircraft engine-control applications, L. J. Palkuti (ARACOR, Sunny- A80-20192 Atmospheric effects on Martian ejecta em- valt, Calif.), i. L. Prince (Clemson University, Clemson, S.C,), and A, placement, P. H. Schultz (Lunar and Planetary Institute, Houston, S. Glista, Jr. (U.S. Navy, Naval Air Systems Command, Washington, Tex.( and 0. E. Gault (Murphys Center for Planetology, Murphys, D.C.). finstitute of Electrical and Electronics Engineers, Electrical Calif.). Journal of Geophysical Research, vol. 84, Dec. 10, 1979, p. Components Conference, 29th, Cherry Hill, N.J., May 14- 16', 1979.) 7669-7687. 53 rel y. Contract No. NSR-09-051-001. IEEE Transactions on Components, Hybrids, and Manufacturing The paper presents analytical , descriptions of crater growth and Technology, vol. CHMT-2, Dec. 1979, p. 405-412. 8 refs. Research numerical calculations of aerodynamic drag to evaluate the possible supported by the U.S. Navy and U,S. Department of Energy. effects of drag on impact crater ejecta emplacement on Mars. The Bipolar circuits with junction or dielectric isolation, other critical particle size below which ejecta deposition is restricted in discrete devices, and integrated circuits (ICy) were examined from range increases with crater size; models of ejecta trajectories in the room temperature so 250 and 300 C as part of a Navy program for current Martian atmosphere under hydrostatic equilibrium reveal the design of uncooled solid-state electronics for aircraft engine critical particle diameters ranging from 0.4 to 20 cm, noting that control applications. Discrete silicon semiconductor devices of ejecta approaching the critical particle size may impact with crater essentially all generic types functioned with modified but usable radius of the excavation crater i im. Ejecta larger than the critical characteristics as junction temperatures up to at least 300 C, but particle size are undecelerated and form secondary impact craters first-order device parameter changes resulted from increased leakage, modified by she later arriving decelerated ejects cloud; thus, ejects reduced mobility, and changes in the Fermi level in the bulk and at emplacement will be multiphased, but the process depends on she the surface. Both analog and digital ICs exhibited dc as well as useful ejecta size distribution. AT. dynamic characteristics up to near 250 C. For a variety of CMOS devices tested, a pnpn latchup mechanism between the p-channel transistor and the input protection network limited useful device operation so 260 C, white no fundamental barrier to 300 C functionality of ICs designed specifically for high-temperature A80-20214 The next supersonic transport. B. Sweetman. application was found. J.P.B. Flight International, vol. 116, Nov. 24, 1979, p. 1772-1774, 1779. The article investigates future concepts for supersonic trans- ports, noting that the concept is still viable because the efficiency of air travel is related so speed. In theory, the less time an aircraft has to be airborne, she less energy it will rise, so faster aircraft should be more efficient. Discussion covers such areas as compromises in wing construction for take off and landing and supersonic cruise, and A80-20151 Jet engine combustion noise Pressure, comparisons between delta and arrow wings. Similar problems in entropy and vorticity perturbations produced by unsteady com- engine design are also considered such as the conflict between noise bustion or heat addition. N. A. Cumpsty (Cambridge University, and supersonic performance, Weight factors are also investigated as Cambridge, England). Journal of Sound and Vibration, vol. 66, Oct. regards the use of composites, as well as the Use of hydrogen as a 22, 1979, p. 527-544. 10 refs. fuel. Finally, it is noted that the general consensus is that a future By idealizing combustion or heat addition processes to occur SST should be substantially larger than the Concorde (about 230 over a short distance in the flow direction it is possible to calculate passengers) and have a non-stop Pacific range. M.E.P. the amplitude and phase of the disturbances corresponding to small amplitude fluctuations in the heat addition. The fluctuating heat input is assumed to vary sinusoidally with time and with distance along the direction normal so the flow. Pressure waves propagate away from the heat input region upstream and downstream, whilst on the downstream side waves of vorticity and entropy are convected away. Strong resonant peaks in the pressure and vorticity waves are present close to the cut-off condition of the pressure waves in two A80-20251 A light aircraft camera Pod - The Enviro-Pod. dimensions. Generally the wave amplitudes tend to be higher when G. E, Howard, Jr. (U.S. Environmental Protection Agency, Environ- the mean flow velocity into the region is close to sonic and to mental Photographic Interpretation Center, Warrenton, Va.(. In: become smaller as the steady heat input is increased. For a simplified American Society of Photogrammetry, Fall Technical Meeting,

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Albuquerque, N. Mex., October 15-20, 1978. Proceedings. elements. In conclusion, it is recommended that design investigations F ails Church, Va., American Society of Photogramme- of operational tilt rotor V/STOL continue and that technology tasks involving experimental investigations with the XV-15 tilt-rotor try, 1978. P. 283-295. The paper deals with an airborne self-contained low-cost remote research vehicle, laboratory test rigs, and models be undertaken. sensing system, called the Enviro-Pod (Pod), developed for monitor- M.E.P. ing the environment of the United-States territory to ensure the validity of environmental standards and assure legal compliance. The results of feasibility tests and demonstrations indicate that the A80-20630 A method of simplifying weight and balance camera-configured Pod will acquire cost effectively high-quality for small aircraft. E. I. Miller (Boeing Co., Seattle, Wash.). Society of high-resolution imagery in routine monitoring of point targets, Allied Weight Engineers, Annual Conference, 38th, New York, N. Y., stream segments, and small areas of generally less than 25 square May 7-9, 1979, Paper 1278. 27 p. 5 refs. miles. In its current configuration, the Pod provides high-resolbtion This paper presents a nomographic method of figuring weight panoramic imagery in both the oblique and vertical camera positions. and balance (an alignment chart), similar to one used by many large At a typical flight altitude of 3000 ft. the resolution of panchromatic aircraft operations because of its speed, simplicity and accuracy. film at nadir is 18cm. V_P. Using a Basic Empty Weight Index, a simplified weight record (manifest), Loadlines and a C. G. Grid it can be easily adapted for use by light aircraft with a minimum of effort, no change in present methods, manual of F.A.A. Regulations, and does not require any A80-20626 Application of RCS guidelines to weight effec- special equipment. - . (Author) tive aircraft design. L. A. Irish and M. C. Vincent (Boeing Co., Seattle, Wash.). Society of A/lied Weighr Engineers. Annual Confer- ence, 38th, New York, N. Y., May 79 1979, Paper 1270. 9 p. Contract No. F33615-78-C-3422. A80. 20631 Analog aircraft weight and balance computer. The need for an organized, proven body of trade data and T. D. Boldt (Quik Trim, Egg Harbor City, N.J.). Society of Allied guidelines on the relationship of radar cross section to the familiar Weight Engineers, Annual Conference, 38th, New York, N. Y., May aircraft design parameters is emphasized. The approach to developing 7-9, 1979, Paper 1283. 20 p. information consisting of many different activities is examined and An analog weight and balance computer was developed for some key activities including data base development, parametric single-engine aircraft in response to a need by general aviation pilots study and guideline development are presented. Attention is given to for this type of aid. A detailed background is given for the reasons explanations of the relationship between parameters of wing size, for the author to develop the computer. The relative merits of the sweep, engine inlet and tailsize and radar cross section. C.F.W. analog vs. the digital computer are explained and the reasons given for the use of the analog techniques. In this respect, the use by the pilot and his understanding of aircraft weight and balance and the factors affecting aircraft balance are considered. The construction A80-20627 Application of finite element analysis to den- and layout of the computer are explained and the influence of pilot vatión of structural weight. J. G. Hutton and L. D. Richmond feedback on the design are discussed. The extension of the computer (Boeing Aerospace Co., Seattle, Wash.). Society of Allied Weight for use in general aviation twins, cargo Operations and heavy aircraft Engineers, Annual Conference, 38th, New York, N. Y., May 7-9, are discussed. The accuracy of weight and balance computations is 1979, Paper 1271. 29 p. 7 refs. analysed to determine the accuracy necessary in the subject The paper presents application of finite element analysis to computer. Appropriate examples are given for various aircraft derive methodology for estimation of structural system weight. The categories. (Author) study developed factoring logic and its testing, and the documenta- tion of interdisciplinary interaction for model development. The numerical factors were composed of subfactors that accounted for modeling technique, Construction method, material, and installation details. The F-iSA was used as the known structural system for A80-20632 Advanced materials and the Canadair Challenger. D. R. Turner )Canadair, Ltd., St. Laurent, Quebec, testing of the weight factor logic; a finite element model was Canada). Society of Allied Weight Engineers, Annual Conference, developed for the wing box, and a simplified beam body and 38th, New York, N. Y., May 7-9, 1979, Paper 1284. horizontal tail were included for simulation of the wing support and 9 p. The Canadair Challenger is a business jet with take-off weight of to provide balanced aircraft loads. The correlation of the factored 34,500 lb. 7500 lb thrust and space of at least 100 cu ft per person. finite element and as-built weights was good for the cover panels; the In order to avoid the inherent weight penalties in the wide-body total cover weight compared within 3% with a plus or minus 10% aircraft, composite materials with high specific strength and good spread among the individual panels. A.T. fracture toughness were used. The airframe primary structure is made of advanced aluminum alloys and the secondary structural com- ponents are made of two epoxy resin based systems, the first being reinforced with Kevlar aramid fibers and the second being based on the higher strength and modulus graphite fibers. For further A80-20628 Tilt rotor - An effective VISTOL concept. J. reduction of both weight and manufacturing costs (36% and 82% DeTore (Bell Helicopter Textron, Fort Worth, Tex.). Society of respectively) the application of graphite and Keelar/epoxy com- A/lied Weight Engineers, Annual Conference, 38th, New York, N. Y., posites in the primary structural areas is considered. L.M. May 7-9, 1979, Paper 1273. 22 p. 6 refs. The paper investigates how the tilt rotor V/STOL concept can be turned into an effective operational system and what such a mission-oriented tilt rotor aircraft is like. Attention is given to the variation of hover efficiency, speed capability, and previously A80-20636 The modular life cycle cost model - An determined weight empty ratios for various V/STOL concepts, such overview. B. I. Rachowitz (Grumman Aerospace Corp., Bethpage, as the helicopter in comparison with the tilt rotor. A tilt rotor design N.Y.) and N. Sternberger (USAF, Flight Dynamics Laboratory, aimed at satisfying Navy/Marine subsonic V/STOL needs is de- Wright-Patterson AFB, Ohio). Society of Allied Weight Engineers, scribed. Results are presented which relate estimated performance Annual Conference, 38th, New York, N. Y., May 7-9, 1979, Paper capabilities during various modes of flight with useful mission 1290. i5p.

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An overview of the first subsystem level Life Cycle Cost Model The paper identifies the distribution of the propulsive system (LCCM( for advanced aircraft is presented. The cost estimating weight for a typical V/STOL concept and illustrates how advanced relationships are based on design parameters which are available technology will affect the weight of the various propulsive system during conceptual and preliminary design phases of an advanced components. Individual technology assessments are given for the technology aircraft program. The modular LCCM was developed to following propulsive system components: (i( core engine compressor provide design engineers with a tool and the capability to effectively section, (21 core engine high pressure turbine section, (3) core engine conduct design/cost/performance trade studies of advanced fighter! low pressure turbine section, (41 core engine combustor section, attack and cargo/transport aircraft, in determining the cost impact of controls and accessories, (51 lift cruise fan weight, (61 transmission design decision on life cycle cost at the major subsystem level. C.F.W. system, (7) exhaust system, and (81 engine section and nacelle. It is concluded that the propulsive system weight decrease due to technology is almost equally distributed between the core engines, fans and nacelles. M.E.P. A80-20637 • Application of parametric weight and cost estimating relationships to future transport aircraft. M. N. Beltramo, M. A. Morris (Science Applications, Inc., Los Angeles, Calif.). and J. L. Anderson (NASA, Ames Research Center, Moffett Field, Calif.). A80-20645 Preliminary weight estimation of engine sec- Society of A/lied Weight Engineers. Annual Conference. 38th, New tion structure. A. H. Schmidt (Boeing Co., Seattle, Wash.). Society of York, N.Y., May 7 .9 1979. Paper 1292. 23 p. Allied Weight Engineers, Annual Conference, 38th, New York, N.Y., A model comprised of system level weight and cost estimating May 7-9, 1979, Paper 1311. 5 p. relationships for transport aircraft is presented. In order to determine The weighs of she engine section is a part of the aircraft the production cost of future aircraft its weighs is first estimated structural weight which has not been given much attention by weight based on performance parameters, and then the cost is estimated as a methodology. This paper discusses a method of estimating the weight function of weight. For initial evaluation CERs were applied to of the following engine section components-engine mounts, nacelles actual system weights of six aircraft (3 military and 3 commercial) or cowlings, firewalls, and pylon support struts such as used on jet with mean empty weights ranging from 30,000 to 300,000 lb. The driven aircraft. Air intakes are not included. Parameters usually resulting cost estimates were compared with actual costs. The average available from preliminary design three-view drawings and group absolute error was only 4.3%. Then the model was applied to five weight statements are used. Factors for estimating the weight effects aircraft still in the design phase (Boeing 757, 767 and 777, and BAC of propeller or jet drive are included along with factors for allowing HS146-100 and HS146-200(. While the estimates for the 757 and for special features such as work platforms. A plot of calculated 767 are within 2 to 3 percent of their assumed break-even costs, it is versus actual weight is included to show the accuracy of the method recognized that these are very sensitive to the validity of the for a broad range of aircraft. (Author) estimated weights, inflation factor, the amount assumed for non- recurring costs, etc., and it is suggested that the model may be used in conjunction with other information such as RDT&E cost estimates and market forecasts. The model will help NASA evaluate new L.M. technologies and production Costs of future aircraft. A80-20646 Weight Integrated Sizing Evaluation /WISE/ - A tool for preliminary design. A. Gersch (Grumman Aerospace A80-20638 Designing to life cycle cost in the Hornet program. R. D. Dighson (McDonnell Aircraft Co., St. Louis, Mo.). Corp., Bethpage, N.Y.). Society of Allied Weight Engineers, Annual Society of Allied Weight Engineers, Annual Conference, 38th, New Conference, 38th, New York, N. Y., May 7-9, 1979, Paper 1312. 36 York, N. Y., May 7-9, 1979, Paper 1293. 24 p. p. A primary requirement in the Hornet program is significant Two computerized preliminary design synthetic programs, reduction in life cycle cost from current Navy systems. In the present WISE-One and WISE-Two (Weight Integrated Sizing Evaluation), paper, the design and management techniques used to develop a new have been developed to facilitate the initial phases of preliminary fighter/attack system at an affordable life cycle cost are described. design. WISE-One is intended to calculate the TOGW of a design V.P. concept in the very early stages of preliminary design; layouts, bated on its output, are produced from a computer based design/drafting system. WISE-Two is used to optimize weight/cost of a preliminary design based on an existing layout to aid in producing a final A80-20639 Small ship-based VTOL aircraft - A design three-view drawing. WISE-One uses empirical methods, while WISE- exercise. J. W. Flaig (U.S. Naval Air Systems Command, Washington, Two used analytical tools (structural/weight multittation analysis). Both programs operate with minimum input and maximum output D.C.). Society of Allied Weight Engineers, Annual Conference, 38th, and are characterized by a dynamic methodology base and multi- New York, N. Y., May 7-9, 1979, Paper 1296. 23 p. V.L. Proposals for moderate performance VTOL aircraft, other than discipline interfaces. the AV-8, which could be based aboard small ships in the mid-to-late 1980's are examined. The vehicles were to have a takeoff gross weight of about 20,000 lb with minimal external stores, and to perform only vertical take-off and landings. Current high-bypass-ratio engines are studied as possible effective power plants. It is found that uprated versions of the Rolls Royce Pegasus-il engine give the most A80 .20647 A simple design synthesis method used to reasonable solutions. Attention is also given to hauldown and estimate aircraft gross weight. K. W. Higham (Vought Corp., Dallas, securing problems inherent in basing aircraft aboard small ships. It is Tex.(. Society of Allied Weight Engineers, Annual Conference, 38th, concluded that a lightly armed reconnaisance vehicle having a radius New York, N.Y., May 7-9, 1979, Paper 1313. i7p. of approximately 300 nmi appears feasible, provided that the mission The paper presents a preliminary weight methodology specifical- requirements remain simple. M.E.P. ly developed to augment synthesis techniques such as ASAP. Attention is given to two sample calculations, the first of which demonstrates a short method recommended only for aircraft with payloads in excess of twenty-five percent of the take-off weight. A A80-20640 Advanced technology effects on V/STOL pro- sub-sonic transport is used in this example. The second sample pulsive system weight. R. S. Saint John (Vought Corp., Dallas, Tex.). calculation demonstrates an expanded method which provides Society of Allied Weight Engineers, Annual Conference, 38th, New greater accuracy and cen result in a complete group weight summary York, N. Y., May 7-9, 1979, Paper 1300. 23 p.

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for balance calculations aid improved cost analysis. An advanced jet The reasons for the continuous increase in brands of oil for trainer is used in this example and it is noted that the second method aircraft gas-turbine engines are examined, and methods of unifying is best used when the payload is expected to be less than twenty-five them are suggested. Some brands of oil are recommended for percent of the take-off weight and is recommended for applications gas-turbine engines, depending on the temperature at which they where time allows. M.E.P. operate. V.P.

A80-20648 Problems associated with cargo airplanes A80-20866 having aft mounted engines. R. E. Stephens (Lockheed-Georgia Co., Computer simulation of an air cargo small package sorting system. A. Hargrove (Hampton Institute, Hampton, Marietta. Ga.). Society of A/lied Weight Engineers, Annual Confer- Va.). In: Modeling and simulation. Volume 10 - Proceedings of the ence, 38th, New York, N. Y., May 7-9, 1979, Paper 1314. 36 p. Tenth Annual Pittsburgh Conference, Pittsburgh, Pa., April 25-27, The effects of engine location are examined by means of 1979. Part 2. comparing a baseline configuration with four wing mounted engines Pittsburgh, Pa., Instrument Society of America, 1979, 333-340. with several arrangements. Initially the analysis makes some simpli- p. fying assumptions which allow the establishment of some trends. An automated baggage sorting system designed for use at the Three aircraft with engines mounted on the aft fuselage are new Atlanta Midfield Airport is reviewed. Adaptation of the system examined, each with a different approach to the solution to the to small air cargo packages is proposed. Computer simulation is used balance problems. Two of the configurations are analyzed further to analyze the system after reviewing results of manual simulation. and a third configuration, with two wing mounted engines and one This paper describes the simulation model, the parameters analyzed, tail mounted engine is added for comparison purposes. It is the sensitivity of those parameters and a possible Solution. (Author) concluded that the results indicate that if an aircraft is designed for use as a cargo aircraft, it should have wing mounted engines. M.E.P.

A80-20867 A survey of the stochastic filtering techniques for data processing in air-traffic control and surveillance systems, A. A80.20655 Navy V/STOL - A continuing initiative, R. G. Farina and S. Pardini (Selenia SpA., Rome, Italy). In: Modeling and Perkins, Jr. (U.S. Naval Air Systems Command, Washington, D.C.). simulation. Volume 10 - Proceedings of the Tenth Annual Pittsburgh Society of Allied Weight Engineers, Annual Conference, 38th, New Conference, Pittsburgh, Pa., April 25-27, 1979. Part 2. York, N. V., May 7.9 7979, Paper 1325. 26 p. Pittsburgh, Pa., Instrument Society of America, 1979, The progress of the project to develop a new subsonic p. 341-351. 23 refs. multimission V/STOL aircraft initiated by the Navy in 1976 has been The application of stochastic filtering techniques for air-traffic hampered by such problems as affordability, design complexity, and control and surveillance systems is examined. The structure of these justification of the V/STOL concept. A decision as to the usefulness systems, their operational requirements and the environment in of the program will be based on the results of the Sea Based Air which they work is studied. A review of various stochastic filters Master Study (SBAMS) which will provide a comparative analysis of such as adaptive and nonlinear filters are reviewed with respect to sea based aircraft alternatives. If the SBAMS supports the project, their different environments. Attention is given to the typical the design definition phase will be founded on the outputs of structure of radar data processing and to the adaptivity of filtering SBAMS, inical industry studies and technology advancement efforts. algorithms to target maneuver. C.F.W. A major aircraft development decision is not anticipated before 1982. V.L.

A80-20868 Shipping by air - Is the value of your time A80-20656 Weight impact of VIOL. S. Kalemaris and P. worth it. A. H. Hagedoorn (Florida Technological University, York (Grumman Aerospace Corp., Bethpage, N.Y.). Society of Allied Orlando. Fla.) and J. B. Crittenden (Virginia Polytechnic Institute Weight Engineers, Annual Conference, 38th, New York, N. V., May and State University, Blacksburg, Va.). In: Modeling and simulation. 7.9 1979, Paper 1326. 17 p. This paper studies the weight increments associated with vertical Volume 10 - Proceedings of the Tenth Annual Pittsburgh Confer- ence, Pittsburgh, Pa., April 25-27, 1979. Part 2. takeoff and landing capability as compared to conventional (horizon- tal) takeoff and landing )CTOL(. Weight increments for various Pittsburgh, Pa., Instrument Society of America, 1979, p. 391-396. - physical and ground rule requirements that transform a CTOL A cost comparison of cargo shipments by air, rail, and truck aircraft into a VTOL aircraft are evaluated. In order to fully transportation is outlined. The economic model comparisons indicate which mode of transportation should be used under various understand the weight increments, preliminary designs of comparable CTOL aircraft are examined, along with Grumman's VTOL designs. circumstances. Nonconventjonal characteristics of the system models include a nonlinear cargo density function and a method for the The 'VTOL weight penalty' for shipboard operation is further calculation of the value of time. (Author) defined by a study of the weight penalty for carrier basing a CTOL aircraft. The total effect of VTOL on subsonic aircraft, with low thrust required for CTOL, is presumably different from the effect on high performance supersonic aircraft with mission demands close to the VTOL requirement, and this difference is addressed. Finally, A80-20869 Models for freight access to air terminals. W. consideration is given to possible additional mission requirements for A. Rabiega (Portland State University, Portland, Ore.). In: Modeling CTOL aircraft that stem from the difference in operational capa- and simulation. Volume 10 - Proceedings of the Tenth Annual bility. (Author) Pittsburgh Conference, Pittsburgh, Pa., April 25-27, 1979. Part 2. Pittsburgh, Pa., Instrument Society of America, 1979, p. 397-401. 16 refs. Demand and traffic volume prediction are necessary to the A80.20690 # Unification of oils for aircraft gas-turbine modeling of freight access to air terminals. The 'abstract modes' engines (Unifikatsiia masel dlia aviatsionnykh gazoturbinnykh dviga' approach may be an appropriate demand submodel. Sequential telei). G. I. Novosartov, V. A. Smeianov, A. V. Vilenkin, and A. I. queue models can be used for the traffic submodel, but require Echin. Kh,miia i Tek/snologiia Topliv/4lasel, no. 11, 1979, p. 11-13. modification to the technologies, terminal configurations, and In Russian. operations of air freight. (Author)

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A80-20870 Air cargo container utilization optimization the hardware in the loop in a hybrid computer facility to simulate through modeling. R. M. Eastman (Missouri-Columbia, University, real-time trajectories. In this way, both the real flight microprocessor Columbia, Mo.). In: Modeling and simulation. Volume 10- Proceed- hardware and software will be verified. This paper presents such a ings of the Tenth Annual Pittsburgh Conference, Pittsburgh, Pa., hardware-in-the-loop analysis for two DAP5 designed for a tactical April 25-27, 1979. Part 2. Pittsburgh, Pa., six-inch test missile fitted with a semiactive laser seeker guidance Instrument Society of America. 1979. P. 403-406. 5 ref s. Army- head, and compares their performance. (Author) supported research, A dynamic programming model is used to solve the problem of optimal air cargo container utilization; other methods are examined but were found to be infeasible, too costly, or incapable of reaching A80-20904 Navigation error using rate of change of signal an optimal solution. Practical obstacles to widespread application of time of arrival from space vehicles. D. Terris (Rockwell International the model are discussed and alternatives mentioned. Attention is Corp.. Satellite Systems Div., Downey, Calif.I. In: Modeling and given to the dynamic programming model which is used to optimize simulation, Volume 10 - Proceedings of the Tenth Annual Pittsburgh the problem using various constraints and it is determined that the Conference, Pittsburgh, Pa., April 25-27, 1979. Part 5. model can be used to solve the problem of optimum air cargo Pittsburgh, Pa., Instrument Society of America, 1979, container utilization. C.F.W. p. 1847-1852. An error analysis model derived for a navigation concept using the measurement of rate of change of signal time of arrival (TOA dot) in addition to TOA is analyzed. An error equation for A80-20879 A nonlinear observer/command generator measurement of range in terms of TOA, error using TOA and TOA tracker approach to the XM-97 helicopter gun turret control law dot, and covariance error for TOA measurements only are discussed design. J. R. Broussard and S. W. Gully (Analytic Sciences Corp., along with covariance error for TOA dot measurements and for both Reading, Mass.). In: Modeling and simulation. Volume 10- Proceed- TOA and TOA dot measurements. Consideration is given to ings of the Tenth Annual Pittsburgh Conference, Pittsburgh, Pa., computer simulation. V.T. April 25-27, 1979. Part 2. Pittsburgh, Pa., Instrument Society of America, 1979, p. 599-609. 6 refs. Army. sponsored research. A80-20907 Recent developments in flight simulation tech- niques. D. Raptis and M. McKinnon (CAE Electronics, Ltd., Saint Laurent, Montreal, Canadal. In: Modeling and simulation. Volume 10 - Proceedings of the Tenth Annual Pittsburgh Conference, A80-20900 Infrared sensor system performance simula- Pittsburgh, Pa., April 25-27, 1979. Part 5. tions. F. T. Wu (U.S. Naval Weapons Center, China Lake, Calif.). In: Pittsburgh, Pa., Instrument Society of America, 1979, p. 1901-1906. Modeling and simulation. Volume 10 . Proceedings of the Tenth 5 reis. Annual Pittsburgh Conference, Pittsburgh, Pa., April 25 . 27, 1979. This paper presents she main concepts in the control of the Pittsburgh, Pa., Instrument Society of Part 5. motion of the cabin of an aircraft simulator, by using a six degree of America, 1979, p. 1755-1763. freedom electrohydraulic motion system controlled by a digital This paper reports on a simulation technique used for surface computer. The versatility and effectiveness of the cost function target search and detection by airborne infrared sensor systems. The approach for solving this constrained problem are demonstrated. The simulation provides a description of detection capability while the main areas of active research as well as future trends are discussed. sensor is in high speed motion (relative to the target) towards the (Author( target area. The simulation also permits the scanning pattern and scanning rate to be input to the simulation, thus allowing different types of scans for different inputs. Hence an optimal scanning pattern and rate can be determined for different sensor altitudes and speeds. The simulation is designed for both automatic and manual A80-20915 Covariance simulation of BCAS - An aircraft search and detection. However, the current version of she simulation llision avoidance system. H. J. Rome and G. Andriotakis (Lowell, is used for the automatic mode only since the manual search University, Lowell, Mass.). In: Modeling and simulation. Volume 10- algorithm is limited in its use to qualitative comparison of search Proceedings of the Tenth Annual Pittsburgh Conference, Pittsburgh, patterns. In this paper, the results of runs for several scanning Pa., April 25-27, 1979. Part 5. Pittsburgh, Pa., patterns are presented. For each scanning pattern, the scanning rate Instrument Society of America, 1979, p. 2049-2060. U.S. Depart- and fields-of-view have been varied. Some comparison of results is ment of Trans portation Contract No. TS-14698. presented. lAuthorl This paper presents algorithms developed and results obtained for a covariance simulation of BCAS-an aircraft collision avoidance system. The simulation models the stochastic environment, aircraft state uncertainties, and the various types of measurements available. The basic algorithms for optimal covariance analysis and specialized A80-20901 Verification of digital autopilot microproces- techniques utilized to obtain parameters germane to collision sor hardware and software via hardware-in-the-loop simulation. W. V. avoidance are presented. Simulation results which demonstrate the Albanes, J. T. Bosley (Computer Sciences Corp., Defense Systems effectiveness of the system and compare it to other collision Div., Huntsville, Ala.), and J. B. Meadows (U.S. Army, Technology avoidance systems are presented. (Author) Laboratory, Redstone Arsenal, AIa.l. In: Modeling and simulation. Volume 10 - Proceedings of the Tenth Annual Pittsburgh Confer- ence, Pittsburgh, Pa., April 25-27, 1979. Part 5. Pittsburgh; Pa., Instrument Society of America, 1979; p . 1815-1820. 8 refs. Simulation permits the early detection of possible (and costlyl errors in missile subsystem development. However, digital autopilot A80-20952 # Assessment at full scale of exhaust nozzle-to' performance is difficult and expensive to verify in a six-degree-of- wing size on STOL-OTW acoustic characteristics. U. von Glahn and freedom digital simulation due to the small time steps required to D. Groesbeck (NASA, Lewis Research Center, Cleveland, Ohio). simulate the digital effects of the microcomputer. To solve this Acoustical Society of America, Meeting, 98th, Salt Lake City, Utah, problem, a microprocessor-based digital autopilot (DAP( is used as Nov. 26-30, 1979, Paper. 25 p. 5 refs.

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On the basis of Static zero/acoustic data obtained at model scale, A80-20966 // Summary of advanced methods for predicting the effect of exhaust nozzle size on flyover noise is evaluated at full high s peed propeller performance. L. J. Bober and G. A. Mitchell scale for different STOL-OTW nozzle configurations. Three types of (NASA, Lewis Research Center, Cleveland, Ohio). American Institute nozzles are evaluated: a circular/deflector nozzle mounted above the of Aeronautics and Astronautics, Aerospace Sciences Meeting, 18th, wing, a slot/deflector nozzle mounted on the wing, and a slot nozzle Pasadena, Ca/if., Jan. 14- 16, 1980, Paper 80-0225. 12 p. 10 refs. mounted on the wing. The nozzle exhaust plane location, measured Three advanced analyses for predicting aircraft propeller perfor- from the wing leading edge was varied from 10 to 46 percent of the mance as high subsonic s peeds are described. Two of these analyses wing chord (flaps retracted). Flap angles of 20 deg (takeoff) and 60 use a lifsing line representation for the propeller blades and vortex deg (approach) are included in the study. Initially, perceived noise filaments for the blade wakes but differ in the details of the solution. levels (PNL) are calculated as a function of flyover distance at 152 m The third analysis iv a finite difference solution of the unsteady, altitude. From these plots static EPNL values, defined as flyover three-dimensional Euler equations for the flow between adjacent relative noise levels, then are obtained as functions of nozzle size for blades. Analysis results are compared to data for a high speed equal aerodynamic performance (lift and thrust). On the basis of propeller having 8 swept blades integrally designed with the spinner these calculations, the acoustic benefits attributable to nozzle size and nacelle. These, analyses provide tools for the propeller designer relative to a given wing chord size are assessed. (Author) ranging from a short running program for initial design studies to a very long running program for checking final configurations. (Author)

A80-20953 II Dispersion of sound in a combustion duct by fuel droplets and soot particles. J. H. Miles (NASA, Lewis Research A80-20968 # Scale model performance test investigation of Center, Cleveland, Ohio) and D. D. Raftopoulos (Toledo, University, exhaust system mixers for an Energy Efficient Engine /E3/ propul- Toledo, Ohio). Acoustical Society of America, Meeting, 98th, Salt sion system. A. P. Kuchar (General Electric Co., Cincinnati, Ohio) Lake City, Utah, Nov. 26-30, 1979, Paper. 27 p. 22 refs. and R. Chamberlin (NASA, Lewis Research Center, Energy Conser- Dispersion and attenuation of acoustic plane wave disturbances vative Engine Office, Cleveland, Ohio). American Institute of propagating in a ducted combustion system are studied. The Aeronautics and Astronautics, Aerospace Sciences Meeting, 18th, dispersion and attenuation are caused by fuel droplet and soot Pasadena, Calif. Jan. 14-16, 1980, Paper 80-0229. 10 p. emissions from a jet engine combustor. The attenuation and A scale model performance test was conducted as part of the dispersion are due to heat transfer and mass transfer and viscous drag NASA Energy Efficient Engine )E3) Program, to investigate the forces between the emissions and the ambient gas. Theoretical geometric variables that influence the aerodynamic design of exhaust calculations show sound propagation at speeds below the isentropic system mixers for high-bypass, mixed-flow engines. Mixer configura- speed of Sound at low frequencies. Experimental results are in good tion variables included 'lobe number, penetration and perimeter, as agreement with the theory. (Author) well as several cutback mixer geometries. Mixing effectiveness and mixer pressure loss were determined using measured thrust and A80-20964 # Comparison of inset suppressor data with nozzle exit total pressure and temperature surveys. Results provide a approximate theory based on cutoff ratio. E. J. Rice and L. J. data base to aid the analysis and design development of the E3 Heidelberg )NASA, Lewis Research Center, Cleveland, Ohio). mixed-flow exhaust system. )Author) American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 18th, Pasadena, Ca/if., Jan. 14-16, 1980, Paper 80-0100. 26 p. 21 refs. This paper represents the initial quantitative comparison of inlet A80-20969 ft Numerical simulation of supersonic inlets suppressor far-field directivity suppression with that predicted using using a three-dimensional viscous flow analysis. B. H. Anderson and an approximate liner design and evaluation method based upon mode C. E. Towne INASA, Lewis Research Center, Cleveland, Ohio). cutoff ratio. The experimental data was obtained using a series of American Institute of Aeronautics and Astronautics, Aerospace cylindrical point-reacting inlet liners on an Avco-Lycoming YF1O2 Sciences Meeting, 18th, Pasadena, Calif., Jan. 14- 16, 1980, Paper engine. The theoretical prediction program is based upon simplified 80-0384. 15 p. 20 refs. sound propagation concepts derived from exact calculations. These A three-dimensional fully viscous computer analysis, which indicate that all of the controlling phenomenon can be approxi- retains she viscous nature of the Navier-Ssokes equations, was mately correlated with mode cutoff ratio which itself is intimately evaluated to determine its usefulness in the design of supersonic related to the angles of propagation within the duct. The objective of inlets. This procedure sakes advantage of physical approximations to the theory-data comparisons is to point Out possible deficiencies in limit the high computer time and storage associated with complete the approximate theory which may be corrected. After all theoretical NavierStokes solutions. Computed results are presented for a Mach refinements have been made, then empirical corrections can be 3.0 supersonic inlet with bleed and a Mach 7.4 hypersonic inlet. applied. (Author) Good agreement was obtained between theory and data for both inlets. Revisits of a mesh sensitivity study are also, shown. (Author)

A80-20965 # Acoustic considerations of flight effects on jet A80-20970 ft An analytical and experimental study of a noise suppressor nozzles. U. von Glahn (NASA, Lewis Research short S-shaped subsonic diffuser of a supersonic inlet, H. E. Center, Cleveland, Ohio). American Institute of Aeronautics and Neumann, L. A. Povinelli, and R. E. Coltrin )NASA, Lewis Research Astronautics, Aerospace Sciences Meeting, 18th, Pasadena, Ca/if., Center, Cleveland, Ohio). American Institute of Aeronautics and Jan. 14-16, 1980, Paper 80-0164. 24 p. 14 refs. Astronautics, Aerospace Sciences Meeting, 18th, Pasadena, Ca/if., Insight into the inflight acoustic characteristics of high-velocity Jan. 14. 16. 1980. Paper 80-0386. 12 p. jet noise suppressor nozzles for supersonic cruise aircraft (SCA) is An experimental investigation of a subscale HiMat forebody and provided. Although the suppression of jet noise over the entire range inlet was conducted over a range of Mach numbers to 1.4. The inlet of directivity angles is of interest, the suppression of the peak noise exhibited a transitory separation within the diffuser but steady state level in the rear quadrant is frequently of the most interest. data indicated reastachment as the diffuser exit. A finite difference Consequently, the paper is directed primarily to the inflight effects procedure for turbulent compressible flow in axisymmetric ducts was at the peak noise level. Both single and inverted-velocity-profile used to successfully model the HiMAT duct flow. The analysis multistream suppressor nozzles are considered. The importance of technique was further used to estimate the initiation of separation static spectral shape on the noise reduction due to inflight effects is and delineate the steady and unsteady flow regimes in similar stressed. (Author) S-shaped ducts. (Author)

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A80-20971 # Flight and wind tunnel test results of the mechanical jet noise suppressor nozzle. R. D. FitzSimmons, A. A. McKinnon, E. S. Johnson (Douglas Aircraft Co., Long Beach, Calif.). and J. R. Brooks (Rolls-Royce, Ltd.. Derby, England). American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 18th, Pasadena, Calif., Jan. 14 . 16, 1980, Paper 80-0165. 49 p. 21 refs. Comprehensive acoustic and propulsion data are presented, based on flight and wind tunnel tests, of a mechanical jet noise suppressor designed to satisfy the requirements of an advanced supersonic transport (AST) under study by the McDonnell Douglas Corporation. The flight program was conducted jointly by MDC, Rolls-Royce Ltd., and-the British Aerospace Corporation, using an HS-125 aircraft modified to accept an upgraded RR Viper 601 engine with conical reference and mechanical suppressor nozzles and an acoustically treated ejector. The nacelle, engine and nozzle configurations from the l-(S . 125 were also tested in one of NASA's wind tunnels to obtain thrust performance at forward velocity and acoustic data. The acoustic flight test data, when scaled to an AST engine nozzle size and projected to a typical sideline distance, indicate reduction in effective perceived noise level of 16 EPNdB at the takeoff power setting, It is estimated that the in-flight thrust loss for a typical AST suppressor/ejector nozzle configuration (37.5 inch equivalent diameter) would be 5.4 percent at takeoff power settings and 6.6 percent at cutback power settings. V.L.

A80.20982 The Russian satellite navigation system. C. D. Wood and G. E. Perry. (Royal Society, Discussion on the Satellite Doppler Tracking and Its Geodetic Applications, London, England, Oct. 10, 11, 1978.) Royal Society (London), Philosophical Transac- tions, SeriesA, vol. 294, no- 1410, Jan. 14, 1980, p. 307-315. Since 1972. systematic analysis of Cosmos satellites, having near-circular orbits and periods close to 105 mm, has revealed that several groups have had the necessary orbital plane spacing to give the global coverage suitable for satellite navigation systems. Replace' ments have been launched at regular intervals. The current systems comprise three satellites with 60 deg spacing, six with 30 deg spacing and three with 45 deg spacing. These satellites have been shown to transmit on frequencies close to 150 and 400 MHz. The modulation of the 150 MHz carrier frequencies is explained together with the techniques employed to decode Standard Moscow Time, the satel' lite's position in geocentric Cartesian coordinates with corresponding rates of change at 3 mm intervals, plus the orbital parameters of all satellites forming the system. (Author)

A80-20992 The Global Positioning System. R. J. Anderle (U.S. Navy, Naval Surface Weapons Center, Dahlgreri, Va.). (Royal Society, Discussion on the Satellite Doppler Tracking and Its Geodetic Applications, London, England, Oct. 10, 11, 1978.) Royal Society (London), Philosophical Transactions, Series A, vol. 294, no. 1410, Jan. 14, 1980, p. 395-405; Discussion, p. 405, 406. The Global Positioning System is described. Consideration is given to the following aspects: the principle of operation; the experimental phase; alternatives for geodetic and geophysical applica- tions; error budget for navigation applications; ephemeris accuracy; accuracy of absolute geodetic positions; the effect of ephemeris errors on relative station positions; and the Doppler approach. B.J.

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N80- 14026

assist in alleviating the growing complexity are then considered. These include: design management aids, such as requirement statement languages: architectural considerations, such as multiplex data busses and distributed processing; and software techniques, such as high level languages, MASCOT, and structured programming. J.M.S. STAR ENTRIES

N80-14023# Deutsche Forschungs . und Versuchsanstalt fuer Luft- und Raumfahrt. Brunswick (West Germany). Inst. fuer N80-14017# Advisory Group for Aerospace Research and Flugfuehrung. Development, Neuilly-Sur-Seine (France). AN OBSERVER SYSTEM FOR SENSOR FAILURE DETEC- ADVANCES IN GUIDANCE AND CONTROL SYSTEMS TION AND ISOLATION IN DIGITAL FLIGHT CONTROL USING DIGITAL TECHNIQUES SYSTEMS Aug. 1979 357 p refs In ENGLISH and FRENCH Presented Norbert Stuckenberg In AGARD Advan. in Guidance and Control at the Guidance and Control Panel Symp.. Ottawa. 8-11 May Systems Using Digital Tech. Aug. 1979 11 p refs 1979 (AGARD-CP-272: I5BN-92-835-0247-7( Avail: NTIS Avail: NTIS HC A16/MF AOl HC A16/MF AOl For the sensor part of a flight control system a sensor failure The application of digital methods to guidance and control detection and isolation concept is presented based on analytic systems is considered. Functional design concepts, trends, and redundancy. A conventional triplex sensor system is replaced by requirements, advances in analytical and design techniques, and a duplex sensor system without loss of the fail-operational advances in digital system design and architecture to assure property. In the case of a sensor failure. deterministic Luenberger high integrity are among the topics covered. Data processing observers provide the information about which of the two and computation techniques, software design validation tech- sensors of the duplex system actually failed. The proposed concept niques. including simulation, and operational and system develop- is applied to a command and stability system of a flight control ment experience are included. system. Author

N80-14024# Office National d'Etudes et de Recherches N80.14.018*# Milco International, Inc.. Huntington Beach. Calif Aerospatiales, Toulouse (France). STATE OF THE ART FOR DIGITAL AVIONICS AND AUTOMATIC RECOVERY AFTER SENSOR FAILURE CONTROLS. 1978 ON BOAR D Richard K. Smyth In AGARD Advan. in Guidance and Control Marc Labarrere, Marc Pelegrin, and Marc Pircher In AGARD Systems Using Digital Tech. Aug. 1979 20 p refs Advan. in Guidance and Control Systems Using Digital Tech. Aug. 1979 12 p refs (Contract NASw'2691) Avail: NTIS HC A16/MF AOl CSCL 02A Avail: NTIS HC A16/MF AOl A brief summary of a comprehensive state of the art survey Two techniques are developed which provide reliable failure is presented. The survey includes five broadly applicable technology detection and isolation for a dual-redundant subset of sensors. areas: flight path management, aircraft control systems, crew A global procedure using a bank of stationary Kalman filters is station & human factors, integration & interfacing technology. described. Some difficulties of this technique lead to a sub-optimal and fundamental technology. In addition the survey included procedure which is developed in order to give all the dynamic military technologies which have a technology transfer potential and static relationships between the measured outputs on the '.o the five broadly applicable technology areas. J.M.S. aircraft. These techniques are sucessfully applied to simulated sensor failure on a six degree of freedom aircraft simulation N80-14019# Air Force Flight Dynamics Lab., Wright-Patterson and are applying to sensor failures injected on flight data from AFB. Ohio. Flight Control Div. the N262 aircraft. F.O.S. A FLIGHT CONTROL SYSTEM USING THE DAIS ARCHITEC- TU RE N80-14025# Marconi Avionics Ltd., Rochester (England). Flight A. P DeThomas and R. A. Hendrix In AGARD Advan. in Automation Research Lab. Guidance and Control Systems Using Digital Tech. Aug. 1979 RECENT ADVANCES IN FIBRE OPTICS FOR HIGH 9 p ref 5 INTEGRITY DIGITAL CONTROL SYSTEMS Avail: NTIS HC A16/MF AOl R. P. G. Colknson In AGARD Advan. in Guidance and Control The development of a digital flight control system simulation Systems Using Digital Tech. Aug. 1979 16 p capability to examine advanced integrated control architectures. in order to increase system performance and availability, is Avail: NTIS HC A16/MF AOl described. Near term issues, such as multiplexing interfaces with The methods for using fiber optic cables for interconnecting other avionics functions and structuring of software, are the elements of an active control system, and the advantages covered. J.M.S. and disadvantages are discussed. The major factors in the use of fiber Optics are practical ones, connectors, terminations. N8O-14020# Royal Aircraft Establishment. Farnborough ruggedness, and environmental capability of cables. The tech- (England). Flight Systems Dept. niques are described which were developed to make a fiber TRENDS IN DIGITAL DATA PROCESSING AND SYSTEM bundle a practical cable link. The use of multi-access optical ARCHITECTURE highways, particularly for interfacing other systems with the flight A. A. Callaway In AGARD Advan. in Guidance and Control control system, (e.g. Air Data and IN systems) is reviewed and Systems Using Digital Tech. Aug. 1979 5 p principles of the candidate networks outlined. Finally, a new concept for a fiber optic multi-access network is presented which Avail: NTIS HC A16/MF AOl is fully compatible with the new data transmission specification. The utilization of airborne digital computers and methods F.O.S. for their integration into digital avionic systems are discussed. The architecture of two aircraft systems, one designed in the N80-14026# General Dynamics/Fort Worth. Tex. 1 96Os and one in the 1970s is described. The growth in complexity REDUNDANCY MANAGEMENT CONSIDERATIONS FOR A is discussed in terms of two factors: the total flow of data CONTROL-CONFIGURED FIGHTER AIRCRAFT TRIPLEX between the subsystems which form the elements of the system. DIGITAL FLY. BY-WIRE FLIGHT CONTROL SYSTEM and the total volume of the computing task in terms of the John H. Watson, William J. Yousey, and James M. Railey In number of words of program required. Techniques which may AGARD Advan. In Guidance and Control Systems Using Digital II N80-14027

Tech. Aug. 1979 23 p ref system (ASIN) and a number of auxiliary sensors, namely, air data and strapdown magnetic sensors. In the present phase. (Contract F33615-77-C-3036) comprehensive software packages were developed to simulate Avail: NTIS HC A16/MF AOl all the subsystems used. A modular and computationally efficient To preclude the shut down of the flight control computers Kalman filtering algorithm was designed and implemented for for control configured fighter aircraft, redundant (parallel) the integration of the GPS and ASIN. During the course of the processing is used in conjunction with redundancy management development. two techniques were developed. An exact algorithm concepts. Using reliability requirements and goals as expressed was derived to transform inertially referenced data into geographic in loss-of-control per flight hour. a digital flight control system coordinates. Also, a dual channel attitude algorithm was architecture is evolved with specific emphasis placed on the formulated which increases the bandwidth of the attitude input, processor and output subsystems. The incorporation of an computation in the strapdown navigator. Other routines developed analog cross strapping of lower reliability sensors is shown to include the baro-damping algorithm, auxiliary sensor processing be an effective means of increasing system reliability by retaining and calibration routines. To provide a baseline level of performance. sensor redundancy after a computer failure. A technique called simulation results were obtained for future flight testing of the control law reconfiguration is developed which insures system hardware. M.M.M. survival after a second like sensor failure. Computer contribution to loss-of-control is reduced by the addition of system monitors which increase the computer self-test confidence level. The N80-14034# Twente Univ. of Technology. Enschede (Nether. resultant architecture is shown to have an inherent reliability lands). Dept. of Electrical Engineering. which is relatively insensitive to the configuration of the actuator METHODS FOR STRAP-DOWN AUITUDE ESTIMATION interface, thus allowing this interface to be designed based on AND NAVIGATION WITH ACCELEROMETERS hardware/software complexity tradeoffs. A.R.H. R. P. Offereins and M. J. L. Tiernego In AGARD Advan. in Guidance and Control Systems Using Digital Tech. Aug. 1979 20 refs N80-14027# Messerschmitt-Boelkow-Blohm G.m.b.H,, Munich p Avail: NTIS HC A16/MF AOl (West Germany). Aircraft Div. FAILURE DETECTION. ISOLATION AND INDICATION IN Methods are presented for calculating the attitude of a vehicle HIGHLY INTEGRATED DIGITAL GUIDANCE AND CONTROL from the signals of three linear and three angular accelerometers SYSTEM which are rigidly attached to the vehicle. Also course, velocity and position measurements relative to some object can be used. Wolfgang J. Kubbat In AGARD Advan. in Guidance and Control Systems Using Digital Tech. Aug. 1979 17 p Apart from the attitude. the velocity and position, with respect to this object, are also obtained as output signals. In fire control Avail: NTIS HC A16/MF AOl systems, filters for target position prediction and attitude determination can be combined ri this way. A broad spectrum of modern failure detection and isolation M.M.M. techniques is discussed and it is shown that the failure problem can be significantly reduced with technology and design, Several advanced methods such as vector redundancy, dissimilar N80-14036# Lockheed-Georgia Co., Marietta. redundancy, and methods applied to computers are described AN ASSESSMENT OF AND APPROACH TO THE VALIDA- and some are backed up by practical examples. Data bus orientated TION OF DIGITAL FLIGHT CONTROL SYSTEMS In guidance and control systems are considered Based upon a D. B. Mulcare and W G. Ness AGARD Advan. in Guidance practical realization example, guidelines are given for the use of and Control Systems Using Digital Tech. Aug. 1979 12 p refs MIL STD 1553 B in redundant applications. A R.H. Avail: NTIS HC A16/MF AOl Flight-critical digital flight control system functions are N80-14028# Electronique Marcel Dassault. St. Cloud (France). evaluated in the context of farther term implementations. The THE INTEGRITY OF ONBOARD COMPUTER PROGRAMS: quality and safety associated with fault tolerant. highly integrated. A SOLUTION (LINTEGRITE DES LOGICIELS EMBARQIJES: control oriented system implementations are emphasized. UNE SOLUTION] Technology needs are addressed so that the verification and G. Germain In AGARD Advan. in Guidance and Control Systems validation process for advanced digital flight control systems can Using Digital Tech. Aug. 1979 8 p refs In FRENCH be sufficiently developed and purposefully accomodated in system engineering methodologies. K.L. Avail. NTIS HC A16/MF AOl A solution is provided for insuring the integrity of the operating system onboard aircraft and engines. The principle effect is to increase the security of the system so as to make it N80-14037# Electronique Marcel Dassault, St. Cloud (France). homogeneous with that of- the material, which in the case THE AVIONICS COMPUTER PROGRAM: PRACTICAL considered. is very high. Interesting consequences are found in EXPERIENCES WITH A METHODOLOGY ILOGICIEL the level of reliability and maintainability of the system, as well AVIONIQUE: EXPERIENCES PRATIQUES DUNE METHOD- as the costs of validation. The means used are the simplest and OLOGIE] most economical possible. They are applied to the structure of J. Penn In AGARD Advan. in Guidance and Control Systems the operating system and hardware of a computer well adapted Using Digital Tech. Aug. 1979 17 p In FRENCH for onboard applications. Emphasis is placed on mechanisms for controlling address, which prevents all untimely destruction of Avail: NTIS HC A16/MF AOl the software. Transl. by A.R,H. The organization and methodology used in the construction of operating systems in the principle computers of the Mirage Fl and Mirage 200 aircraft are described. Particular emphasis is N80- 14031 # Defence Research Establishment, Ottawa. (Ontario). placed on the definition phases and program validation. DEVELOPMENT OF AIDING GPS/STRAPDOWN INERTIAL Transl, by A.R.H. NAVIGATION SYSTEM 0. F. Liang, 0. B. Reid (Lapp (Philip A.) Ltd.. Toronto), R. H. Johnson (S and S Software Ltd.. Ottawa). and B. G. Fletcher In AGARD Advan. in Guidance and Control Systems Using Digital Tech. Aug. 1979 15 p refs

Avail: NTIS HC A16/MF AOl N80. 14038# Westland Helicopters Ltd.. Yeovil (England). An overview is presented of the design and development of EXPERIENCE IN PRODUCING SOFTWARE FOR THE an integrated multisensor navigation system comprised of a GROUND STATION OF A REMOTELY PILOTED HELICOP- NAVSTAR GPS receiver, an aiding strapdown inertial navigation TER SYSTEM

112 N80-14051

J. P. Webby. P. L. Wescott. M. I. Tucker. and H. M. Smith In are applicable not only to Sonic-boom studies but also to the AGARD Advan. in Guidance and Control Systems Using Digital calculation of noise generated by a supersonic rotor or propeller Tech. Aug. 1979 9 p blade tip. Author

Avail: NTIS HC A16/MF AOl A Computer system to control the aircraft, produce graphic N8O14047*# Nevada Univ.. Las Vegas. displays, and handle data received from the aircraft was produced IWO DIMENSIONAL AERODYNAMIC INTERFERENCE using the Modular Approach to System Construction, Operation. EFFECTS ON OSCILLATING AIRFOILS WITH FLAPS IN and Test, written in CORAL 66 language. The overall design of VENTILATED SUBSONIC WIND TUNNELS the software and the methods used to design, code, and test Joseph Fromme. Michael Golberg. and John Werth Washington the software system are described in detail. K.L NASA Dec. 1979 150 p refs (Grant N5G-2 140) (NASA-CR-321O( Avail: NTIS HC AO7/MF AOl CSCL O1A N80-14042# Litton Systems (Canada) Ltd.. Rexdale. (Ontario). The numerical computation of unsteady airloads acting upon A HIGH ACCURACY FLIGHT PROFILE DETERMINING thin airfoils with multiple leading and trailing-edge controls in SYSTEM two-dimensional ventilated subsonic wind tunnels is studied. The Peter Roy Vousden and Peter Jonathori Gollop In AGARD Advan. foundation of the computational method is strengthened with a in Guidance and Control Systems Using Digital Tech. Aug. new and more powerful mathematical existence and convergence 1979 16 p theory for solving Cauchy singular integral equations of the first Avail: NTIS HC A16/MF AOl kind, and the method of convergence acceleration by extrapolation The characteristics of a system that determines the flight to the limit is introduced to analyze airfoils with flaps. New profile of an aircraft in three orthogonal coordinates to an accuracy results are presented for steady and unsteady flow, including of a few feet are described. A standard commercial quality inertial the effect of acoustic resonance between ventilated wind-tunnel navigation system provides the required aircraft dynamic and walls and airfoils with oscillating flaps. The computer program attitude data while a special infrared sensor provides periodic TWODI is available for general use and a complete set of updates. A digital computer implements an 18 state Kalman instructions is provided. Author filter for estimation of the inertial errors. Filter data is stored on magnetic tape for immediate reprocessing by a fixed interval Bryson-Frazier smoothing algorithm that further refines the system performance. The techniques, applied in real time, are controlled itt a multitask environment by a software operating system. Applications for the systems capability are discussed with emphasis on the initial purpose of providing an accurate self N80- 14049*// National Aeronautics and Space Administration. contained trajectory measuring system for ILS and MLS flight Ames Research Center, Moffett Field, C"lif. checking. Other uses such as airborne surveying and weapon EFFECT OF TIP PLANFORM ON BLADE LOADING CHARAC- release determining systems are examined. A.W.H. TERISTICS FOR A TWO-BLADED ROTOR IN HOVER John D. Ballard, Kenneth L. Orloff, and Alan B. Luebs (Gates Lear Corp., Wichita, Kan.) Nov. 1979 89 p refs (NASA-TM-78615; A-7939( Avail: NTIS HC A05/MF AOl N80-14043# Air Force Flight Dynamics Lab.. Wright-Patterson CSCL O1A AFB. Ohio. INTEGRATION OF FLIGHT AND FIRE CONTROL A laser velocimeter was used to study the flow surrounding Robert K. Huber In AGARD Advan. in Guidance and Control a 2.13 m diam. two-bladed. teetering model-scale helicopter rotor operating in the hover condition. The rotor system employed Systems Using Digital Tech. Aug. 1979 9 p refs interchangeable blade tips over the outer 25% radius. A Avail: NTIS HC A16/MF AOl conventional rectangular planform and an experimental ogee tip An evaluation of an integrated flight and fire control (IFFC( shape were studied. The radial distribution of the blade circula- system in modern fighter aircraft is described. The IFFC systems tion was obtained by measuring the velocity tangent to a closed for air to air gunnery, air to ground gunnery, and bombing are rectangular contour around the airfoil section at a number of outlined. The concept involves the coupling of fire control radial locations. A relationship between local circulation and bound commands into the flight control system. The concept will be vorticity was invoked to obtain the radial variations in the sectional tested on a F-15B aircraft. Primary modifications to the F-15B lifting properties of the blade. The tip vortex-induced velocity aircraft include the addition of a digital computer for flight control was also measured immediately behind the generating blade and fire control signal processing, an electro-optical tracker, and and immediately before the encounter with the following blade. a 1 553A multiplex bus for communication between the F- 15 The mutual influence between blade loading. shed vorticity, and central computer, the tracker, and the added digital computer. the structure of the encountered vortex are quantified by the The IFFC concepts, the planned hardware implementation on results presented and are discussed comparatively for the rectangular and ogee planforms. The experimental loading for the F-15B. and safety of flight considerations are discussed. A.W.H. the rectangular tip is also compared with predictions of existing rotor analysis. Author

N80- 14045*// National Aeronautics and Space Administration. Langley Research Center. Hampton. Va. SONIC-BOOM WAVE-FRONT SHAPES AND CURVATURES ASSOCIATED WITH MANEUVERING FLIGHT N80-14051 t # National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. Raymond L. Barger Dec. 1979 30 p refs (NASA-TP-1611; L-13339( Avail: NTIS HC A03/MF AOl MODIFICATION OF AXIAL COMPRESSOR STREAMLINE CSCL O1A PROGRAM FOR ANALYSIS OF ENGINE TEST DATA Sonic-boom wave shapes and caustic lines generated by an Jeffrey G. Williams Nov. 1979 49 p refs airplane performing a general maneuver are studied. The equations (NASA-TM-79312; E-268( Avail: NTIS HC A03/MF AOl CSCL are programmed for graphical output as a perspective view of O1A the wave shape. This quasi three-dimensional presentation An existing axial compressor streamline analysis computer provides a qualitative insight into the effects of the maneuver program to allow input of measured radial pressure and on the wave shape and the caustic locations. For the special temperature profiles obtained from engine or cascade data is case of planar maneuvers, the principal curvatures of the wave described. The proposed modifications increase the input flexibility front are derived. These curvatures are needed to calculate the and are accomplished without changing the computer program's sound field in the vicinity of a caustic. The results of the analysis input format. A.R.H.

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N80- 14052

N8O14O52 * # Kansas Univ. Center for Research. Inc., Lawrence. A formulation is given for calculating flutter frequency and Flight Research Lab. flutter speed for a problem with two degrees of freedom. Two THE QUASI-VORTEX-LATTICE METHOD FOR WINGS WITH different solutions for evaluating the flutter determinant are EDGE VORTEX SEPARATION Final Report presented and the results for each method are compared. A Jenn-Louh Pao and Edward Lan Jan. 1980 25 p refs program flow diagram, partial program listing, and a sample (Grant NsG-1537( problem with input and output for the two different methods (NASA-CR- 162530: CR1 NC-FRL-385- 1 ( Avail: NTIS are included. Although the method was developed for computing HC A02/MF AOl CSCL O1A flutter characteristics of a pylon installed in the NASA Langley The aerodynamic characteristics of wings with leading-edge VSTOL tunnel. it is sufficiently general to solve any flutter system vortex separation were predicted using a method based on a that can be characterized by two degrees of freedom. A.R.I-I. flow model with free vortex elements which are allowed to merge into a concentrated core. The calculated pressure distribution is N8O14O56* # Boeing Commercial Airplane Co.. Seattle. Wash. more accurate than that predicted by methods with discrete AN INVESTIGATION OF SEVERAL FACTORS INVOLVED vortex filaments alone. In addition, the computer time is IN A FINITE DIFFERENCE PROCEDURE FOR ANALYZING reduced approximately by half. A.R.H. THE TRANSONIC FLOW ABOUT HARMONICALLY OSCIL- LATING AIRFOILS AND WINGS N8O14O53*# Old Dominion Univ. Research Foundation, Norfolk. F. E. Ehlers. J. D. Sebastian. and W. H. Weatherill May 1979 Va. 89 p refs THEORETICAL STUDY OF AERODYNAMIC CHARACTERIS- (Contract NAS1-15128) TICS OF WINGS HAVING VORTEX FLOW Report. 1 Feb. - (NASA-CR . 159143; 06-48852) Avail: NTIS 31 Aug. 1978 I-IC A05/MF AOl CSCL O1A C. Subba Reddy Nov. 1979 63 p refs Analytical and empirical studies of a finite difference method (Contract NAS1-14193) for the solution of the transonic flow about harmonically oscillating (NASA-CR-159184( Avail: NTIS HC A04/MF AOl CSCL wings and airfoils are presented. The procedure is based on O1A separating the velocity potential into steady and unsteady parts The aerodynamic characteristics of slender wings having and linearizing the resulting unsteady equations for small separation induced vortex flows are investigated by employing disturbances. Since sinusoidal motion is assumed. the unsteady three different computer codes--free vortex sheet, quasi vortex equation is independent of time. Three finite difference investiga- lattice, and suction analogy methods. Their capabilities and tions are discussed including a new operator for mesh points limitations are examined, and modifications are discussed. Flat with supersonic flow, the effects on relaxation solution converence wings of different configurations: arrow, delta, and diamond of adding a viscosity term to the original differential equation, shapes, as well as cambered delta wings, are studied. The effect and an alternate and relatively simple downstream boundary of notch ratio on the load distributions and the longitudinal condition. A method is developed which uses a finite difference characteristics of a family of arrow and diamond wings is explored. procedure over a limited inner region and an approximate analytical The sectional lift coefficients and the accumulated span loadings procedure for the remaining outer region. Two investigations are determined for an arrow wing and are seen to be unusual concerned with three-dimensional flow are presented. The first in comparison with the attached flow results. The theoretically is the development of an oblique coordinate system for swept predicted results are compared with the existing experimental and tapered wings. The second derives the additional terms values. A.W.H. required to make row relaxation solutions converge when mixed flow is present. A finite span flutter analysis procedure is described N8O14O54*# Old Dominion Univ. Research Foundation, Norfolk. using the two-dimensional unsteady transonic program with a Va. full three-dimensional steady velocity potential. Author OPTIMIZED AERODYNAMIC DESIGN PROCESS FOR SUBSONIC TRANSPORT WING FITTED WITH WINGLETS John M. Kuhlman Dec.- 1979 184 refs p N80-14058# Messerschmjtt'Boelkow-Blohm G.m.b.H., Otto- (Contract NsG-1357( brunn (West Germany). Unternehmensbereich Flugzeuge. (NASA-CR-15918O) Avail: NTIS HC A09/MF AOl CSCL HIGH ANGLE OF ATTACK CHARACTERISTICS OF O1A DIFFERENT FIGHTER CONFIGURATIONS The aerodynamic design of a wind-tunnel model of a wing Helmut John and Kraus Werner 7 Sep. 1978 40 refs representative of that of a subsonic jet transport aircraft, fitted p Presented at Symp. on High Angle of Attack Aerodyn., Sandefjord. with winglets, was performed using two recently developed Norway, 4-6 Oct. 1978 optimal wing-design computer programs. Both potential flow codes (MBB-UFE-1443(O(( Avail: NTIS HC AO3/MF AOl use a vortex lattice representation of the near-field of the Basic aerodynamic characteristics of different fighter confige- aerodynamic surfaces for determination of the required mean rations at separated flow beyond maximum lift where the resultant camber surfaces for minimum induced drag. and both codes derivatives are completely different from those associated with use far-field induced drag minimization procedures to obtain the attached flow are reviewed. The change in trim conditions is required spanloads. One code uses a discrete vortex wake model primarily dependant on wing planform and overall aircraft fo this far-field drag computation, while the second uses a 2-0 configuration. Results are shown for the aerodynamic development advanced panel wake model. Wing camber shapes for the two of aircraft configurations which meet these requirements and, at codes are very similar. but the resulting winglet camber shapes the same time. minimize the resulting drag penalties in the differ widely. Design techniques and considerations for these conventional angle of attack regime. Furthermore, problem areas two wind-tunnel models are detailed, including a description of and deficiencies must be identified to allow the definition of the necessary modifications of the design geometry to format it concepts for stabilizing such configurations artificially by aid of for use by a numerically controlled machine for the actual a flight control system. It is shown that an auxiliary momentum model construction. Author generating system is necessary for controlling the aircraft at flight conditions where aerodynamic control power is not sufficient. Author (ESA( N8O14O55*# National Aeronautics and Space Administration. Langley Research Center, Hampton. Va. A COMPUTERIZED METHOD FOR CALCULATING FLUTTER N80-14061# Aeronautical Systems Div., Wright-Patterson AFB, CHARACTERISTICS OF A SYSTEM CHARACTERIZED BY Ohio. Technical and Resources Management Div. TWO DEGREES OF FREEDOM AERONAUTICAL SYSTEMS TECHNOLOGY NEEDS: ES- Winifred A. Stalnaker and William F. Hunter Nov. 1979 52 p CAPE. RESCUE AND SURVIVAL Annual report for calendar ref year 1979 (NASA-TM-8O153( Avail: NTIS HC AO3/MF AOl CSCL Donald C. Kittinger Aug. 1979 30 p refs Supersedes O1A ASD-TR-78-2 1

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)AD-A074906; ASD-TR-79-5038; ASD-TR-78-21) Avail: NTIS N8O-14067// Selenia S.p.A.. Rome (Italy). Div. Radar e Sistemi HG A03/MF AOl CSCL 06/7 Civili. This report is a part of a Compilation of formalized Technology METHODOLOGY FOR THE EVALUATION OF A RADAR SITE Needs TN covering Equipment Subsystems as identified in the Final Report IMET000LOGIA Dl VALUTAZIONE DI UN Aeronautical Systems Division. They are based on development! SITO RADAR] operational experience, systems studies and new concepts - all B. Labozzetta In Fond. Ugo Bordoni On Radar in Air Traffic related to future system applications. Their presentation is to Control Jul. 1979 p 25-30 In ITALIAN: ENGLISH summary serve a threefold purpose. i.e.. 1 guidance for technology program. 2 proven development potential, and 3 engineering data! Avail: NTIS HG A21/MF AOl requirements essential for technology use in systems. The The technical and economical factors involved in a radar identified needs delineate progress desired in performance. site selection are described. The operation requirements are control, design flexibility, safety and cost. GRA expressed as covered volume, and data flow rate. The macrositing and micrositing criteria are discussed jointly with the analysis of the factors that determine the radar performance for reducting N80-14063# Air Force Engineering and Services Center. Tyndall the candidate sites. The fixed echoes, the angles, other signal AFB. Fla. Directorate of Environmental Planning. interference, the overall visibility, and the impact on environment AN EVALUATION OF THE BIRD/AIRCRAFT STRIKE are examined as relevant to the procedure. The analysis is limited HAZARD AT BARKSDALE AIR FORCE BASE. LOUISIANA to implementation cost only. Running costs are deemed similarly (SAC) Final Report structured. Author (ESA) Jeffrey J. Short and James S. Kent Feb. 1979 68 p NTIS )AD-A074390: AFESC-TM-2-79) Avail: N80-14068# Selenia SpA.. Rome (Italy). HG A04/MF AOl CSCL 06/6 PERFORMANCE EVALUATION METHODS OF A SECON- Barksdale Air Force Base was surveyed from 31 January to DARY RADAR NETWORK Final Report [METODI DI 9 February 1979 by the Air Force Engineering and Service Center's VALUTAZIONE DELLE PRESTAZIONI DI UNA RETE DI Bird/Aircraft Strike Hazard Team. During this period, operational RADAR SECONDARII and environmental factors which combine to create bird strike G. Fraschetti and U. Merlo (Fond. Ugo Bordoni. Rome) In Fond. hazards were observed. Specific recommendations based on Ugo Bordoni On radar in Air Traffic Control Jul. 1979 p 3 1-41 observations are provided to reduce the bird strike hazard. GRA refs In ITALIAN: ENGLISH summary

Avail: NTIS HG A21/MF AOl Interference in secondary surveillance radar is evaluated. N8O-14O64jl Lincoln Lab., Mass. Inst. of Tech.. Lexington. Analytical and simulation methods for the evaluation of the effects AIR TRAFFIC DENSITY AND DISTRIBUTION MEASURE- of sensor network and transponder spatial density on detection MENTS probability, azimuth measurement, and code identification are W. H. Harman 3 May 1979 63 refs p proposed. Some results obtained under a typical Italian air traffic (Contract DOT-FA77WAI-817; FAA Proj. 052-241-04) condition, taking into account propagative effects, are reported. )AD-A073229: FAA-RD-78-45; ATC-8O) Avail: NTIS Extention of the proposed methods to the case of monopulse HC AO4/MF AOl CSCL 01/2 radar is also outlined. Author )ESA) The measurements made in 1976 to determine the peak air traffic density. the spatial distribution, and the variation with Compagnia Italiana Servizi Tecnici, Rome. time for transponder equipped aircraft in the Los Angeles area N80-14069# and at several locations on the east coast are presented. The ORGANIZATION OF AN INTEGRATED GLOBAL MAINTE- use of these measurements for the design and evaluation of the NANCE SERVICE Final Report [ORGANIZZAZIONE DI UN discrete address beacon system and the air traffic control radar SERVIZIO INTEGRATO DI MANUTENZIONE GLOBAI.E] R. Grazi In Fond. Ugo Bordoni On Radar in Air Traffic Control beacon system is discussed. A.W.H. Jul. 1979 p 43-54 In ITALIAN: ENGLISH summary Fondazione Ugo Bordoni. Rome (Italy). N80-14065# Avail: NTIS HC A21/MF AOl ON RADAR IN AIR TRAFFIC CONTROL Final Report [IL The development of integrated maintenance techniques is RADAR NEL CONTROLLO DEL TRAFFICO AEREO] examined to better satisfy the requirements of a future comprehen- Jul. 1979 485 refs In ITALIAN: ENGLISH summary Proc. p sive radar system. The present situation is described showing of lectures at CNR Aiuti alla Navagazione a Controllo del Traffic that the present organization for air traffic control is adequate Aereo, Rome 3-5 Jul. 1979 for present and immediate future requirements. For the planned (FUB-1 1-1979) Avail: NTIS HC A21/MF AOl expansion of the radar network an automated. and centralized A collection of 41 papers is presented, grouped in the following radar control is proposed. The details of the technical control main chapters: planning and operation of radar networks. centers and the organization of the new system are discussed. automation in air traffic control, processing and visualization of Author (ESA) radar data, developments in primary radar, radar antennas and wave propagation. and developments in secondary radar.

N80-14070# Consiglio Nazionale delle Ricerche, Rome (Italy). N8O-14066# Aeronautica Militare Italiana, Rome. Central di Studi dei Sistemi di Controllo e Calcolo Automatici. PROBLEMS RELATED TO THE DESIGN AND CONSTRUC- AUTOMATION OF FLIGHT ON-LINE STRATEGIC CONTROL: TION OF A .RADAR NETWORK Final Report [PRO- THE CASE OF SPEED CONTROL ON PRE.ESTABLISHED B LEM ATI C HE NELL'IMPOSTAZIONE E REALIZZAZIONE ROUTES Final Report IL'AUTOMAZIONE DEL CONTROLLO DELLA RETE RADAR] STRATEGICO ON-LINE DELVOLI: IL CASO DEL CONT- A. Tangorra In Fond. Ugo Bordoni On Radar in Air Traffic ROLLO Dl VELOCITA SU ROTTE PRESIABILITE] L. Bianco, M. Cmi. and L. Grippo In Fond. Ugo Bordoni On Control Jul. 1979 p 14-23 In ITALIAN: ENGLISH summary Radar in Air Traffic Control Jul. 1979. p 58-68 rets In Avail: NTIS HG A21/MF AOl ITALIAN: ENGLISH summary The radar planning for Italy. issued in 1976 by the Italian Air Force, is discussed. The more interesting features connected Avail: NTIS HG A21/MF AOl with the construction of a radar center are examined with special The problem of on-line strategic control is examined with regard to operational availability. automation, and costs. Some reference to speed control on preassigned routes, and under the of the problems of the execution phase are especially analyzed. hypothesis that planning is performed for each flight on the including siting criteria, social and administrative problems, and basis of the first in, first out discipline. The control problem is coordination between various organizations involved. formulated as a constrained mathematical programming problem. Author (ESA) A real time working algorithm is proposed. Author (ESA) N80-14071

N80-14071# Consiglio Nazionale delle Ricerche. Rome (Italy). Avail: NTIS HC A21/MF AOl Centro di Studi dei Sistemi di Controllo e Calcolo Automatici. Some algorithms for target tracking by means of track-while- RADAR DATA UTILIZATION IN AUTOMATING THE scan techniques are analyzed. Some models of target paths, SEQUENCING OF AIRCRAFTS IN TERMINAL AREAS Final matched to typical air traffic control trajectories, are shown. In Report ILUTILIZZAZIONE DEl DATA RADAR NEL- the case of multiradar systems, additional causes of measurement LAUTOMAZIONE DEL SEGUENZIAMENTO DEGU AEREI error are discussed, and some ways to integrate information IN AREA TERMINALE] coming from different radars are compared. Author (ESA) L. Bianco, S. Ricciardelli, G. Rinaldi, and A. Sassano In Fond. Ugo Bordoni On Radar in Air Traffic Control Jul. 1979 p 69-79 refs In ITALIAN; ENGLISH summary N80-14075# Selenia SpA., Rome )ltaly). Div. Radar e Sistemi Civili. Avail: NTIS HC A21/MF AOl A DISTRIBUTED PROCESSING SYSTEM FOR RADAR DATA A mathematical model for aircraft sequencing is presented, PRESENTATION Final Report [SISTEMA DI PROCESSING and an optimizing algorithm is proposed including some tests E PRESENTAZIONE DATI RADAR A STRUTTURA DIS- results. The algorithm finds the optimum by progressively TRIBUITA] restricting the set of admisable sequences, and evaluating each G. Barale In Fond. Ugo Bordoni On Radar in Air Traffic Control time preset value function related to the given objectives. As a Jul. 1979 p 123-134 In ITALIAN; ENGLISH summary programming language FORTRAN 5 was used on a Univac 1110/22 computer for the test method. The results show Avail NTIS HC A21/MF AOl satisfactory operation of the algorithm in the tested interval, The main processing functions used for radar data handling especially in relation to the problem of real time operation. in air traffic control automated systems are described using the Author (ESA) example of a distributed processing system based on a minicompu- ter architecture in which all the system functions are performed. N8O-14072# Consiglio Nazionale delle Ricerche, Rome (Italy). Another example consisting of recent studies on a multiprocessor 1st. di Automatica. systems for air traffic control is also given. Author )ESA( TACTICAL ANALYSIS OF CONFLICTS IN AN AIR TRAFFIC CONTROL SYSTEM: DESIGN AND IMPLEMENTATION OF N80-14076# Selenia S pA.. Rome (Italy). Div. Radar e Sistemi A PROVISIONAL MODEL Final Report IANALISI DEl Civili. CONFLIUI IN UN SISTEMA ATC SU BASE TATTICA: FILTERING OF SYNTHETIC RADAR DATA Final Report COSTRUZIONE Dl UN MODELLO Dl PREVISIONE E SUA [FILTRAGGIO DELL'INFORMAZIONE RADAR SINTETICA) IMPLEMENTAZIONE] N. lafolla and R. Petrioli (Fond. Ugo Bordoni) In Fond. Ugo P. Bertolazzi and M. Lucertini In Fond. Ugo Bordoni On Radar Bordoni On Radar in Air Traffic Control Jul. 1979 p 135-142 in Air Traffic Control Jul. 1979 p 81 . 89 refs In ITALIAN: In ITALIAN; ENGLISH summary ENGLISH summary Avail: NTIS I-IC A21/MF AOl Avail: NTIS I-IC A21/MF AOl Further processing of radar data coming out of the primary An algorithm for the conflict alert automated function in an and secondary extractors is studied to reduce mistakes and noise air traffic control system is described. The influence of radar level by using space and time correlations wider than those errors is analyzed and the numerical results on computing time currently adopted in radar sensors and extractors. The most and on reliability are presented. The program conflict analysis frequent anomalies of primary and secondary radar data are first was tested with artificial data and with experimental data from reviewed. A detailed description of synthetic radar data filtering Rome and Genoa. The results show that no false alarms occured, is presented, and then compared to a multiradar air traffic control and that the average CPU time (Univac 1100/22) for a constant system with distributed architecture. It includes the initial plot load of 30 artificial trajectories is in the order of one second. processing, the plot combination, the signature-plot association, Author (ESA) the logic of signature characterization, and the multiradar combination and special processing. The aim is to simulate human N8O-14073# Consiglio Nazionale delle Ricerche, Pisa (Italy). operator data processing leading to a possibility of further 1st. di Elaborazione dell'Informazione. automation of radar surveillance systems. Author )ESA( SIMULATION OF A SURVEILLANCE AND CONTROL SYSTEM OF SURFACE TRAFFIC IN AN AIRPORT Final N80-14077# Selenia SpA., Rome (Italy). Report ISIMULAZIONE DI UN SISTEMA DI SORVEGLIANZA VISUAL DISPLAYS FOR AIR TRAFFIC CONTROL DATA E CONTROLLO DEL TRAFFICO SUPERFICIALE DI UN Final Report [SISTEMI DI VISUALIZZAZIONE DEl DATI AEROPORTO] ATC] M. Mercatanti. G. Bastianini, U. Fern. and M. Saliba In Fond. Franco Odoardi In Fond. Ugo Bordoni On Radar in Air Traffic Ugo Bordoni On Radar in Air Traffic Control Jul. 1979 p 91-101 Control Jul. 1979 p 143-153 In ITALIAN; ENGLISH summary refs In ITALIAN Avail: NTIS HC A21/MF AOl Avail: NTIS HC A21/MF AOl The main requirements of a program for the simulation of a A review of visual displays for air traffic control data is surveillance and control system are examined for the case of a presented. Topics discussed include: raw radar data and computer system using primary radar to control aircraft and service vehicles. generated data mixed systems. maximum displayable load and Several complexity levels of the system are proposed correspond- readability of synthetic data in a very bright environment, dedicated ing to program modules. A minimum configuration of the program displays and requirements, and color display and digital scan includes airfield definition data, simulation of radar signals from converter developments. Author (ESA) aircraft on the airport surface, recognition of the aircraft based upon radar signals and identification data given to the system at the landing stage, and representation on a video screen of N80-14086# Selenia SpA., Rome (Italy). the airport, and the aircraft identified by corresponding labels. IMPLEMENTATION OF AIR TRAFFIC CONTROL RADAR Author )ESA) RECEIVERS WITH FAST FOURIER TRANSFORM PROCES- SORS Final Report [INTEGRAZIONE COERENTE CON FFT NEI RICEVITORI RADAR PER ATCI N8O-14O74j Selenia SpA., Rome (Italy). TRACKING ALGORITHMS FOR MONO AND MULTIRADAR In Fond. Ugo Bordoni On Radar in Air Traffic Control Jul. Final Report [ALGORITMI DI TRACKING MONO E MULTI 1979 p 249-260 In ITALIAN; ENGLISH summary RADAR] S. Pardini, N. Del (Florence Univ.). and G. Zappa (Florence Univ.) Avail: NTIS HC A21/MF AOl In Fond. Ugo Bordoni On Radar in Air Traffic Control Jul. The main radar problems concerning present and future air 1979 p 111-122 refs In ITALIAN; ENGLISH summary traffic control )ATC) radars are briefly reviewed with emphasis

116 N80-14105

on moving clutter. The equivalence between a fast Fourier N80-14100# Selenia SpA.. Rome (Italy). transform (FFT) processor and a Doppler filter bank is shown. A ANTIREFLECTION TECHNIQUES FOR DETECTING FALSE video FFT receiver for an ATC radar is described. Results on TRACKS IN AIR TRAFFIC SURVEILLANCE WITH SECOND- the performance of the FF1 receiver are compared to that of ARY RADAR Final Report ITECHNICHE ANTIRIFLES- the moving window receiver, It is concluded that in a clutter SIONE PER LA INDIVIDUAZIONE DELLE FALSE TRACCE free environment the FFT receiver has greater losses, while in NELLA SORVEGLIANZA AEREA CON RADAR SECOND- moving clutter it shows relevant advantages. Author (ESA) ARI1 G. Fraschetti. D. Giuli (Florence Univ.). and V. Sacco (Florence N80-14087# Segnalamento Marittimo ed Aereo SpA.. Florence Univ.) In Fond. Ugo Bordoni On Radar in Air Traffic Control (Italy). Jul. 1979 p 415-424 refs In ITALIAN; ENGLISH summary DEVELOPMENT TRENDS OF AIRPORT SURFACE TRAFFIC CONTROL RADAR Final Report [PREVEDIBIU SVILUPPI Avail: NTIS HC A21/MF AOl DEL RADAR PER IL CONTROLLO DEL TRAFFICO SULLA Algorithms are presented which allow the target reports to SUPERFICIE AEROPORTUALE] be processed for false target and false track detection in order S. Betini. M. Piattelli. and G. Defina In Fond. Ugo Bordoni On to avoid the consequent problems in secondary surveillance radar Radar in Air Traffic Control Jul. 1979 p 261-267 In ITALIAN; systems. The procedure is based upon the following characteristics ENGLISH summary of false tracks due to reflections: (1) same codes for false and true reports. (2) same elevation. (3) larger distance for the false Avail: NTIS HC A21/MF AOl report. (4) 'corresponding azimuth of the false report with that The systems in use, and development trends are examined. of a fixed obstacle, and (5) correlation is kept between both pointing out that surface traffic growth in airports makes reports of the same radar sweep. Experimental results ,are economically attractive a generalized use of dedicated radar presented, showing that 2.74% of the reports were declared sensors. It is shown that trends at present are oriented towards false, while 2.42% of those reports were correlated with a false the I and J band frequencies which are more reliable in rainfall, track. Author (ESA) while some time ago the millimeter waves were studied because of their higher angular resolution. Some specific techniques. together with new electronic components suggest that it is possible to develop a fully operative, cost-effective device. Author (ESA)

N80-14088# Consiglio Nazionale delle Ricerche. Florence (Italy). N80-14104# Trieste Univ. (Italy). 1st. di Elettrotecnia ed 1st. di Ricerca sulle Onde Eiettromagnetiche. Elettronica. AN AIR TRAFFIC CHANNEL SIMULATION BY MEANS OF AUTOMATIC SYSTEMS FOR AIRPORT SURFACE MOBILE RAY-TRACING TECHNIQUES Final Report [LA SIMULAZ- MEDIA SURVEILLANCE BASED ON THE USE OF SECOND- lONE DEL CANALE AERONAUTICO PER MEZZO DI ARY MEDIA Final Report ISISTEMI AUTOMATICI PER TECNICHE Dl RAY-TRACING] LA SORVEGLIANZA DEl MEZZI MOBILI SU UNA SUPER- P. Beni. F. Bertini. and P. F. Pellegrini In Fond. Ugo Bordoni FICIE AEROPORTUALE BASATI SULLUSO DEL RADAR On Radar in Air Traffic Control Jul. 1979 p 277-285 In SECONDARIOI ITALIAN; ENGLISH summary E. Carli, T. Corzani. G. Falciasecca (Bologne Univ.). F. Ferdani (Fond. Ugo Bordoni). L. Mania, and F. Vatalaro In Fond. Ugo Avail: NTIS HC A21/MF AOl Bordoni On Radar in Air Traffic Control Jul. 1979 p 467-476 A three-dimensional ray tracing procedure is described which refs In ITALIAN: ENGLISH summary was used for propagation studies on the secondary surveillance radar (SSR( RF aeronautical channels. This procedure is based Avail: NTIS HC A21/MF AOl on the numerical integration of the ray canonical equations The studies carried out on airport surface surveillance systems originating from the geometric optics. Phenomena such as suggest the use of secondary radar for a fully automated solution. multipath (due to the specular reflections) and shadowing, can Some techniques tried in other countries are first reviewed and be investigated by means of this method of numerical computer then an original one is advanced. It is based on the combination simulation. The computed ray paths of the RF energy, utilizing of the hyperbolic/azimuth interrogation and the side lobe an environment model (whichincludes a tridimensional true model suppression technique. The system can be implemented with of the ground surface and of the atmosphere, constructed from free space propagation, or by means of open waveguides. The - experimental data) can be compared with propagation data open waveguide propagation is the more promising one but its (measured) obtained in real situations. The theoretical formula- feasibility is conditioned to the design of a suitable Structure. tion of ray tracing is summarized. A description is given of the Some significant results are presented. Author (ESA) procedure followed for modelling the ground surface, and an example of ray tracing is presented Author (ESA)

N8O-14105// Politecnico di Torino (Italy). 1st. di Elettronica e Telecommunicazioni. N80-14092# Consiglio Nazionale delle Ricerche. Florence (Italy). ONBOARD COLLISION AVOIDANCE SYSTEM: ENVIRON- 1st. di Ricerca sulle Onde Elettromagnetiche. MENTAL INFLUENCE ON THE TRACKING ALGORITHM 1-BAND MEASUREMENTS IN THE AIR TRAFFIC CHANNEL REQUIREMENTS Final Report [SISTEMI DI ANTICOL- TO CHARACTERIZE SECONDARY RADAR SYSTEMS Final LISIONE Dl BORDO: INFLUENZE DELLAMBIENTE Report [MISURE SUL CANALE AERONAUTICO IN BANDA OPERATIVO SUI REQUISITI DEGLI ALGORITMI DI L Al FINI DELLA CARATERRIZZAZIONE DI SISTEMI DI TRACKING I RADAR SECONDARI] V. Castellani and M. Pent In Fond. Ugo Bordoni On Radar in P. F. Pellegrini. R. Cappadona. R. Ruisi, M. Trambusti. and V. Air Traffic Control Jul. 1979 p 477-486 refs In ITALIAN: Venturi In Fond. Ugo Bordoni On Radar in Air Traffic Control ENG LISH summary Jul. 1979 p 323-332 In ITALIAN; ENGLISH summary Avail: NTIS HC A21/MF AOl Avail: NTIS HC A21/MF AOl A simulation program was studied to assess the performance The equipment used to characterize secondary radar propaga- of an airborne secondary surveillance radar collision avoidance tion channels is described. The equipment includes a transmitting system. Some first qualitative results are given, and the system, a receiving system, and a data processing system. Part implementation of tracking and prediction algorithms is discussed. of the apparatus was designed to be airborne, and part to be The problem of preventing interfererke effects is discussed used on the ground independently. or with a radar system. showing the need for the development of suitable algorithms to Author (ESA) that effect. Author (ESA)

117 N80-14106

N80-14106# Arinc Research Corp.. Santa Ana. Calif. (Contract DAAKSO-78-C-0008( AVIONICS INSTALLATION (AVSTALU COST MODEL FOR (AD-AO7O8O6; USAAVRADCOM . TR . 79-30) Avail: NTIS USER EQUIPMENT OF NAVSTAR GLOBAL POSITIONING HC A05/MF AOl CSCL 01/3 SYSTEM Non-contact Contour measurements of helicopter rotor blades W. Stewart, D. Allen. and P. Orth Jun. 1979 48 p to accuracies of 0.000 1 in. are possible via range finding by (Contract F04701-78-C-0124) triangulation employing electro-optical techniques. A laboratory (AD-A073681; Rept- 1727-04-1-1959) Avail: NTIS breadboard of such a system has been built and tested. The HC A03/MF AOl CSCL 17/7 results of these tests indicate that the construction of a full An avionics installation (AVSTALL) cost model developed prototype system is feasible and desirable. GRA for application to the NAVSTAR Global Positioning System (GPS) is described. The model determines the aircraft-peculiar costs of N80- 1411 3*# National Aeronautics and Space Administration. installing avionics equipment--for example. GPS user equipment-- Lewis Research Center. Cleveland. Ohio. into military aircraft. It is based on cost estimating relationships DIGITAL SYSTEM FOR DYNAMIC TURBINE ENGINE BLADE (CERs) developed from an analysis of 51 previous Class V avionics DISPLACEMENT MEASUREMENTS modifications to Air Force aircraft. The development and Louis J. Kiraly 13 Mar. 1979 13 rets Proposed for application of these CERs are explained in this report. GRA p presentation at 25th Ann. Intern. Gas Turbine Conf. and the 22d Ann. Fluids Engr. Conf.. New Orleans. 9-13 Mar. 1980; N8O141O7* National Aeronautics and Space Administration. sponsored by Am. Soc. of Mech. Engr. Ames Research Center, Moffett Field, Calif. (NASA-TM . 81382; E-288( Avail: NTIS HC AO2/MF AOl CSCL ACOUSTICALLY SWEPT ROTOR Patent 21E Fredric H. Schmitz, Donald A. Boxwell, and Rande Vause. inventors An instrumentation concept for measuring blade tip displace- (to NASA) Issued 25 Sep. 1979 23 p Filed 8 Sep. 1977 ments which employs optical probes and an array of micro- Supersedes N77-31 130 (15 - 22. p 2893) computers is presented. The system represents a hitherto unknown (NASA-Case-ARC- 11106-1: US-Patent-4, 168,939; instrumentation capability for the acquisition and direct digitization US-Patent-Appl-SN-83 1633; US-Patent-Class-41.6-228; of deflection data concurrently from all of the blade tips of an US-Patent-Class-41 6-238; US-Patent-Class-41 5-199) Avail: US operational engine rotor undergoing flutter or forced vibration. Patent and Trademark Office CSCL 01 C System measurements are made using optical transducers which Impulsive noise reduction is provided in a rotor blade by are fixed to the case. Measurements made in this way are the acoustically sweeping the chord line from root to tip so that equivalent of those obtained by placing three surface-normal the acoustic radiation resulting from the summation of potential displacement transducers at three positions on each blade of an singularities used to model the flow about the blade tend to operational rotor. M.M.M. cancel for all times at an observation point in the acoustic far field. Official Gazette of the U.S. Patent and Trademark Office N80- 141 14* # National Aeronautics and Space Administration. N8O141O8* National Aeronautics and Space Administration. Langley Research Center. Hampton, Va. Ames Research Center, Moffett Field. Calif. PRELIMINARY TEST RESULTS OF A FLIGHT. MANAGE- QUIET SHORT-HAUL RESEARCH AIRCRAFT FAMILIARIZA- MENT ALGORITHM FOR FUEL CONSERVATIVE DESCENTS TION DOCUMENT IN A TIME BASED METERED TRAFFIC ENVIRONMENT Robert C. McCracken Nov. 1979 96 p Charles E. Knox and Dennis G. Cannon (Boeing Commercial (NASA-TM-81149; A-7975) Avail: NASA. Ames Res. Center. Airplane Co., Seattle. Wash.) Nov. 1979 34 p refs Moffett Field, Calif. 94035 CSCL O1C (NASA-TM-8O194( Avail: NTIS HC A03/MF AOl CSCL The design features and general characteristics of the NASA 010 Quiet Short-Haul Research Aircraft are described. Aerodynamic A flight management algorithm designed to improve the characteristics and performance are discussed based on predictions accuracy of delivering the airplane fuel efficiently to a metering and early flight-test data. Principle airplane systems, including fix at a time designated by air traffic control is discussed. The the airborne data-acquisition system, are also described. The algorithm provides a 3 . D path with time control (4 . 0) for a test aircraft was designed and built to fulfill the need for a national B 737 airplane to make an idle thrust. clean configured descent research facility to explore the use of upper surface-blowing to arrive at the metering fix at a predetermined time, altitude, propulsive-lift technology in providing short takeoff and landing and airspeed. The descent path is calculated for a constant capability, and perform advanced experiments in various technical Mach/airspeed schedule from linear approximations of airplane disciplines such as aerodynamics, propulsion, stability and control. performance with considerations given for gross weight, wind. handling qualities, avionics and flight-control systems, trailing. and nonstandard pressure and temperature effects. The flight vortex phenomena, acoustics, structure and loads, operating management descent algorithms and the results of the flight systems, human factors, and airworthiness/certification criteria. tests are discussed. AWN. An unusually austere approach using experimental shop practices resulted in a low cost and high research capability. Author

N80-14109# Aerospace Engineering Test Establishment. Cold Lake (Alberta). N8O14115*# General Electric Co.. Cincinnati. Ohio. Aircraft DETERMINATION OF THE REPEATABILITY OF PEC Engine Group. QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE R. D. Michas 23 Oct. 1979 37 p refs (AETE-PR-79/36; CF-5) Avail: NTIS HC AO3/MF AOl (QCSEE) ACOUSTIC AND AERODYNAMIC TESTS ON A Position error calibrations conducted on four CF-5A, six SCALE MODEL OVER-THE-WING THRUST REVERSER AND CF-S AIR, and five CF . 5D aircraft using the standard tower fly FORWARD THRUST NOZZLE by and pacing methods are discussed. The variation in position 0. L. Stimpert 18 Jan. 1978 85 p refs error, between individual aircraft of each type is examined. (Contract NAS3-18021) Ammendments to the position error correction charts for the (NASA-CR- 135254; R75AEGSO4( Avail: NTIS CF-SA and CF-5D Aircraft Operation Instruction and redesign of NC A05/MF AOl CSCL 21E the correction cam are discussed. A.W.H. An acoustic and aerodynamic test program was conducted on a 1/6.25 scale model of the Quiet, Clean. Short-Haul Experimental Engine (QCSEE( forward thrust over-the-wing (O'PN( nozzle and 01W thrust reverser. In reverse thrust, the effect of N80- 14111 # Dreyfuss-Pellman Corp.. Stamford. Conn. reverser geometry was studied by parametric variations in blocker NON-CONTACTING ELECTRO-OPTICAL CONTOURING OF spacing, blocker height, lip angle, and lip length. Forward thrust HELICOPTER ROTOR BLADES Final Report. Oct. 1977 nozzle tests determined the jet noise levels of the cruise and Oct. 1978 takeoff nozzles, the effect of opening side doors to achieve takeoff Marc G. Dreyfus and Arnold Pellman 11 Dec. 1978 80 p thrust, and scrubbing noise of the cruise and takeoff jet on a

118 N80- 141 22

simulated wing surface. Velocity profiles are presented for both N80.14120*// General Electric Co.. Cincinnati, Ohio. Advanced forward and reverse thrust nozzles. An estimate of the reverse Engineering and Technology Programs Dept. thrust was made utilizing the measured centerline turning angle. QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE Author (QCSEE) OVER-THE .WING (01W) PROPULSION SYSTEM TEST REPORT. VOLUME 2: AERODYNAMICS AND N80_14116*# General Electric Co., Cincinnati. Ohio. Advanced PERFORMANCE Engineering and Technology Programs Dept. Jul. 1978 49 p refs QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE (Contract NAS3-18O21( (OCSEE). UNDER-THE-WING (UTW) ENGINE BOILERPLATE (NASA-CR- 135324; R77AEG474-Vol-2( Avail: NTIS NACELLE TEST REPORT. VOLUME 2: AERODYNAMICS HC AO3/MF AOl CSCL 21E AND PERFORMANCE The design and testing of the over the wing engine, a high 31 Dec. 1977 61 p refs bypass. geared turbofan engine, are discussed. The propulsion (Contract NAS3-18021) system performance is examined for uninstalled performance and (NASA-CR-i 35250; R77AEG2 1 22-Vol-2) Avail: NTIS installed performance. The-fan aerodynamic performance and the HC A04/MF AOl CSCL 21E D nozzle and reverser thrust performance are evaluated. A.W.H. The initial phase of testing of the under the wing engine and boilerplate nacelle components is discussed. The aerodynamics N80.14121*# National Aeronautics and Space Administration. and performance are outlined. M.M.M. Lewis Research Center, Cleveland, Ohio. STATIC TEST-STAND PERFORMANCE OF THE YF-102 N8O14117*# General Electric Co.. Cincinnati. Ohio. Aircraft TURBOFAN ENGINE WITH SEVERAL EXHAUST CONFIG- Engine Group. URATIONS FOR THE QUIET SHORT-HAUL RESEARCH QUIET. CLEAN. SHORT-HAUL EXPERIMENTAL ENGINE AIRCRAFT (QSRA) (QCSEE) UNDER-THE-WING (UTW) ENGINE ACOUSTIC Jack G. McArdle, Leonard Homyak. and Allan S. Moore Nov. DESIGN 1979 62 p H. D. Sowers and W. E. Coward Jan. 1978 62 refs p INASA-TP-1556; E-0191 Avail: NTIS HC A04/MF AOl CSCL (Contract NAS3-18O21( 21E (NASA-CR-i 35267; R76AEG 195) Avail: NTIS The performance of a YF-102 turbofan engine was measured HC A04/MF AOl CSCL 21E in an outdoor test stand with a bellmouth inlet and seven The acoustic considerations involved in the ow source noise exhaust-system configurations. The configurations consisted of basic engine design and the design procedures followed in the three separate-flow systems of various fan and core nozzle sizes development of the under-the-wing IUTW) engine boilerplate and and four confluent-flow systems of various nozzle sizes and shapes. composite nacelle acoustic treatment designs are presented. A computer program provided good estimates of the engine Laboratory experiments, component tests, and scale model and performance and of thrust at maximum rating for each exhaust engine tests supporting the UTW engine acoustic design are configuration. The internal performance of two different-shaped referenced. Acoustic design features include a near-sonic inlet, core nozzles for confluent-flow configurations was determined low fan and core pressure ratios, low fan tip speed, high and to be satisfactory. Pressure and temperature surveys were made low frequency stacked core treatment, multiple thickness with a traversing probe in the exhaust-nozzle flow for some treatment, and fan frame and stator vane treatment. R.E.S. confluent-flow configurations. The survey data at the mixing plane. plus the measured flow rates, were used to calculate the N8O14118* # General Electric Co.. Cincinnati. Ohio. Aircraft static-pressure variation along the exhaust nozzle length. The Engine Group. computed pressures compared well with experimental wall QUIET. CLEAN. SHORT-HAUL EXPERIMENTAL EN G I NE static-pressure data. External-flow surveys were made. for some (QCSEE) OVER-THE-WING (01W) ENGINE ACOUSTIC confluent-flow configurations. with a large Tixed rake at various DESIGN locations in the exhaust plume. A.R.H. H. D. Sowers and W. E. Coward Jun. 1978 58 p refs (Contract NAS3-18O21( (NASA-CR- 135268; R76AEG228) Avail: NTIS HC AO4/MF AOl CSCL 21E The acoustic considerations involved in the low source noise basic engine design and the design procedures followed in the development of the over-the-wing (OTW( nacelle acoustic N8014122*# General Electric Co.. Cincinnati, Ohio. Aircraft treatment design are presented. Laboratory experiments. Engine Group. component tests, and scale model and engine tests supporting FEASIBILITY OF SiC COMPOSITE STRUCTURES FOR the O'flN engine acoustic design are referenced. Acoustic design 1644 K (2500 F)GAS TURBINE SEAL APPUCATION Final features include a near-sonic inlet., low fan and core pressure Report. 28 Apr. - 30 May 1979 ratios. low fan tip speed. high and low frequency stacked core A. Darolia Nov. 1979 120 p ref treatment, multiple thickness treatment, and fan frame and stator (Contract NAS3-20082) vane treatment. R.E.S. (NASA-CR-i 59597; R79AEG6251 Avail: NTIS HC AO6/MF AOl CSCL 21E The silicon carbide composites evaluated consisted of Si/SiC and sintered silicon carbide as substrates, both with attached surface layers containing BN as an additive. A total of twenty-eight N8014119*# General Electric Co., Cincinnati. Ohio. Advanced candidates with variations in substrate type and density, and Engineering and Technology Programs Dept. layer chemistry, density, microstructure, and thickness were QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE evaluated for abradability. cold particle erosion resistanáe, static (QCSEE) UNDER-THE-WING (UTW) GRAPHITE/PMR COWL oxidation resistance, ballistic impact resistance, and fabricability. DEVELOPMENT BN-free layers with variations in density and pore size were C. L. Ruggles Jul. 1978 75 p refs later added for evaluation. The most promising candidates were (Contract NAS3-18O21( evaluated for Mach 1.0 gas oxidation/erosion resistance from (NASA-CR- 135279; R78AEG206( Avail: NTIS 1477 K (2200 F( to 1644 K (2500 Fl. The as-fabricated rub HC AO4/MF AOl CSCL 21E layers did not perform satisfactorily in the gas oxidation/erosion The PMR process development, tooling concepts, testing tests. However. preoxidation was found to be beneficial in conducted to generate materials properties data. and the improving the hot gas erosion resiStance. Overall. the laboratory fabrication of a subscale model of the inner cowl are presented. and rig test evaluations show that material properties are suitable It was concluded that the materials. processes. and tooling for 1477 K 12200 F) gas turbine seal applications. Further concepts were satisfactory for making an inner cowl with adequate improvements are needed in hot gas erosion resistance and structural integrity. M.M.M. abradability to demonstrate feasibility to 1644 K (250 F).A.R.H.

119 N80-1 4123

N8O14123 * # National Aeronautics and Space Administration. The program presented is a contracted effort to evolve and Lewis Research Center, Cleveland, Ohio. demonstrate the technology required to utilize broad-specification DYNAMIC RESPONSE OF A MACH 2.5 AXISYMMETRIC fuels in current and next generation commercial Conventional INLET AND TURBOJET ENGINE WITH A POPPET-VALUE Takeoff and Landing aircraft engines. and to verify this technology CONTROLLED INLET STABIUTY BYPASS SYSTEM WHEN in full-scale engine tests in 1983. The program consists of three SUBJECTED TO INTERNAL AND EXTERNAL AIRFLOW phases: Combustor Concept Screening, Combustor Optimization TRANSIENTS Testing. and Engine Verification Testing. The development and Bobby W. Sanders Washington Jan. 1980 102 p refs screening of the combustion system designs for the CF6- (NASA-TP-1531; E-9467) Avail: NTIS HC AO6/MF AOl CSCL 80 engine and the JT9D-7 engine, respectively, in high-pressure 21E sector test rigs are reported. M.M.M. The throat of a Mach 2.5 inlet that was attached to a turbojet engine was fitted with a poppet-valve-controlled stability N8O14127*// General Electric Co.. Cincinnati. Ohio. Aircraft bypass system that was designed to provide a large, stable airflow Engine Group. range. Propulsion system response and stability bypass perfor- THE CF6 JET ENGINE PERFORMANCE IMPROVEMENT: mance were determined for several transient airflow disturbances. NEW FRONT MOUNT both internal and external. Internal airflow disturbances included W. A. Fasching Dec. 1979 139 p refs reductions in overboard bypass airflow, power lever angle, and (Contract NAS3-20629( primary-nozzle area as well as compressor stall. For reference. (NASA-CR- 159639; R79AEG366( Avail: NTIS data are also included for a conventional, fixed-exit bleed system. HC A07/MF AOl CSCL 21E The poppet valves greatly increased inlet stability and had no The New Front Mount was evaluated ii. r y'mponent tests adverse effects on propulsion system performance. Limited including stress, deflection/distortion and fatigue tests. The test unstarted-inlet bleed performance data are presented. Author results demonstrated a performance improvement of 0.1% in cruise sfc, 16% in compressor saIl margin and 10% in compressor N8O14124*# National Aeronautics and Space Administration. stator angle margin. The New Front Mount hardware successfully Lewis Research Center. Cleveland. Ohio. completed 35.000 simulated flight cycles endurance testing. TURBOJET-EXHAUST-NOZZLE SECONDARY-AIRFLOW Author PUMPING AS AN EXIT CONTROL OF AN INLET-STABILITY BYPASS SYSTEM FOR A MACH 2.5 AXISYMMETRIC N80- 141 28# National Aeronautics and Space Administration. MIXED-COMPRESSION INLET Lewis Research Center, Cleveland, Ohio. Bobby W. Sanders Jan. 1980 82 p refs LASER-OPTICAL BLADE TIP CLEARANCE MEASUREMENT (NASA-TP-1532: E-9468( Avail: NTIS HC A05/MF AOl CSCL SYSTEM 21E John P. Barranger and M. John Ford (Pratt and Whitney Aircraft The throat of a Mach 2.5 inlet that was attached to a Group, West Palm Beach, Fla.( 13 Mar. 1979 10 p refs turbojet engine was fitted with large, porous bleed areas to Proposed for presentation at 25th Ann. Intern. Gas Turbine Conf. provide a stability bypass system that would allow a large, stable and the 22d Ann. Fluids Engr. Conf., New . Orleans. 9-13 Mar. airflow range. Exhaust-nozzle, secondary-airflow pumping ias 1980; sponsored by Am. Soc. of Mech. Engr. used as the exit control for the stability bypass airflow. Propulsion (NASA-TM-81376( Avail: NTIS HC A02/MF AOl CSCL system response and stability bypass performance were obtained 21E for several transient airflow disturbances, both internal and A laser-optical measurement system was developed to external. Internal airflow disturbances included redactions in measure single blade tip clearances and average blade tip overboard bypass airflow, power lever angle, and primary-nozzle clearances between a rotor and its gas path seal in rotating area, as well as compressor stall. Nozzle secondary pumping as component rigs and complete engines. The system is applicable a stability bypass exit control can provide the inlet with a large to fan. compressor and turbine blade tip clearance measurements. stability margin with no adverse effects on propulsion system The engine mounted probe is particularly suitable for operation performance. Author in the extreme turbine environment. The measurement system Consists of an optical subsystem. an electronic subsystem and a N8O14125*# National Aeronautics and Space Administration. computing and graphic terminal. Bench tests and environmental Lewis Research Center, Cleveland, Ohio. tests were conducted to confirm operation at temperatures, EFFECT OF DEGREE OF FUEL VAPORIZATION UPON pressures. and vibration levels typically encountered in an operating EMISSIONS FOR A PREMIXED PARTIALLY VAPORIZED gas turbine engine. DOE COMBUSTION SYSTEM Larry P. Cooper Jan. 1980 25 p refs N8O14129*# Detroit Diesel Allison, Indianapolis, nd. - (NASA-TP-1582: E-010( Avail: NTIS HC A02/MF AOl CSCL STUDY OF TURBOPROP SYSTEMS RELIABILITY AND 21E MAINTENANCE COSTS Final Report An experimental and analytical study of the combustion of Jun. 1978 304 p refs partially vaporized fuel-air mixtures was performed to assess the (Contract NAS3-20057( impact of the degree of fuel vaporization upon emissions for a (NASA-CR- 135192; EDR-91 32( Avail: NTIS premixing-prevaporizing flametube combustor. Data collected in HC A14/MF AOl CSCL 21E this study showed near linear increases in nitric oxide emissions The overall reliability and maintenance costs (R&MC's( of with decreasing vaporization at equivalence ratios of 0.6. For past and current turboprop systems were examined. Maintenance equivalence ratios of 0.72, the degree of vaporization had very Cost drivers were found to be scheduled overhaul (40%(. lack of little impact on nitric oxide emissions. A simple mechanism which modularity particularly in the propeller and reduction gearbox. accounts for the combustion of liquid droplets in partially vaporized and lack of inherent durability (reliability( of some parts. mixtures was found to agree with the measured results with Comparisons were made between the 5O1 . D13/54H6O turboprop fair accuracy with respect to both trends and magnitudes. system and the widely used JT8D turbofan. It was found that Author the total maintenance cost per flight hour of the turboprop was 75% higher than that of the JT8D turbofan. Part of this difference N8O14126* # National Aeronautics and Space Administration. was due to propeller and gearbox costs being higher than those Lewis Research Center, Cleveland, Ohio. of the fan and reverser. but most of the difference was in the NASA BROAD-SPECIFICATION FUELS COMBUSTION engine core where the older technology turboprop core mainte- TECHNOLOGY PROGRAM: STATUS AND DESCRIPTION nance costs were nearly 70 percent higher than for the turbofan. The estimated maintenance cost of both the advanced turbop'op James S. Fear 1979 14 p refs Presented at 25th Ann. Intern. Gas Turbine Conf.. New Orleans. 9-13 Mar. 1980: and advanced turbofan were less than the JT8D. The conclusion sponsored by Am. Soc. of Mech. Engr. was that an advanced turboprop and an advanced turbofan. using (NASA-TM-79315: E-272) Avail: NTIS HC A02/MF AOl CSCL similar cores. will have very competitive maintenance costs per 21E flight hour. J.M.S.

120 N80- 14136

N80-14130# Avco Lycoming Div., Williamsport. Pa. C. E. Chamblee AEDC Sep. 1979 99 p refs EXHAUST EMISSION REDUCTION FOR INTERMITTENT (AD-A074478: AEDC-TR-79-39( Avail: NTIS COMBUSTION AIRCRAFT ENGINES HG A05/MF AOl CSCL 21/5 R. N. Moffett Oct. 1979 114 p A one-dimensional, steady-state TF41 -A-i compressor (Contract NAS3-19754( mathematical model for stability assessment with undisturbed (NASA-CR-159757) Avail: NTIS HG A06/MF AOl CSCL flow, and a three-dimensional time-dependent TF41-A-1 21E compressor mathematical model for analysis of distorted inflows Three concepts for optimizing the performance, increasing and transient and dynamic disturbances were developed. the fuel economy, and reducing exhaust emission of the piston Example problems and comparisons to experimental results are aircraft engine were investigated. High energy-multiple spark presented for both models. The problems using the one- discharge and spark plug tip penetration, ultrasonic fuel vaporiza- dimensional. steady-state model consisted of determination of tion, and variable valve timing were evaluated individually. the steady-state stability limits (surge lines( with undisturbed Ultrasonic fuel vaporization did not demonstrate sufficient flow for three distinct inlet guide vane schedules. Those problems improvement in distribution to offset the performance loss caused using the three-dimensional, time-dependent model included by the additional manifold restriction. High energy ignition and determination of the stability limit (surge line( reduction caused revised spark plug tip location provided no change in performance by pure radial pressure inlet distortion, pure circumferential or emissions. Variable valve timing provided some performance pressure, and pure circumferential temperature inlet distortion. benefit; however, even greater performance improvement was The effects of rapid upward ramps of inlet temperature on obtained through induction system tuning which could be compressor stability were also investigated. The TF41-A-1 accomplished with far less complexity. A.R.H. compressor models computed the compressor stability limits with reasonable accuracy. GRA N8O14131*# Universal Systems. Inc.. Arlington. Va. OBLIQUE DETONATION WAVE RAMJET Richard B. Morrison Jan. 1980 87 p refs (Contract NAS1-15344( N80-14135# Institut National des Sciences Appliquees, Lyon (NASA-CR-159192) Avail: NTIS HG A05/MF AOl CSCL (France(. Lab. de Mecanique de Structures. 21E ON THE USE OF VIBRATION SELF-DAMPING MATERIALS Two conceptual designs of the oblique detonation wave ram(et IN THE MANUFACTURE OF PARTS FOR ROTATING are presented. The performance is evaluated for stoichiometric MACHINERY Final Report EUTILISATION DES MATERIAUX hydrogen-air equivalence ratios of phi = 1/3, 2/3 and 1 for a AMORTISSANTS POUR LA REALISATION DELEMENTS DE range of flight Mach numbers from 6 to 10. A.R.H. MACHINE TOURNANTE] Michel Lalanne, Phillippe Trompette. David Jones, Johan N80-14132# Martin Marietta Aerospace. Denver. Cob. DerHagopian, and Abdul Hommeida Oct. 1977 124 p refs PROPULSION OPTIONS FOR THE HI SPOT LONG ENDUR- In FRENCH ANCE DRONE AIRSHIP Final Report. Nov. 1978 - Aug. (Contract DGRST-75-7-0968( 1979 Avail: NTIS HG A06/MF AOl William L. Marcy and Ralph 0. Hookway 15 Sep. 1979 55 p The control of structural vibration in rotating pieces in the refs 400C to 600C temperature range by the utilization of damping (Contract N62269-79-C-0204( materials was studied. The test facilities and measuring systems (AD-AO74595: MCR-79-632: NADC-78 1 93-60( Avail: NTIS developed for this study are described, including the high HG AO4/MF AOl CSCL 21/5 temperature measurement of complex modes and frequencies. Airbreathing, monofueled, stored-energy, and solar- A computing method for rotating structures with structural rechargeable propulsion systems have been studied for the HI damping which was developed in this study is presented, and SPOT Long Endurance Drone Airship, providing constant-level applied to real cases, such as a stator vane (three dimensional electrical power as well as variable aerodwiamic thrust to maintain behavior( and a motor element (axisymmetrical structure(. position in winds varying from 15 to 100 knots at high altitude. Author (ESA) A hydrogen fueled airbreathing engine is optimum for mission lengths up to 30 days or more. GRA

N80-14133# Naval Postgraduate School, Monterey. Calif. AN ADAPTATION AND VALIDATION OF A PRIMITIVE N80- 141 36# National Aeronautics and Space Administration. VARIABLE MATHEMATICAL MODEL FOR PREDICTING Langley Research Center, Hampton. Va. THE FLOWS IN TURBOJET TEST CELLS AND SOLID FUEL SIMULATOR STUDY OF STALL/POST-STALL CHARACTER- RAMJETS MS. Thesis ISTICS OF A FIGHTER AIRPLANE WITH RELAXED Charles Albert Stevenson Jun. 1979 75 refs p LONGITUDINAL STATIC STABILITY (AD-A074187( Avail: NTIS HG AO4/MF AOl CSCL 21/5 Luat T. Nguyen. Marilyn E. Ogburn, William P. Gilbert, Kemper An adaptation of a primitive variable, finite-difference S. Kibler, Phillip W. Brown. and Perry L. Deal Washington computer program was accomplished in order to predict the Dec. 1979 226 p non-reacting flow fields in turbojet test cells and the reacting (NASA-TP-1538: L-12854( Avail: NTIS HC Al l/MF AOl flow fields in solid fuel ramjets. The study compares the CSCL DiG predictions of the primitive variable computer model with an A real-time simulation piloted was conducted to evaluate the earlier computer model and empirical data. It was found that high-angle-of-attack characteristics of a fighter configuration based the new model reasonably predicted the flow fields in both on wind-tunnel testing of the F-16. with particular emphasis on geometries. In addition, the primitive variable model allowed the effects of various levels of relaxed longitudinal static stability. simulation of test cell flows up to full engine throttle conditions The aerodynamic data used in the simulation was conducted on and solid fuel ramjet flows which included an aft mixing the Langley differential maneuvering simulator, and the evalua- chamber. GRA tion involved representative low-speed combat maneuvering. Results of the investigation show that the airplane with the basic control system was resistant to the classical yaw departure: however, it was susceptible to pitch departures induced by inertia N80-14134# ARO, Inc., Arnold Air Force Station. Tenn. coupling during rapid, large-amplitude rolls at low airspeed. The APPLICATION OF THE MULTISTAGE AXIAL-FLOW airplane also exhibited a deep-stall trim which could be flown COMPRESSOR TIME . DEPENDENT MATHEMATICAL into and from which it was difficult to recover. Control-system MODELING TECHNIQUE TO THE TF41-A-1 MODIFIED modifications were developed which greatly decreased the airplane BLOCK 76 COMPRESSOR Final Report. Jan. 1978 - Mar, susceptibility to the inertia-coupling departure and which provided 1979 a reliable means for recovering from the deep stall. Author

121

N80- 14137

N8O14137*# Boeing Commercial Airplane Co.. Seattle. Wash. N80-14141# Messerschmitt-Boelkow-Blohm G.m.b.H., Otto- LINEAR SYSTEMS ANALYSIS PROGRAM. L224(QR). brunn (West Germany). Unternehmensbereich Flugzeuge. VOLUME 1: ENGINEERING AND USAGE Topical Report. STABILITY AND CONTROL ASPECTS OF THE CCV-F1O4G Apr. 1978 - Oct. 1979 H. Beh, U. Korte. and G. Loebert Sep. 1978 33 p refs P. C. Shah and K. W. Heidergott Dec. 1979 180 p refs Presented at AGARD Flight Mech. Panel Meeting on Stability (Contract NAS1-15346; BCS-G0061) and Control. Ottawa, 25-28 Sept. 1978 (NASA-CR-2861) Avail: NTIS HC A09/MF AOl CSCL 09B (MBB-UFE-1447(0)) Avail: NTIS HC A03/MF AOl The QR computer program is described as well as its use The CCV command system, its implementation. and the design in classical control systems analysis and synthesis (root locus. of the control laws are described. The superior flight-mechanical time response, and frequency response). A.R.H. performance of the CCV flight control system is compared with that of the basic F 104G on the basis of simulator results. The N8O14138*# National Aeronautics and Space Administration. validity of these results is demonstrated by comparing the principal Ames Research Center. Moffett Field. Calif. characteristics of longitudinal and lateral motion measured in PILOT CONTROL THROUGH THE TAFCOS AUTOMATIC flight with the corresponding predicted values. Author (ESA) FLIGHT CONTROL SYSTEM William R. Wehrend. Jr. Dec. 1979 42 p refs N80-14142# Messerschmitt-Boelkow-Blohm G.m.b.H.. Munich (NASA-TM-81 152; A-79961 Avail: NTIS HC A03/MF AOl (West Germany). CSCL O1C INVESTIGATION OF THE OSCILLATORY AND FLIGHT The set of flight control logic used in a recently Completed BEHAVIOR OF ROTOR SYSTEMS IN RELATION WITH flight test program to evaluate the total automatic flight control ATMOSPHERIC TURBULENCE EUNTERSUCHUNGEN ZUM system (TAFCOS) with the controller operating in a fully automatic SCHWINGUNGS- UND FLUGVERHALTEN VON HUBS- mode, was used to perform an unmanned simulation on an CHRAUBERN UNTER ATMOSPHAERISCHER TURBUL- IBM 360 Computer in which the TAFCOS concept was extended E NZ] to provide a multilevel pilot interface. A pilot TAFCOS interface H. DahI and 0. Weger 1979 72 p refs In GERMAN; ENGLISH for direct pilot control by use of a velocity-control-wheel-steering summary Sponsored by Bundesmin. der Verteidigung mode was defined as well as a means for calling up conventional IBMVG-FBWT-79-5) Avail: NTIS NC A04/MF AOl; autopilot modes. It is concluded that the TAFCOS structure is DOKZENTBw, Bonn DM 30 easily adaptable to the addition of a pilot control through a The effects of stochastic atmospheric disturbances on the stick-wheel-throttle control similar to conventional airplane performance of various helicopter rotor systems was investigated controls. Conventional autopilot modes, such as airspeed-hold. in order to determine their gust sensitivity. A statistical description altitude-hold, heading-hold, and flight path angle-hold, can also of turbulent excitations which permits sufficiently accurate be included. A.R.H. simulation of helicopter oscillatory behavior resulting from gust disturbances was developed. Results show that during low altitude N8O14139*# National Aeronautics and Space Administration. flight and slow speed flight the gust vector distribution over the Langley Research Center. Hampton. Va. helicopter is very nonuniform. At any instant therefore, the ALTITUDE RESPONSE OF SEVERAL AIRPLANES DURING individual rotor blades are affected by very different gust velocities LANDING APPROACH which leads to different responses of the blades. In conclusion. William H. Phillips Nov. 1979 39 p refs the Investigations pursue the important objective of elaborating (NA5A-TM-80186( Avail: NTIS HC A03/MF AOl CSCL and clarifying possibilities for improvement of the flight characteris- O1C tics of the investigated rotor systems, in so far as the inclusion The response in altitude and pitching velocity of the shuttle of special gust reduction systems on helicopters is possible and and of four other airplanes during the landing approach is profitable. Author (ESA) compared. The effects of airplane type, pitch damping, center-of- gravity location, lift coefficient, and cockpit position are presented. N80-14143# European Space Agency. Paris (France). The reasons for the differences observed and the effects of these FLIGHT TESTING OF THE BUFFETING BEHAVIOR OF differences on control characteristics are discussed. A.R.H. COMBAT AIRCRAFT G. Redeker Feb. 1979 44 p refs Transl. into ENGLISH of "Flugversuche sum Buffeting-Verhalten von Kampfflugzeugen". Rep. DFVLR-FB-IB-151-78/6 DFVLR. Brunswick. 18 Dec. 1979 N80-14140# Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto- (ESA-T'T-523: DFVLR-FB-IB- 151-78/6) brunn (West Germany). Unternehmensbereich Flugzeuge. Avail: NTIS HC A03/MF AOl EXCITATION AND ANALYSIS TECHNIQUE FOR FLIGHT The flight testing of buffeting behavior in combat aircraft is FLUtTER TESTS reviewed. After a description of the buffeting phenomenon and G. Haidl and M. Steininger 8 Sep. 1978 27 p refs Presented at 47th SMP/AGARD Meeting. Florence.. 24-29 Sep. 1978 its effects on the pilot and the performance of a combat aircraft. flight testing techniques from several American reports are )MBB-UF-14461011 Avail: NTIS NC A03/MF AOl discussed. Excitation methods applied recently for flight flutter testing Author (ESA) are surveyed. Examples of excitation by frequency sweep. pseudo-random, harmonic oscillation, and control loop are given and their effectiveness and adaptation to digital processing is discussed. Experience gained in generating aerodynamic forces by control surfaces or additional vanes is reported. The digital .4# analysis of flight flutter test data is then considered. Recommenda- N80-1414 Federal Aviation Administration, Washington, 0 C. tions for selection of analysis parameters and how to avoid errors REFLECTION CRACKING OF BITUMINOUS OVERLAYS FOR due to digital processing are given. For data evaluation in flight AIRPORT PAVEMENTS: A STATE OF THE ART Final flutter tests the autopower spectrum as well as transfer and Report coherence functions are used. Errors and effects of digital Aston L. McLaughlin May 1979 91 p refs blockwise Computation with analysis procedures like block (AD-A073484; FAA-RD-79-57; ARD-430( Avail: NTIS overlapping, windowing, averaging, or curve fitting are demon- HC A05/MF AOl CSCL 13/2 strated. The filter correlation and the modal analysis technique Methods and practices pursued by various pavement are applied for mode separation and damping evaluation based authorities in an effort to reduce the incidence of reflection cracking on the above mentioned functions. Practical experience and of bituminous overlays are discussed. The theoretical. analytical examples from wind tunnel. flight, and laboratory tests are and laboratory efforts in this connection are presented. The discussed. An online computer program is presented for realtime mechanics of reflection cracking and criteria for design of overlay calculation of resonance frequencies and damping factors. systems which are resistant to reflection cracking are examined. Author (ESA) A.W.H.

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N80-14147# Defence and Civil Inst. of Environmental Medicine. growth was generally equivalent to that in 100% petroleum JP-5. Downsview (Ontario). A search was made among samples of soil, creosoted wood INVESTIGATION OF NOISE HAZARDS IN THE ENGINE and tree resins for microorganisms that could thrive in the presence TEST CELL CFB BADEN-SOELLINGEN of synthetic fuels. This endeavor produced a strain of C. resinae S. E. Forshaw Jun. 1979 22 p refs that grew as well with oil shale JP-5 as with petroleum JP-5. (AD-A074391: DCIEM-TR-79-X23) Avail: NTIS These exploratory experiments indicate that microorganisms HC A02/MF AOl CSCL 21/5 adapted to growth with conventional petroleum fuel tend to be Although the sound pressure levels occuring in the engine inhibited by synthetic fuels, but that organisms probably exist in test cell. CFB Baderi-Soellingeri, are extremely intense (137 dBA) nature which can readily adapt to and grow in the presence of with a J79 engine running at military power, the attenuation synthetic fuels. GRA provided by Canadian Forces standard-issue earmuffs is sufficient to reduce the noise at operators' ears to more tolerable levelc (108 dBA(. Moreover, the noise doses sustained during engine N80-14303# Logicon, Inc.. San Diego. Calif. Tactical and check-outs permit average work periods of up to 49 minuter Training Systems Div. per day in the test cell with engines running. GRA VOCABULARY SPECIFICATION FOR AUTOMATIC SPEECH RECOGNITION IN AIRCRAFT COCKPITS Final Report. Sep. 1978 - Jun. 1979 N80-14199# Avco Systems Div.. Wilmington. Mass. Rohn J. Petersen, Nancey Lee. Catherine Meyn. Elaine Regelson, PROTECTIVE COATINGS FOR AIRCRAFT COMPOSITES IN and William Satzer 31 Aug. 1979 92 p refs NUCLEAR ENVIRONMENTS Final Report. 1 Jan. - 30 Nov. (Contract N00014.78-C-0692( 1977 (AD-A073703( Avail: NTIS HC A05/MF AOl CSCL 17/2 J. G. Alexander and P. J. Grady 1 Apr. 1978 168 p refs The general focus of this research was to design a communica- (Contract DNAOO1-77-C-O098) tion media (a vocabulary) that is advantageous to both machine (AD-A074889; AD-E300594; AVSD-O082-78-RR; recognition and human production of speech events. The problem DNA-4735F) Avail: NTIS HC A08/MF AOl CSCL 11/3 was analyzed from a human factors perspective that centered This program selected and experimentally evaluated several upon the man-computer dialogue (interaction( required for cockpit classes of protective coatings for nuclear flash for application application of ASR. The results indicated that phrase familiarity on graphite epoxy and quartz polyimide composite aircraft skins. and stimulus familiarity had major impact on the learning and An analytical/experimental assessment was also performed to utilization of the phrases in the paired-associate task. Phrase demonstrate the increased tensile capability of the two composite length and meaningfulness did not appear to differentially affect materials with the application of selected coatings. GRA either the learning or utilization of the paired associate. In addition. pretraining of stimulus familiarity did not seem to result in improved performance. Acoustic lexical confusability also was discussed in general methodological terms. The results of the N8O-1 4256# Lockheed-Georgia Co.. Marietta. study were interpreted in terms of a contextualist viewpoint with AIRCRAFT FUEL SYSTEM SIMULATOR TESTS WITH the necessity of a broader contextual manipulation being pointed ANTIMISTING KEROSENE (JET A FUEL WITH Out 05 a requirement for further research. GRA FM-9 ADDITIVE) Final Report. Oct. 1978 - May 1979 R. E. Pardue May 1979 50 p (Contract DOT-FA78WAI-925( (AD-A073237; FAA-RD-79-52( Avail: NTIS N80-14325# Forschungsinstitut fuer Funk und Mathematik. HC A03/MF AOl CSCL 21/4 Werthoven (West Germany(. Tests were conducted on a full-scale C-141 aircraft fuel TARGET TRACKING USING DOPPLER-INFORMATION IN system simulator to evaluate system and component operation SENSOR ORIENTED COORDINATES WITH A THREE using antimisting kerosene fuels (Jet A fuel with FM-9 additive). DIMENSIONAL ARRAY RADAR A typical aircraft flight profile was simulated with the tank-to- G. vanKeuk Aug. 1978 33 refs In GERMAN: ENGLISH engine fuel feed system operating. Tests were also conducted p summary to evaluate the tank quantity gaging system accuracy, tank refuel (Rept-270( Avail: NTIS HC A03/MF AOl valve operation and fuel transfer ejector operation. Fuels tested Measurement statistics, expressed in three dimensional included Jet A, .30% FM-9 AMK. .35% FM-9 AMK and .40% radar oriented coordinates. and the nonlinear equations of target FM-9 AMK. Flammability tests were conducted on selected fuel motion are presented. An extended Kalman filter was developed samples to evaluate degradation caused by the above tests. to solve the problem of automatic target tracking. It Consists of Author three decoupled filters, one of which prdcesses Doppler information directly. Depending on target speed, distance, and flight direction of the Object being tracked, the domain of applicability for the proposed method is derived. Doppler information is then used to improve the plot to track correla- Naval Research Lab.. Washington. D. C. N80-14259# tion. It is shown that this information is very sensitive for detecting MICROBIAL DETERIORATION OF HYDROCARBON FUELS target maneuvers in an adaptive tracing mechanism. FROM OIL SHALE. COAL AND PETROLEUM. 1: EXPLOR- Author (ESA) ATORY EXPERIMENTS Interim Report Marian E. May and Rex A. Neihof 20 Aug. 1979 28 p refs (ZF5757 1004) N8O14355*# Wisconsin Univ. - Milwaukee. (AD-A073761; AD-E000316; NRL-M R-4060( Avail: NTIS UNSTEADY FLOW AND DYNAMIC RESPONSE ANALYSES HC A03/MF AOl CSCL 21/4 FOR HELICOPTER ROTOR BLADES Final Progress Report. As part of the Navy's program on alternative sources of 2 Jan. 1971 - 30 Jun. 1979 hydrocarbon fuel, the susceptibility to microbial deterioration of Theodore Bratanow Nov. 1979 30 p refs JP-5 derived from oil shale and coal (referred to as synthetic (Grant NGR-5O-O07-O01) fuels( was investigated and compared with that of petroleum (NASA-CR-159190( Avail: NTIS HC AO3/MF AOl CSCL JP-5. Six fungi, including three strains of Cladosporium resinae, 02A a yeast (Candida) and a bacterium (Pseudomonas( which normally Research is presented on helicopter rotor blade vibration grow well in association with petroleum JP . 5 were used as test and on two and three dimensional analyses of unsteady organisms in two-phase systems containing fuel/aqueous media. incompressible viscous flow past oscillating helicopter rotor blades. Most of the test organisms were inhibited to various extents in A summary is presented of the two international research the presence of the synthetic fuels. An exception was a Fusarium collaborations which resulted from the NASA project: the species (fungus) which grew equally well under all three fuels. collaboration under the auspices of NATO between the University In mixtures of 75% petroleum and 25% synthetic fuels, microbial of Wisconsin-Milwaukee. University of Brussels, Belgium and the

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N8O14359*# Bionetics Corp.. Hampton. Va. obtain validation of these techniques and provide insight as to THE TRANSFER OF CARBON FIBERS THROUGH A possible modifications of stress simulation or fracture prediction COMMERCIAL AIRCRAFT WATER SEPARATOR AND AIR criteria. The objective was to develop a design methodology, CLEANER which will improve on current design methods, thus permitting the design of interface Configurations in which strengths more Jerome A. Meyers Nov. 1979 22 p refs (Contract NAS1-15238) indicative of the inherent strength of ceramic materials can be (NASA-CR-159183) Avail: NTIS HC A02/MF AOl CSCL realized. GRA 20D The fraction of carbon fibers passing through a water separator and an air filter was determined in order to estimate NSO-14422# Laboratorium fuer Betriebsfestigkeit, Darmstadt the proportion of fibers outside a closed aircraft that are (West Germanyl. transmitted to the electronics through the air conditioning system. REVIEW OF INVESTIGATIONS INTO AERONAUTICS When both devices were used together and only fibers 3 mm RELATED FATIGUE FEDERAL REPUBLIC OF GERMANY or larger were considered, a transfer function of .001 was Status Report. May 1977 - Apr. 1979 obtained. K.L. D. Schutz and 0. Buxbaum 1979 166 p refs Presented at 16th Cent, of Intern. Comm. Aeron. Fatigue, Brussels, 1979 )LBF-S-l42; ICAF-CONF-1979l Avail: NTIS HC A08/MF AOl N80-14377# Army Test and Evaluation Command, Aberdeen Investigations into fatigue and fatigue related disciplines, as Proving Ground. Md. they regard aeronautics, are reviewed. Studies treated are limited US ARMY TEST AND EVALUATION COMMAND TEST to those Carried out in the Federal Republic of Germany. Subjects OPERATIONS PROCEDURES: PHOTOGRAPHIC AND include measurement and analysis of operational loads, fatigue VIDEO IMAGE SUPPORT AVIATION MATERIEL Final behavior of joints and notched specimens, fatigue life prediction, Report cyclic stress-strain behavior, and low cycle fatigue. Also considered 17 Aug. 1979 16 p refs are crack propagation, fracture mechanics, and residual Static (AD-A074883: TOP-7-3 . 519) Avail: NTIS HC A02/MF AOl strength. Fatigue of fiber reinforced plastics and hybrid structures CSCL 14/5 as well as some investigations of general interest with and without Photographic techniques can be utilized to obtain precise relation to aircraft are reported on. Finally. a bibliography of data in relation to time velocity, rates and characteristics of a fatigue related documents by German authors is given. developmental test event or simply to document a physical defect. Author )ESA) deficiency or shortcoming in a human factors evaluation. This document provides requirements, suggestions and techniques for N8O14634*# Saint Cloud State Coil., Minn. incorporating photographic coverage into the developmental test METEOROLOGICAL INPUT TO GENERAL AVIATION PILOT of aviation materiel. GRA TRAINING John R. Colomy In Tennessee Univ. Space Inst. Proc., 3d Ann. Workshop on Meteorological and Environ. Inputs to Aviation N80-144005 # National Aeronautics and Space Administration. Systems Apr. 1979 p 30-36 Lyndon B. Johnson Space Center. Houston, Tex. SURFACE CONFORMING THERMAL/PRESSURE SEAL Avail: NTIS HC A09/MF AOl CSCL 04B Patent Application The meteorological education of general aviation pilots is Martin L. Stevens. inventor Ito NASA) (Fairchild Republic Co.) discussed in terms of the definitions and concepts of learning Filed 12 Dec. 1979 21 p Sponsored by NASA and good educational procedures. The effectiveness of the INASA-Case-MSC- 18422-1: US-Patent-Appl-SN- 102593) Avail metoeorological program in the training of general aviations pilots NTIS HC A02/MF AOl CSCL hA is questioned. It is suggested that flight instructors provide real A sealing apparatus is described which serves both pressure experience during low ceilings and visibilities, and that every and thermal sealing functions between adjacent and relatively pilot receiving an instrument rating should experience real movable elements of relatively large surfaces. The sealing instrument flight. F.0.S. apparatus has the flexhility required for large movable surfaces. and can accommodate moderate variations in the gap between such surfaces which may be affected by thermal distortion. Sealing N80-146365 # National Transportation Safety Board, Washington. is accomplished with a nonabrasive, low frictional material. D. C. creating as little resistance as possible to movement of control ACCIDENT INVESTIGATION members and minimal wear and damage to surface coatings. Alan I. Brunstein In Tennessee Univ. Space Inst. Proc.. 3d NASA Ann. Workshop on Meteorological and Environ. Inputs to Aviation Systems Apr. 1979 p 46-57

Avail: NTIS HC A09/MF AOl CSCL 04B AiResearch Mfg. Co.. Phoenix, Ariz. N80-14417# Aircraft accident investigations are discussed with emphasis CONTACT STRESS ANALYSIS OF CERAMIC-TO-METAL on those accidents that involved weather as a contributing factor. INTERFACES Final Report The organization of the accident investigation board for air carrier David G. Finger 21 Sep. 1979 35 refs p accidents is described along with the hearings, and formal report IContract N0001 4-78-C-0547) preparation. Statistical summaries of the investigations of general (AD-A074491 AiResearch-2 1-32391 Avail: NTIS aviation accidents are provided. F.0.S. HC A03/MF AOl CSCL 14/2 The objective of this proposed 8-month program was to conduct analysis, specimen testing, and data correlation to provide an improved understanding of the local contact conditions that N8O14638*# Port Columbus International Airport. Ohio. prevail at an interface between ceramic and metal components EFFECT OF WEATHER CONDITIONS ON AIRPORT for gas turbine engines. The program was specifically directed OPERATIONS to study contact stresses at the interface between inserted ceramic Daniel F. Ginty In Tennessee Univ. Space Inst. Proc.. 3d Ann. turbine blades Ihot-pressed silicon nitride) and a metal rotor, Workshop on Meteorological and Environ. Inputs to Aviation but the method of analysis, results. and conclusions also provided Systems Apr. 1979 p 63-66 a better understanding of contact stresses at ceramic-to-metal and ceramic-to-ceramic interfaces for static components. A Avail: NTIS HC A09/MF AOl CSCL O4B finite-element Stress analysis procedure and structural evaluation The effect of adverse weather on airport operations are technique consistent with the statistical nature of ceramic discussed. The meteorological conditions discussed included rain materials was generated. Specimen testing was conducted to and hyoroplaning. snow and slush. and icing. F.O.S.

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N8O14639*# National Aeronautics and Space Administration. diffraction of a plane wave by a half-plane. Infinite series and Langley Research Center. Hampton. Va. geometric acoustic methods for Solving diffraction problems are EFFECT OF SPANWISE GUST VARIATIONS described. Four applications of diffraction theory are discussed: John C. Houbolt In Tennessee Univ. Space Inst. Proc.. 3d the selection of an appropriate shape for a microphone. the use Ann. Workshop on Meteorological and Environ. Inputs to Aviation of aircraft wings to shield the community from engine noise. Systems Apr. 1979 p 72-79 the reflection of engine noise from an aircraft fuselage, and the radiation of trailing edge noise. K.L. Avail: NTIS HC A09/MF AOl CSCL 04B The spanwise, vertical force, and rolling moment effects of random gusts encountered by aircraft are analyzed. Mathematical NBO14873 * # National Aeronautics and Space Administration. models are given for approximating atmospheric turbulence. Langley Research Center, Hampton, Va. Inst. for Computer F.O.S. Application in Science and Engineering. EXPERIMENTAL AND NUMERICAL RESULTS OF SOUND N8O1464,O*# South Dakota School of Mines and Technology. SCATTERING BY A BODY Rapid City. L. Maestrello and A. Bayliss In AGARD Special Course on THE T-28 THUNDER/HAILSTORM PENETRATION AIR- Acoustic Wave Propagation Aug. 1979 12 p refs CRAFT John Prodan In Tennessee Univ. Space Inst. Proc.. 3d Ann. Avail: NTIS HC A1O/MF Aol CSCL 20A - - Workshop on Meteorological and Environ. Inputs to Aviation The interaction of aerodynamic noise with a fuselage shaped Systems Apr. 1979 p 80-97 body is discussed. A numerical technique is presented which permits the computation of the scattering of an acoustic source Avail: NTIS HC A09/MF AOl . CSCL 04B by a body at rest for frequencies of aeroacoustic interest. A Modifications to the T-28 Aircraft to make it safe for parallel experiment is described which confirms the results of penetrating hailstorms to take scientific measurements are the computations. A numerical study of varying the geometry of described. F.O.S. the scattering is presented. In addition. the effect of forward motion on the mean velocity and static pressure profiles in the wake of such a body with a jet exiting from it is simulated. N8O14551 * # Tennessee Univ. Space Inst.. Tullahoma. Experimental results are presented and a similarity law is given. CURRENT RESEARCH ON AVIATION WEATHER (BIBLIOG- K. L. RAPHY). 1979 Barry S. Turkel and Walter Frost Jan. 1980 96 p refs IContract NAS8-32692I N80-14876# Deutsche Forschungs . und Versuchsanstalt fuer INASA-CR-3214I Avail: NTIS HC A05/MF AOl CSCL 04B Luft- und Raumfahrt, Berlin IWest Germanyl. Inst. fuer The titles, managers, supporting organizations. performing Experimentelle Stroemungsmechanik. organizations, investigators and objectives of 127 current research AEROACOUSTIC MEASURING TECHNIQUES IN OR projects in advanced meteorological instruments, forecasting, icing. OUTSIDE TURBULENT FLOWS lightning, visibility, low level wind shear, storm hazards/severe Helmut V. Fuchs In AGARD Special Course on Acoustic Wave storms, and turbulence are tabulated and cross-referenced. A Propagation Aug. 1979 27 p refs list of pertinent reference material produced through the above tabulated research activities is given. The acquired information Avail: NTIS HC A1O/MF AOl is assembled in bibliography form to provide a readily available The motion of aerodynamic or acoustic sources relative to source of information in the area of aviation meteorology. A.R.H. the fluid and/or the measuring instrument is discussed. Some practically important effects on the pressure and velocity fields in and outside the active source region are deduced from linearized N80-14.853# Air Force Flight Dynamics Lab.. Wright-Patterson wave equations with simple source functions. Limitations on AFB, Ohio. fluctuating aerodynamic and acoustic pressure measuring THE ANALYSIS OF SOUND PROPAGATION IN JET ENGINE techniques employing special microphone probes are discussed. DUCTS USING THE FINITE DIFFERENCE METHOD Interim Applications include: Ii) the pressure pulsations induced in the Report. Nov. 1975 - Nov. 1978 near fields of jet. wake, and duct flows. and (2) the effects of Dennis W. Quinn Jun. 1979 60 p refs source convection and forward speed on the far field radiation IAD-A074233; AFFDL-TR-79-3063I Avail: NTIS characteristics of jets or other aeroacoustic sources in motion. HC A04/MF AOl CSCL 20/1 K.L. In this report, the author derives the partial differential equations which describe sound propagation in jet engine ducts N80-15026# Department of Defence, Canberra (Australia). and then presents a finite difference approach for solving these AERONAUTICAL RESEARCH LABORATORIES Annual equations. Also included is a computer program listing, sample Report. 1977 - 1978 input and sample output. The program can handle uniform 1978 95 p refs rectangular and cylindrical ducts with or without uniform flow. 1RM78/3O1O7I Avail: NTIS HC A05/MF AOl In addition, if a mapping function which maps a nonuniform Research and development in the areas of aerodynamic duct to a uniform duct is specified. the program can determine configurations and aeronautical engineering for design purposes sound fields in nonuniform ducts in the absence of flow. GRA and/or operational aspects of aircrafts is presented. Wind tunnel tests, materials tests. engine tests. and aircraft structural analysis are discussed. A.W.H. N80.14.870*# National Aeronautics and Space Administration. Langley Research Center, Hampton. Va. Aeroacoustics Branch. APPLICATIONS OF DIFFRACTION THEORY TO AEROA- COUSTICS N8O15O28*# National Aeronautics and Space Administration. Donald L. Lansing. Chen-Huei Liu, and Thomas D. Norum In Hugh L Dryden Flight Research Center. Edwards, Calif. AGARD Special Course on Acoustic Wave Propagation Aug. LANDING APPROACH AIRFRAME NOISE MEASURE- 1979 12 p refs MENTS AND ANALYSIS Avail: NTIS HC A1O/MF AOl CSCL 2OA Paul L. Lasagna. Karen G. Mackall. Frank W. Burcham. Jr.. and The fundamentals of diffraction theory were reviewed and Terrill W, Putnam Jan. 1980 36 p refs applied to several problems of aircraft noise generation. propaga- (NASA-TP-1602) Avail: NTIS HC A03/MF AOl CSCL 2OA tion, and measurement. The general acoustic diffraction problem Flyover measurements of the airframe noise produced by is defined and the governing equations were set down. Diffraction the AeroCornmander. JetStar. CV-990. and 6-747 airplanes are phenomena are illustrated using the classical problem of the presented for various landing approach configurations. Empirical

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and semiempirical techniques are presented to correlate the A discussion of the principles of hydrodynamics of nonviscous measured airframe noise with airplane design and aerodynamic fluids in the case of motion of solid bodies in a fluid is presented. parameters. Airframe noise for the jet-powered airplanes in the Formulae are derived to demonstrate the transition from the clean configuration (flaps and gear retracted) was found to be fluid surface to a corresponding 'control surface'. The external adequately represented by a function of airplane weight and the forces are compounded of the fluid pressures on the control fifth power of airspeed. Results show the airframe noise for all surface and the forces which are exercised on the fluid by any four aircraft in the landing configuration (flaps extended and solid bodies which may be inside of the control surfaces. gear down) also varied with the fifth power of airspeed, but Illustrations of these formulae as applied to the acquisition of this noise level could not be represented by the addition of a transformations from a known simple flow to new types of flow constant to the equation for clean-configuration airframe noise. for other boundaries are given. Theoretical and experimental M.G. investigations of models of airship bodies are presented. M.M.M.

N80-15029# Boeing Aerospace Co.. Seattle. Wash. N80. 1 5036*# National Advisory Committee for Aeronautics. FLEET HARDNESS VARIATION Final Report. Jan. - Sep. Ames Aeronautical Lab., Moffett Field, Calif. 1978 PRESSURE DISTRIBUTION ON JOUKOW5KI WINGS E. N. York and S L. Strack 29 Sep. 1978 45 refs p Otto Blumenthal In NASA. Ames Res. Center Classical Aerodyn. (Contract DNAOO1-78-C-0138( Theory Dec. 1979 67 . 83 ref Transl. into ENGLISH from (AD-A074849: AD-E300588( Avail: NTIS HC A03/MF AOl p Z fuer Flugtech. und Motorluftschiffahrt (Germany), 31 May 1913 CSCL 01/3 16 p The variation of nuclear hardness in a fleet of aircraft is (NACA-TM-336( Avail: NTIS HC A14/MF AOl CSCL O1A considered and the potential hardness degradation mechanisms The hydrodynamics and mathematical models as applied to identified. These include cracks, corrosion, paint deterioration. the potential flow about a Joukowski wing are presented. and aging of equipment. Methods are developed whereby the variation in hardness in a fleet could be estimated for each of M.M.M. these degradation mechanisms. GRA

N80-15030fl Technology. Inc. Dayton. Ohio Instruments N8O-15038 t fl National Advisory Committee for Aeronautics. and Controls Div Ames Aeronautical Lab,, Moffett Field, Calif. APPLICATION OF THE SIRS CONCEPT TO NAVY HELICOP- THE MINIMUM INDUCED DRAG OF AEROFOILS TE R S Max M. Munk In NASA. Ames Res. Center Classical Aerodyn. 1 Oct. 1979 112 p refs Theory Dec. 1979 o 95-110 (Contract N00019-77-C-O318) )AD-A074801, TI-0798-05-02) Avail: NTIS (NACA-l21) Avail: NTIS HC A14/MF AOl CSCL O1A I-IC A06/MF AOl CSCL 01/3 Equations are derived to demonstrate which distribution of lifting elements result in a minimum amount of aerodynamic In an effort to determine the feasibility of applying the U.S. Army-developed SIRS recording system to U.S. Navy helicopters, drag. The lifting elements were arranged (1 (in one line, (2) parallel a study was conducted into the specific application of SIRS on lying in a transverse plane. and (3) in any direction in a transverse the RH-53D helicopter. A fatigue damage assessment model plane. It was shown that the distribution of lift which causes was formulated for nine fatigue-critical dynamic components of the least drag is reduced to the solution of the problem for the RH-53D helicopter, and two possible flight condition systems of airfoils which are situated in a plane perpendicular to the direction of flight. monitoring systems were synthesized. Both systems were found M M M to be technically acceptable, but only one was practical based on current recording technology. The resulting system was analyzed from a life-cycle cost viewpoint and found to be cost-effective. G RA N8O15O39*# National Advisory Committee for Aeronautics. Ames Aeronautical Lab., Moffett Field, Calif. N8O15O31*# National Aeronautics and Space Administration. THE AERODYNAMIC FORCES ON AIRSHIP HULLS Langley Research Center, Hampton, Va. Max M. Munk In NASA. Ames Res. Center Classical Aerodyn. COMPUTER PROGRAM TO PREPARE AIRFOIL CHARAC- Theory Dec. 1979 p 111-126 refs TERISTIC DATA FOR USE IN HELICOPTER PERFORMANCE CALCULATIONS )NACA-184) Avail: NTIS HC A14/MF AOl CSCLO1A Henry E. Jones Dec 1977 57 p The new method for making computations in connection (DA Proj. 1 L1-61 1O2-AH.45( with the study of rigid airships, which was used in the investigation (NASA-TM-78627; L-1 1608) Avail, NTIS HC A04/MF AOl of Navy's ZR-i by the special subcommittee of the National CSCL O1A Advisory Committee for Aeronautics appointed for this purpose A computer program developed to prepare wind tunnel is presented. The general theory of the air forces on airship generated airfoil data for input into helicopter performance hulls of the type mentioned is described and an attempt was prediction programs is described The program provides for made to develop the results from the very fundamentals of numerically cross plotting the data. plotting the data, and mechanics. M M.M. tabulating and punching the tabulated result into computer cards for use in the rotorcraft flight simulation model A W.H

N80-15040t # National Advisory Committee for Aeronautics, N80-15034t # National Advisory Committee for Aeronautics Ames Aeronautical Lab., Moffett Field. Calif. Ames Aeronautical Lab., Moffett Field. Calif. ELEMENTS OF THE WING SECTION THEORY AND OF THE APPLICATIONS OF MODERN HYDRODYNAMICS TO WING THEORY AERONAUTICS. PART 1: FUNDAMENTAL CONCEPTS Max M. Munk In NASA, Ames Res Center Classical Aerodyn AND THE MOST IMPORTANT THEOREMS. PART 2: Theory Dec. 1979 p 127-149 refs APPLICATIONS L. Prandtl In NASA. Ames Res. Center Classical Aerodyn. )NACA-191( Avail: NTIS HC A14/MF AOl CSCLO1A Theory Dec. 1979 p 1-56 refs Transi. into ENGLISH of Results are presented of the theory of wings and of wing unidentified German document sections which are of immediate practical value They are proven and demonstrated by the use of the simple conceptions of kinetic (NACA . 116( Avail: NTIS HC A14/MF AOl C5CL CiA energy and momentum only. - M.M.M

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N80-15046t # National Advisory Committee for Aeronautics. Three advanced analyses for predicting aircraft propeller Langley Aeronautical Lab.. Langley Field. Va, performance at high subsonic speeds are described. Two of these GENERAL POTENTIAL THEORY OF ARBITRARY WING analyses use a lifting line representation for the propeller blades SECTIONS and vortex filaments for the blade wakes but differ in the details Theodore Theodorsen and I, E. Garrick /,, NASA. Ames Res. of the solution. The third analysis is a finite difference solution Center Classical Aerodyn. Theory Dec. 1979 p 257-289 of the unsteady, three dimensional Euler equations for the flow refs between adjacent blades. Analysis results are compared to data (NACA-452) Avail: NTIS NC A14/MF AOl CSCL O1A for a high speed propeller having eight swept blades integrally The problem of determining the two dimensional potential designed with the spinner and nacelle. Author flow around wing sections of any shape is examined. The problem is condensed into the compact form of an integral equation capable of yielding numerical solutions by a direct process. An attempt is made to analyze and coordinate the results of earlier studies relating to properties of wing sections. The existing approximate theory of thin wing sections and the Joukowski theory with its numerous generalizations are reduced to special cases of the general theory of arbitrary sections. permitting a N80.15052*# Boeing Commercial Airplane Co., Seattle, Wash. clearer perspective of the entire field The method which permits A USERS GUIDE FOR A344: A PROGRAM USING A FINITE the determination of the velocity at any point of an arbitrary DIFFERENCE METHOD TO ANALYZE TRANSONIC FLOW section and the associated lift and moments is described. The OVER OSCILLATING AIRFOILS Final Report iiiethod is also discussed in terms for developing new shapes Warren H Weatherill and F. Edward Ehlers Nov. 1979 65 p of preassigned aerodynamical properties. A.W.H. refs (Contract NAS1-15128) (NASA-CR . 159141: 06-48837) Avail: NTIS National Advisory Committee for Aeronautics N8015047*# HC A04/MF AOl CSCL O1A Langley Aeronautical Lab.. Langley Field. Va. The design and usage of a pilot program for calculating the GENERAL THEORY OF AERODYNAMIC INSTABILITY AND pressure distributions over harmonically oscillating airfoils in THE MECHANISM OF FLUTTER transonic flow are described, The procedure used is based on Theodore Theodorsen In NASA. Ames Res. Center Classical separating the velocity potential into steady and unsteady parts Aerodyn. Theory Dec. 1979 291-311 p and linearizing the resulting unsteady differential equations for small disturbances. The steady velocity potential which must be (NACA-496( Avail: NTIS HC A14/MF AOl CSCL O1A obtained from some other program, was required for input The The aerodynamic forces on an oscillating airfoil or airfoil- unsteady equation, as solved. is linear with spatially varying aileron combination of three independent degrees of freedom coefficients, Since sinusoidal motion was assumed, time was were determined. The problem resolves itself into the solution not a variable. The numerical solution was obtained through a of certain definite integrals, which were identified as Bessel finite difference formulation and either a line relaxation or an functions of the first and second kind, and of zero and first out of core direct solution method. ' ACT, order. The theory, based on potential flow and the Kutta condition, is fundamentally equivalent to the conventional wing section theory relating to the steady case. The air forces being known, the mechanism of aerodynamic instability was analyzed. An exact solution, involving potential flow and the adoption of the Kutta condition, was derived. The solution is of a simple form and is expressed by means of an auxiliary parameter k. The flutter velocity, treated as the unknown quantity, was determined as a function of a certain ratio of the frequencies in N80-15055# ARO, Inc., Arnold Air Force Station, Tenn. the separate degrees of freedom for any magnitudes and EVALUATION OF THE AERODYNAMIC CHARACTERISTICS combinations of the airfoil-aileron parameters. A.W.H. OF A 1/20-SCALE A-b MODEL AT MACH NUMBERS FROM 0.30 TO 0.75 Final Report Phillip L. Yeakley AEDC Sep. 1979 90 p refs (AF Proj. 329A) N80- 1 5050*# National Aeronautics and Space Administration. Langley Research Center, Hampton, Va (AD -A074867; AEDC-TR-78-66; AFATL-TR-78- 103) Avail' A PARAMETRIC WING DESIGN STUDY FOR A MODERN NTIS NC A05/MF AOl CSCL 20/4 LAMINAR FLOW WING A 1/20-scale model of the A-b aircraft was tested to determine the aerodynamic and control characteristics of the John A. Koegler. Jr. Dec. 1979 44 p refs (NASA-TM-80154) Avail: NTIS NC A03/MF AOl CSCL basic aircraft, evaluate the effect of external store configurations O1A on the static stability and drag characteristics of the aircraft, The results of a parametric wing design study using a modern and investigate the effects of Reynolds number, boundary layer laminar flow airfoil designed to exhibit desirable stall characteristics transition grit. and aerodynamic hysteresis on the data, Data while maintaining high cruise performance are presented. It was were obtained at angles of attack from -4 to 20 deg and at found that little is sacrificed in cruise performance when satisfying sideslip angles from . 10 to 10 deg. The Mach number range the stall margin requirements if a taper ratio of 0.65 or greater was from 0.30 to 0.75. and the Reynolds number range was from 0.7 to 49 million per foot. is used. M.G. GRA.

N80-15051 t # National Aeronautics and Space Administration Lewis Research Center. Cleveland, Ohio. SUMMARY OF ADVANCED METHODS FOR PREDICTING N80-15058# Dayton Univ. Research Inst.. Ohio HIGH SPEED PROPELLER PERFORMANCE A FIRST LOOK AT THE EFFECT OF SEVERE RAINFALL L. A Bober 1980 14 p refs Presented at 18th Aerospace UPON AN AIRCRAFT Sci. Meeting, Pasadena, Calif., 14-16 Jan. 1980; sponsored by Jan. 1980 34 p refs AIAA (Grant N5G-6026( (NASA'TM'81409) Avail: NTIS NC A02/MF AOl CSCL )NASA-CR-162569) Avail: NTIS HC A03/MF AOl CSCL O1A O1C

127 N80- 15059

An aircraft penetrating heavy rain can be affected exceeds runway capacity and aircraft delays occur. To reduce aerodynamically in at least four ways: (1) raindrops striking the delays at major airports, the Congress and Secretary of fuselage and wings of the aircraft impart a downward momen- Transportation should take actions to shift traffic from peak to tum to the aircraft: (2) increased aircraft drag results from the off-peak periods or to other airports by amending the Airport aircraft striking the raindrops head on: (3) at any instant of and Airway Development Act of 1970. GRA time the aircraft will contain a thin layer of water over most of its surfaces which will give additional mass to the aircraft: and N80- 15062*11 Magnavox Government and Industrial Electronics (4) the water on the airfoil will result in a roughened airfoil Co., Torrance, Calif. Advanced Products Div. surface that could produce significant aerodynamic penalties. An DESIGN STUDY OF A LOW COST CIVIL AVIATION GPS order of magnitude calculation was made for the penalty RECEIVER SYSTEM Final Report associated with the factors one two and three. The roughness R Cnossen and G. Gilbert (GAC Assoc.) Dec. 1979 150 p factor required detailed modeling and boundary layer calculations refs and was studied using the aerodynamic effects of frost model. (Contract NAS1-15343( The results achieved on each of the penalty factors are described INASA-CR-159176; 8-6132) Avail: NTIS HC A07/MF AOl and the factors most likely to cause significant performance CSCL 17G R.E.S. degradation are indicated. A low cost Navstar receiver system for civil aviation applications was defined. User objectives and constraints were N80-15O59# National Aeronautics and Space Administration. established. Alternative navigation processing design trades were Lewis Research Center. Cleveland. Ohio. evaluated, Receiver hardware was synthesized by comparing SIMULTANEOUS CABIN AND AMBIENT OZONE MEA- technology projections with various candidate system designs. A SUREMENTS ON TWO BOEING 747 AIRPLANES. control display unit design was recommended as the result of VOLUME 1 field test experience with Phase I GPS sets and a review of Porter J. Perkins. J. D. Holdeman. and G. 0. Nastrom (Control special human factors for general aviation users. Areas requiring refs Data Corp.. Minneapolis. Minn.) Jul. 1979 826 p technology development to ensure a low cost Navstar Set in (NASA-TM-79166; FAA-EE-79-05: E-196) Avail: NTIS the 1985 timeframe were identified. ACT. HC A99/MF AOl CSCL O1C Measurements of zone concentrations both outside and in N8O-15063 Ohio Univ., Athens. the cabin of an airline operated Boeing 747SP and Boe- 5 # Avionics Engineering Center. ing 747-100 airliner are presented. Plotted data and the corresponding tables of observations taken at altitude between EXPERIMENTAL LOOP ANTENNAS FOR 60 KHz TO 200 KHz the departure and destination airports of each flight are Ralph W. Burhans Dec. 1979 9 refs arranged chronologically for the two aircraft. Data were taken p (Grant NGR-36-OO9-017(' at five or ten minute intervals by automated instrumentation used in the NACA Global Atmospheric Samplin Program. (NASA-CR-162729; TM-71( Avail: NTIS HC AO2/MF AOl CSCL 17G M.M.M. The design and design data for broadband loop antenna systems are presented. An investigation of some simple systems for possible Loran C receivers which require a bandwidth of greater than 20 KHz is discussed, Designs are presented for a 60 KHz WWVB antenna. several Loran C variations, and some 1750 meter band antennas Signals received on all these, including N8O. 15060*# National Aeronautics and Space Administration. one airborne experiment where a Loran C receiver gave the Washington. 0. C. correct time difference reading within 1 microsecond while flying NASA TECHNICAL ADVANCES IN AIRCRAFT OCCUPANT on a straightline course are examined. The phase reversal in the SAFETY Loran C when the direction of travel changes 180 degrees is John H. Enders 1978 28 p refs Presented at the SAE Congr and Exposition. Detroit. 27 Feb. - 3 Mar 1978 discussed and possible corrections are studied. A.W.H )NASA-TM-8085 1, ISSN-0148-7 191) Avail NTIS HC A03/MF AOl CSCLO1C NASA's aviation safety technology program examines specific safety problems associated with atmospheric hazards, crash-fire survival, control of aircraft on runways, human factors, terminal N80 . 15064*# Ohio Univ. Athens. Avionics Engineering area operations hazards, and accident factors simulation. While Center. aircraft occupants are ultimately affected by any of these hazards. DATA REDUCTION SOFTWARE FOR LORAN-C FLIGHT their well-being is immediately impacted by three specific events: TEST EVALUATION unexpected turbulence encounters, fire and its effects, and crash Joseph P Fischer Dec. 1979 43 p refs impact NASA research in the application of laser technology to (Grant NGR-36-OO9-017( the problem of clear air turbulence detection, the development (NASA-CR-16273O; TM-72( Avail: NTIS HC AO3/MF AOl of fire resistant materials for aircraft construction, and to the CSCL hG improvement of seats and restraint systems to reduce crash A set of programs designed to be run on an IBM 370/ injuries are reviewed A R,H 158 computer to read the recorded time differences from the tape produced by the LORAN data collection system. convert them to latitude/longitude and produce various plotting input files are described The programs were written so they may be tailored easily to meet the demands of a particular data reduction N80-15061// General Accounting Office. Washington. D. C lob. The tape reader program is written in 370 assembler language Community and Economic Development Div. and the remaining programs are written in standard IBM AIRCRAFT DELAYS AT MAJOR US AIRPORTS CAN BE FORTRAN-IV language. The tape reader program is dependent REDUCED upon the recording format used by the data collection system 4 Sep. 1979 36 p refs and on the I/O macros used at the computing facility. The (P8-299442/4. CED . 79-102( Avail. NTIS HC AO3/MF AOl other programs are generally device-independent, although the CSCL OlE plotting routines are dependent upon the plotting method used. In 1977, aircraft delays cost U.S. airlines over $800 million, The data reduction programs convert the recorded data to a detained the traveling public over 60 million hours: and caused more readily usable form; convert the time difference (TD( numbers the airlines to use an additional 700 million gallons of fuel, to latitude/longitude (Iat/Iong(. to format a printed listing of the over 8 percent of their total consumption. Generally, aircraft TDs, lat/long, reference times, and other information derived delays result from excessive air traffic and bad weather. Many from the data, and produce data files which may be used for major U.S airports have peak, congested periods when air traffic subsequent plotting. M MM.

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NBO. 15065*# Ohio Univ. Athens. Avionics Engineering Thomas W Showalter and Benton L. Parris Jan. 1980 45 p Center. refs LORAN DIGITAL PHASE-LOCKED LOOP AND RF FRONT- INASA-TP-1601: A-7875l Avail: NTIS HC A03/MF AOl CSCL END SYSTEM ERROR ANALYSIS OlC Daryl L. McCall Dec. 1979 19 p Data are presented that show the effects of motion system (Grant NGR-39.0O9-017) cues. g-seat cues, and pilot experience on pilot performance (NASA-CR-16273l; TM . 73) Avail: NTIS HC A02/MF AOl during takeoffs with engine failures, during in-flight precision CSCL 17G turns, and during landings with wind shear. Eight groups of An analysis of the system performance of the digital phase USAF pilots flew a simulated KC- 135 using four different cueing locked loops IDPLLI and RF front end that are implemented in systems. The basic cueing system was a fixed-base type the MINI- L4 Loran receiver is presented. Three of the four (no-motion cueing) with visual cueing. The other three systems esperiments deal with the performance of the digital phase locked were produced by the presence of either a motion system or a loops. The other experiment deals with the RF front end and g-seat. or both. Extensive statistical analysis of the data was' DPLL system error which arise in the front end due to poor performed and representative performance means were examined. signal to noise ratios. The ability of the DPLLs to track the These data show that the addition of motion system cueing offsets is studied. results in significant improvement in pilot performance for all three tasks: however. the use of g-seat cueing. either alone or in conjunction with the motion system, provides little if any N80.15067*# National Aeronautics and Space Administration. performance improvement for these tasks and for this aircraft Ames Research Center. Moffett Field, Calif. type. Author NASA/ARMY XV-15 TILT ROTOR RESEARCH AIRCRAFT WIND-TUNNEL TEST PROGRAM P(.AN James A. Weiberg and Martin D. Maisel IAVRADCOM Res. and N8O15O7O*# Lockheed-Georgia Co., Marietta, Technol. Labs.) Mar. 1979 73 p refs EXPLORATORY STUDIES OF THE CRUISE PERFORMANCE (NASA-TM-78562. A-7740; AVRADCOM-TR-79-7(AM)( Avail OF UPPER SURFACE BLOWN CONFIGURATION: EXPER- NASA Ames Research Center, Moffett Field, Calif. 94035 IMENTAL PROGRAM. HIGH-SPEED FORCE TESTS CSCL O1C .J. A, Braden, J. P. Hancock. K. P. Burdges. and J. E. Hackett To ensure that the XV- 1 5 tilt iotor research aircraft will Langley Rex Center, Hampton. Va. NASA Oct 1979 231 p meet the requirements of the Program plan and the contract refs model specification and statement of work, one of the two aircraft (Contract NASI.13871I will be tested in the Ames 40 x 80 foot wind tunnel to provide (NASA-CR- 159134. LG77ER0028( Avail. NTIS an initial assessment of the aerodynamic characteristics. HC All/ME AOl CSCLO1C structural loads, and rotor/pylon/wing dynamics in a simulated The work to develop a wing-nacelle arrangement to accommo- flight environment for correlation with estimated values The tests date a wide range of upper surface blown configuration is reported will also serve to verify the functional operation of the aircraft Pertinent model and installation details are described. Data of systems and on-board instrumentation in a flight environment. the effects of a wide range of nozz(e geometric variations are The management structure, operational plan, support require- presented. Nozzle aspect ratio, boattail angle, and chordwise ments and responsibilities, safety provisions and reporting position are among the parameters investigated. Straight and requirements for conduct of the wind tunnel tests are defined swept wing configurations were tested across a range of nozzle and related to other phases of the program. A.R.H. pressure ratios, lift coefficientx, and Mach numbers. F.O S.

N80,15071*# Lockheed-Georgia Co.. Marietta. N8O15O68*# National Aeronautics and Space Administration. EXPLORATORY STUDIES OF THE CRUISE PERFORMANCE Hugh L. Dryden Flight Research Center, Edwards. Calif. OF UPPER SURFACE BLOWN CONFIGURATIONS: LOADING TESTS OF A WING STRUCTURE FOR A EXPERIMENTAL PROGRAM. HIGH-SPEED PRESSURE HYPERSONIC AIRCRAFT TESTS Roger A Fields, Lawrence F Reardon, and William H. Siegel J A. Braden. J. P. Hancock. K. P. Burdges. and J. E. Hackett Jan. 1980 72 p refs Langley Rex. Center. Hampton. Va. NASA Oct. 1979 226 p (NASA-TP-1596, H-1046( Avail. NTIS HC A04/MF AOl CSCL refs 01 C (Contract NAS1-1387 11 Room-temperature loading tests were conducted on a wing (NASA-CR-159135; LG77ER0028( Avail: NTIS structure designed with a beaded panel concept for a HC All/ME AOl CSCLO1C Mach 8 hypersonic research airplane. Strain, stress, and deflec- Basic pressure data are presented which wax obtained from tion data were compared with the resultx of three finite-element an experimental study of upper-surface blown configurations at structural analysis computer programs and with design data The cruise. The high-speed (subsonic) experimental work. studying test program data were used to evaluate the structural concept the aerodynamic effects of wing-nacelle geometric variations, was and the methods of analysis used in the design. A force stiffness conducted around semi-span model configurations composed of technique was utilized in conjunction with load conditions which diversified. interchangeable components. Power simulation was produced various combinations of panel shear and compression provided by high-pressure air ducted through closed forebody loading to determine the failure envelope of the buckling critical nacelles. Nozzle geometry was varied across size, exit aspect beaded panels. The forcestiffness data did not result in any ratio, exit position and boattail angle. Both 3-D force and 2-D predictions of buckling failure. It was, therefore, concluded that pressure measurements were obtained at cruise Mach numbers the panels were conservatively designed as a result of design from 0.5 to 0.8 and at nozzle pressure ratios up to about 3.0. constraints and assumptions of panel eccentricities. The analysis The experimental Investigation was supported by an analytical programs calculated strains and stresses competently. Compari- synthesis of the system using a vortex lattice representation sons between calculated and measured structural deflections with first-order power effects. Results are also presented from a showed good agreement. The test program offered a positive compatibility study in which a short-haul transport ix designed demonstration of the beaded panel concept subjected to on the basis of the aerodynamic findings in the experimental roomtemperature load conditions. Author study as well as acoustical data obtained in a concurrent program. High-lift text data are used to substantiate the projected performance of the selected transport design. Author N80. 15069*# National Aeronautics and Space Administration. Ames Research Center, Moffett Field. Calif. N8O15O72*# Lockheed-Georgia Co.. Marietta. THE EFFECTS OF MOTION AND g . SEAT CUES ON PILOT EXPLORATORY STUDIES OF THE CRUISE PERFORMANCE SIMULATOR PERFORMANCE OF THREE PILOTING OF UPPER SURFACE BLOWN CONFIGURATIONS: TASKS PROGRAM ANALYSIS AND CONCLUSIONS

129 N80- 15073

J. A. Braden. J. P. Hancock, J. E. Hackett. and V. Lyman Langley assembly: (2) optimizing fiber orientation in the vicinity of heavily Res. Center. Hampton. Va. NASA Oct. 1979 349 p refs loaded joints: (3( failure mechanisms and delamination: (4( the (Contract NAS1-13871) construction of an ultralight sailplane: (5) computer-aided (NASA-CR . 159136: LG77EROO2B( Avail: NTIS design: finite element analysis programs. preprocessor develop. HC A15/MF AOl CSCL O1C ment. and array preprocessor for SPAR: l6( advanced analysis The experimental data encompassing surface pressure methods for composite structures: (7( ultrasonic nondestructive measurements, and wake surveys at static and wind-on conditions testing: (8) physical properties of epoxy resins and composites: are analyzed. Cruise performance trends reflecting nacelle (9) fatigue in composite materials. and (10( transverse thermal geometric variations, and nozzle operating conditions are expansion of carbon/epoxy composites. A.R.H. presented. Details of the modeling process are included. F.O.S. N80-15077# Boeing Vertol Co.. Philadelphia. Pa. N80. 15073*# Rockwell International Corp. El Segundo. Calif. CH-46 COMPOSITE ROTOR BLADE FLIGHT STRESS ANALYSES AND TESTS OF THE B-i AIRCRAFT STRUC- SURVEY DATA. VOLUME 3: PLO1TED FORWARD ROTOR TURAL MODE CONTROL SYSTEM Final Report BLADE CHORD. TORSION AND ABSOLUTE LOADS John H. Wykes, Thomas A. Byar. Cary J. MacMiller. and David R. AielIo and J. Bendo 1978 324 p refs C. Greek Jan. 1980 268 p refs IContract N00019-75-C-0396l (Contract NAS4-2519) (AD-A075612: D210-i 1 168-3-VoI-3( Avail: NTIS INASA-CR-144887: H-i 109: NA-79-405( Avail: NTIS NC Al4/MF AOl CSCL 01/3 HC Al2/MF AOl CSCL O1C Data plots are presented of flight stress tests performed on Analyses and flight tests of the B- 1 structural mode control the CH-46 aircraft composite rotor blades. M M.M. system (SMCS( are presented. Improvements in the total dynamic response of a flexible aircraft and the benefits to ride qualities. N80-15078fl Army Test and Evaluatibn Command. Aberdeen handling qualities, crew efficiency, and reduced dynamic loads Proving Ground, Md. on the primary structures, were investigated. The effectiveness AIRCRAFT ANTI-ICING/DE-ICING Final Report and the performance of the SMCS. which uses small aerody- 31 Aug. 1979 21 p namic surfaces at the vehicle nose to provide damping to the (AD-A074128: TOP-7-3-528l Avail: NTIS HC A02/MF AOl structural modes, were evaluated. R.E.S. CSCL 01/3 This document provides information, methodology and N8O15O74*# Lockheed-California Co.. Burbank. techniques necessary to plan. conduct and document a develop- HYPERSONIC CRUISE AIRCRAFT PROPULSION INTEGRA- ment test of an aircraft anti-icing/de-icing system. A development TION STUDY. VOLUME 1 Final Report. Jun. 1978 - Sep. test of an aircraft anti . icing/de . icing system will determine the 1979 degree to which a subject system and its associated documenta- R. E. Morris and G D Brewer Sep. 1979 96 p ref tion, tools and auxiliary equipment meets the requirements of (Contract NAS1-15057( the Army Materiel Needs documents. GRA (NASA-CR- 158926-Vol-i: LR-2865 i-Vol-i ( Avail NTIS NC A05/MF AOl CSCL O1C N80-15079# Textron Bell Helicopter, Fort Worth, Tex A hypersonic cruise transport conceptual design is described. ANALYSIS OF LOW-SPEED HELICOPTER FLIGHT TEST The integration of the subsonic, supersonic, and hypersonic DATA Final Report. Mar. 1977 . Mar. 1979 propulsion systems with the aerodynamic design of the airframe James L. TangIer Aug. 1979 145 p rets is emphasized. An evaluation of various configurations of aircraft (Contract DAAJO2-77-C-0022: DA ProI 1 L2-62209-AH-76( and propulsion integration concepts, and selection and refinement (AD-A074i4l: BHT-699-099-103: USARTL-TR-79- 19( Avail: of a final design are given. This configuration was used as a NTIS NC A07/MF AOl CSCL 01/3 baseline to compare two propulsion concepts - one using a The purpose of this study was to investigate the aerodynamic fixed geometry dual combustion mode scramlet and the other a behavior of a helicopter rotor operating in the low-speed flight variable geometry ramjet engine. Both concepts used turbojet regime. particularly in the nap-of-the-Earth (NOE) evasive mode. engines for takeoff. landing and acceleration to supersonic The effort consisted of reducing and analyzing existing AH-1G speed. R.C.T. flight test response data acquired for simulated NOE flight under contract DAAJO2-73-C-0105. Specific areas of interest analyzed N8O15O75* # Lockheed-California Co., Burbank. in this study include blade/vortex interaction at 50 knots and HYPERSONIC CRUISE AIRCRAFT PROPULSION INTEGRA- angle-of-attack data derived from hot-wire measurements taken TION STUDY. VOLUME 2 Final Report. Jun. 1978 - Sep. in hover. GRA 1979 R. E. Morris and G. D. Brewer Sep. 1979 244 p refs (Contract NAS1-15057( N80-15080# Naval Air Test Center, Patuxent River. Md. (NASA-CR-i 58926-Vol-2: LR-28651 -Vol-2( Avail: NTIS JA-6A CIRCULATION CONTROL WING CONTRACTOR NC Ai1/MF AOl CSCLO1C FLIGHT DEMONSTRATION Conceptual vehicle configuration and propulsion approach for R. W Boyd 28 Aug. 1979 25 p refs a Mach 6 transport aircraft capable of carring 200 passengers (AD-A074888, NATC-TM-79-2-SA( Avail' NTIS 9260 km was investigated. Wind tunnel test data for various NC A02/MF AOl CSCL 01/3 hypersonic transport configurations were examined. Canidates for A Circulation Control Wing (CCW( Flight Demonstrator was baseline reference vehicles were selected. An explanation of designed and built by Grumman Aerospace Corporation (GAC( technical methods which were used and configuration details using a modified A-6A airplane The design was a joint effort which were significant in the final vehicle concept are given. by David Taylor Naval Ship Research and Development Center R.C.T. (DTNSRDC( and GAC based on research originated by DTNSRDC. The airplane demonstrated significant STOL potential. Compared N80-15076 t # Rensselaer Polytechnic Inst., Troy. N. Y. to the basic A-6A airplane. takeoff and landing roll distances COMPOSITE STRU CTU RAL MATERIALS Semiannual were improved by 36% and 43%, respectively. Maximum CL Report. Apr. Sep. 1979 was increased by 80%. Some Handling Qualities problems are George S. Ansell, Robert G. Loewy, and Stephen E. Wiberly discussed. The CCW concept was shown to be a viable, simple, Dec. 1979 107 p refs Sponsored in part by AFOSR and powerful STOL tool for use in future designs. GRA (Grant NGL-33-018-003( (NASA'CR-i62578: SAR-37( Avail: NTIS NC A06/MF AOl CSCL O1C A multifaceted program is described in which aeronautical, N80-15081# Army Research and Technology Labs., Fort Eustis. mechanical, and materials engineers interact to develop composite Va. aircraft structures. Topics covered include: (1 ( the design of an MODEL 540 ROTOR BLADE CRACK PROPAGATION advanced composite elevator and a proposed spar and rib INVESTIGATION Final Report. Jan, - Feb. 1978

130 N80- 15088

Danny E. Good Aug. 1979 35 p refs Tests of a twenty inch diameter, low tip speed. low pressure (DA Proj. 1F2-62209-AH-76) ratio fan which investigated aft fan noise reduction techniques (AD-A074734; USARTL-TR-79-26) Avail: NTIS are reported. The 1/3 octave band sound data are presented HC A03/MF AOl CSCLO1/3 for all the configurations tested. The model data are presented The rate of crack propagation from an induced defect in a on 17 foot arc and extrapolated to 200 foot sideline. J.M.S. metal Bell Helicopter 540 main rotor blade was investigated. A controlled crack front was introduced into the top surface of N8015086*# General Electric Co.. Cincinnati, Ohio. Advanced the blade spar. Fatigue testing was conducted at maximum level Engineering and Technology Programs Dept. flight loads and the crack growth was monitored, Experimental QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE data was then compared with analytical predictions to measure (QCSEE) OVER THE WING (OTW) DESIGN REPORT Final the ability to predict crack growth characteristics. GRA Report Jun. 1977 530 p (Contract NAS3- 18021) N80-15082# Naval Air Development Center. Warminster. Pa. (NASA-CR . 134848; R75AEG443( Avail. NTIS Aircraft and Crew Systems Technology Directorate. HC A23/MF AOl CSCL 21E VISUAL ACCOMMODATION RESPONSES IN A VIRTUAL The design. fabrication, and testing of two experimental high IMAGE ENVIRONMENT Phase Report bypass geared turbofan engines and propulsion systems for short Gloria Twine Chisum and Phyllis E. Morway 1979 15 p refs haul passenger aircraft are described. The propulsion technology (WRO4 1010101) required for future externally blown flap aircraft with engines (AD-A0744 15; NADC.792 13-60) Avail: NTIS located both under the wing andover the wing is demonstrated, HC A02/MF AOl CSCL 05/5 Composite structures and digital engine controls are among the The virtual imges generated for helmet mounted displays topics included. R.C.T. and head-up displays are reflected by beam splitters to the eyes of a user. The influence of the beam splitters, with and without N80. 15087*# General Electric Co., Cincinnati, Ohio. Aircraft images reflected, on the accommodation responses of observers Engine Group. was measured utilizing an eyetracker which continuosly monitored the accommodation response. The results indicate that the QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE presence of the beam splitter aids in maintaining accommodation (QCSEE). AERODYNAMIC AND AEROMECHANICAL at or near infinity. GRA PERFORMANCE OF A 50.8 cm (20 INCH) DIAMETER 1.34 PR VARIABLE PITCH FAN WITH CORE FLOW R. G. Giffin. A. A. McFalIs. and B. F. Beacher Aug. 1977 N8015083*# General Electric Co., Washington. D. C. Aircraft 133 p refs Engine Group (Contract NAS3- 18021) DEMONSTRATION OF SHORT-HAUL AIRCRAFT AFT (NASA-CR-i 35017; R75AEG445( Avail: NTIS NOISE REDUCTION TECHNIQUES ON A TWENTY INCH HC AO7/MF AOl CSCL 21E (50.8 cm) DIAMETER FAN. VOLUME 1 The fan aerodynamic and aeromecharrical performance tests 0. L Stimpert and A. A. McFalls May 1975 131 p refs of the quiet clean short haul experimental engine under the 3 Vol. wing fan and inlet with a simulated core flow are described. (Contract NAS3-18021( Overall forward mode fan performance is presented at each rotor (NASA-CR- 134849, R75AEG252-VoI- 1) Avail NTIS pitch angle setting with conventional flow pressure ratio efficiency HC A07/MF AOl CSCL 21E fan maps, distinguishing the performance characteristics of the Tests of a 20 inch diameter, low tip speed, low pressure fan bypass and fan core regions. Effects of off design bypass ratio fan which investigated aft fan noise reduction techniques ratio, hybrid inlet geometry, and tip radial inlet distortion on fan are reported. These techniques included source noise reduction performance are determined. The nonaxisymmetric bypass OGV features of selection of vane-blade ratio to reduce second harmonic and pylon configuration is assessed relative to both total pressure noise. spacing effects, and lowering the Mach number through loss and induced circumferential flow distortion. Reverse mode a vane row Aft suppression features investigated included porosity performance, obtained by resetting the rotor blades through both effects, variable depth treatment, and treatment regenerated flow the stall pitch and flat pitch directions, is discussed in terms of noise. Initial results and selected comparisons are presented, the conventional flow pressure ratio relationship and its implica- J.M S. tions upon achievable reverse thrust. Core performance in reverse mode operation is presented in terms of overall recovery levels N80-15084t # General Electric Co.. Washington, D. C. Aircraft and radial profiles existing at the simulated core inlet plane. Engine Group. Observations of the starting phenomena associated with the DEMONSTRATION OF SHORT-HAUL AIRCRAFT AFT initiation of stable rotor flow during acceleration in the reverse NOISE REDUCTION TECHNIQUES ON A TWENTY INCH mode are briefly discussed. Aeromechanical response characteris- (50.8) DIAMETER FAN. VOLUME 2 tics of the fan blades are presented as a separate appendix, 0. L Stimpert Apr. 1975 307 p 3 Vol. along with a description of the vehicle instrumentation and method (Contract NAS3- 18021) of data reduction. R.C.T (NASA-CR-134850: R75AEG252-Vol-2( Avail: NTIS HC A14/MF AOl CSCL 21E N8015088*# General Electric Co., Cincinnati, Ohio. Advanced Aft fan noise reduction techniques were investigated. The Engineering and Technology Programs Dept. 1/3 octave band sound data were plotted with the following QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE plots included: perceived noise level vs acoustic angle at 2 fan (QCSEE) PRELIMINARY UNDER THE WING FLIGHT speeds: PWL vs frequency at 2 fan speeds: and sound pressure PROPULSION SYSTEM ANALYSIS REPORT level vs frequency at 2 aft angles and 2 fan speeds. The source 0. F. Howard Feb. 1976 261 p refs noise plots included: band pass filter sound pressure level vs (Contract NAS3-18O21( acoustic angle at 2 fan speeds; and 2nd harmonic SPL acoustic (NASA-CR- 134868: R75AEG349( Avail: NTIS angle at 2 fan speeds. A C.T HC Al2/MF AOl CSCL 21E The pre(iminary design and installation of high bypass, N80-15085 5 # General Electric Co. Cincinnati, Ohio. Aircraft geared turbofan engine with a composite nacelle forming the Engine Group. propulsion system for a short haul passenger aircraft are described. DEMONSTRATION OF SHORT HAUL AIRCRAFT AFT NOISE The technology required for externally blown flap aircraft with REDUCTION TECHNIQUES ON A TWENTY INCH (50.8 cm) under the wing (UTW( propulsion system installations for DIAMETER FAN. VOLUME 3 introduction into passenger service in the mid 1 980's is included. D. L. Stimpert Apr. 1975 725 p 3 Vol. The design, fabrication. and testing of this DEW experimental (Contract NAS3- 18021) engine containing the required technology items for low noise. (NASA-CR- 134851, R75AEG252-Vol-3( Avail: NTIS fuel economy, with composite structure for reduced weight and HC A99/MF AOl CSCL 21E digital engine control are provided. R.C.T.

131 N80- 15089

N80, 15089*# General Electric Co.. Cincinnati. Ohio. Group Noise measurements were taken on a turbofan engine which Engineering Div. uses the same core, with minor modifications, employed on the QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE quiet clean short-haul experimental engine (QCSEEI propulsion (QCSEE). THE AERODYNAMIC AND MECHANICAL systems. Both nearfield and farfield noise measurements were DESIGN OF THE QCSEE OVER-THE-WING FAN taken in order to determine the core internally generated noise Apr. 1976 98 p levels. The resulting noise measurements were compared to (Contract NAS3-18O21( predicted combustor and turbine noise levels, to verify or improve (NASA-CR-134915( Avail: NTIS HC AO5/MF AOl CSCL the predicted QCSEE combustor and turbine noise levels. Author 21E The aerodynamic and mechanical design of a fixed-pitch 1.36 pressure ratio fan for the over-the-wing (OTW( engine is presented. The fan has 28 blades. Aerodynamically, the fan blades N8O15O94*# General Electric Co.. Cincinnati. Ohio. Aircraft were designed for a composite blade, but titanium blades were Engine Engineering Div. used in the experimental fan as a cost savings measure. R.E.S. QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE (QCSEE) UNDER-THE-WING (UTW) ENGINE COMPOSITE NACELLE TEST REPORT. VOLUME 1: SUMMARY. N8O15O9O*fl General Electric Co.. Cincinnati. Ohio. Advanced Engineering and Technology Programs Dept. AERODYNAMIC AND MECHANICAL PERFORMANCE Apr. 1979 214 QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE p refs (QCSEE) UNDER-THE-WING ENGINE DIGITAL CONTROL (Contract NAS3-18O21( SYSTEM DESIGN REPORT (NASA-CR- 159471; R78AEG573-VoI- 11 Avail: NTIS HC A1O/MF AOl CSCL 21E Jan. 1978 321 refs p The performance test results of the final under-the-wing engine (Contract NAS3-18021) configuration are presented. One hundred and six hours of engine (NASA-CR- 134920; R75AEG483( Avail: NTIS operation were completed, including mechanical and performance HC A14/MF AOl CSCL 21E checkout, baseline acoustic testing with a bellmnuth inlet, reverse A digital electronic control was combined with conventional thrust testing, acoustic technology tests, and limited Controls hydromechanical components to operate the four controlled testing. The engine includes a variable pitch fan having advanced variables on the under-the-wing engine: fuel flow, fan blade pitch. composite fan blades and using a ball-spline pitch actuation fan ehaust area, and core compressor stator angles. The engine system. and control combination offers improvements in noise, pollution. R.E.S. thrust response, operational monitoring, and pilot workload relative to current engines. R.E.S. N8O15O95*# General Electric Co.. Cincinnati. Ohio. Group Engineering Div. N8O15O91*# General Electric Co.. Cincinnati, Ohio. Advanced QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE Engineering and Technology Programs Dept. / (QCSEE) PRELIMI NARY OVER-THE-WING FLIGHT PROPUL- QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE SION SYSTEM ANALYSIS REPORT (QCSEE) UNDER-THE-WING ENGINE SIMULATION D. F. Howard Jun. 1977 174 p refs REPORT (Contract NAS3-18D21( (NASA-CR- 135296; R77AEG305( Avail: Jul. 1977 103 p refs NTIS (Contract NAS3-18O21( HC A08/MF AOl CSCL 21E The preliminary design of the Over-the-wing flight propulsion (NASA-CR- 134914: R75AEG444( Avail: NTIS HC AD6/MF AOl CSCL 21E system installation and nacelle component and systems design Hybrid computer simulations of the under-the-wing engine features of a short-haul, powered lift aircraft are presented. were constructed to develop the dynamic design of the controls. Economic studies are also presented and show that high bypass. The engine and control system includes a variable pitch fan and low pressure ratio turbofan engines have the potential of a digital electronic control. Simulation results for throttle bursts providing an economical propulsion system for achieving the very from 62 to 100 percent net thrust predict that the engine will quiet aircraft noise level of 95 EPNdB on a 152.4 m sideline. accelerate 62 to 95 percent net thrust in one second. R.E.S. R.E.S.

N8O15O92*# General Electric Co.. Cincinnati, Ohio. Advanced N8O15o96*# General Electric Co., Cincinnati, Ohio. Advanced Engineering and Technology Programs Dept. Engineering and Technology Programs Dept. QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE (QCSEE) OVER-THE-WING CONTROL SYSTEM DESIGN (QCSEE). UNDER-THE-WING (UTW) ENGINE BOILERPLATE REPORT NACELLE TEST REPORT. VOLUME 1 Summary Report 31 Dec. 1977 65 Dec. 1977 249 p refs p 3 Vol. (Contract NAS3-18D21( (Contract NAS3-18O21( (NASA-CR- 135337; R77AEG664( Avail: NTIS (NASA-CR- 135249; R77AEG2 121-Vol-i) Avail: NTIS HC A11/MF AOl CSCL 21E HC A04/MF AOl CSCL 21E A control system incorporating a digital electronic control The design and testing of high bypass geared turbofan engines was designed for the over-the-wing engine. The digital electronic with nacelles forming the propulsion systems for short haul control serves as the primary controlling element for engine fuel passenger aircraft are considered. The test results demonstrate flow and core Compressor stator position. It also includes data the technology required for externally blown flap aircraft for monitoring capability, a unique failure indication and corrective introduction into passenger service in the 1980's. The equipment action feature. and optional provisions for operating with a new tested is described along with the test facility and instrumentation. type of servovalve designed to operate in response to a A chronological history of the test and a summary of results digital-type signal and to fail with its output device hydraulically are given. J.M.S. locked into position. R.E.S.

N8O-15O97# General Electric Co.. Cincinnati, Ohio. Advanced Engneering and Technology Programs Dept. N8O15O93*# General Electric Co.. Cincinnati, Ohio. Aircraft QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE Engine Group. (QCSEE). UNDER-THE-WING (UTW) ENGINE BOILERPLATE QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE NACELLE TEST REPORT. VOLUME 3: MECHANICAL (QCSEE). CORE ENGINE NOISE MEASUREMENTS PERFORMANCE H. 0. Sowers and W. E. Coward Dec. 1977 52 p ref 31 Dec. 1977 128 p refs 3 Vol. (Contract NAS3-18021( (Contract NAS3-18O21( (NASA-CR-13516O; R75AEG51 1( Avail: NTIS (NASA-CR-i 35251; R77AEG2 1 2-V0I-3( Avail: NTIS HC A04/MF AOl CSCL 21E H,C A07/MF AOl CSCL21E

132 N80-15 104

Results of initial tests of the under the wing experimental containing a ball screw/spline driving two counteracting master engine and boilerplate nacelle are presented. The mechanical bevel gears meshing pinion gears attached to each of 18 fan performance of the engine is reported with emphasis on the blades. R.E.S. advanced technology components. Technology elements of the propulsion system covered include: system dynamics, composite fan blades, reduction gear, lube and accessory drive system, fan N8O151O2*# General Electric Co., Cincinnati. Ohio. frame, inlet, core cowl cooling, fan exhaust nozzle, and digital ACOUSTIC ANALYSIS OF AFT NOISE REDUCTION control system. J.M.S. TECHNIQUES MEASURED ON A SUBSONIC TIP SPEED 50.8 cm (TWENTY INCH) DIAMETER FAN N80-15098t # General Electric Co.. Cincinnati. Ohio. D. L. Stimpert and A. Clemons Jan. 1977 149 p refs QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE (Contract NAS3-18O21) (QCSEE). COMPOSITE FAN FRAME SUBSYSTEM TEST (NA5A-CR-134891; R75AEG368( Avail: NTIS REPORT HC AO7/MF AOl CSCL 21E C. L. Stotler. Jr. and J. H. Bowden Sep. 1977 71 p Sound data which were obtained during tests of a 50.8 cm (Contract NAS3- 18021) diameter, subsonic tip speed. low pressure ratio fan were analyzed. (NASA-CR- 135010: R76AEG233( Avail: NTIS The test matrix was divided into two major investigations: HC A04/MF AOl CSCL 21E (1) source noise reduction techniques; and (2) aft duct noise The element and subcomponent testing conducted to verity reduction with acoustic treatment. Source noise reduction the composite fan frame design of two experimental high bypass techniques were investigated which include minimizing second geared turbofan engines and propulsion systems for short haul harmonic noise by varying vane/blade ratio, variation in spacing. passenger aircraft is described. Emphasis is placed on the and lowering the Mach number through the vane row to lower propulsion technology required for future externally blown flap fan broadband noise. Treatment in the aft duct which includes aircraft with engines located both under the wing and over the flow noise effects, faceplate porosity, rotor OGV treatment, slant wing, including technology in composite structures and digital cell treatment, and splitter simulation with variable depth on engine controls. The element tests confirmed that the processes the outer wall and constant thickness treatment on the inner used in the frame design wQuld produce the predicted mechanical wall was investigated. Variable boundary conditions such as properties. The subcomponent tests verified that the detail variation in treatment panel thickness and orientation, and mixed structural components of the frame had adequate structural porosity combined with variable thickness were examined. Significant results are reported. Integrity. J.M.S. R.C.T.

N8O15O99*// General Electric Co.. Cincinnati. Ohio. Aircraft Engine Group. N8O15103*# Curtiss-Wright Corp.. Wood-Ridge, N.J. Power Systems. QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE (QCSEE) OVER-THE-WING (01W) BOILERPLATE NACELLE DESIGN REPORT (QCSEE) MAIN REDUCTION GEARS TEST PROGRAM Final Report May 1977 78 p 0. W. Misel Mar. 197/ 220 (Contract NA53-18O21( p refs (Contract NAS3-18O21( (NASA-CR- 135168; R77AEG300) Avail: NTIS (NASA-CR- 134669: HC AO5/MF AOl CSCL 21E CW-WR-77-OO8( Avail: NTIS HC A1O/MF AOl CSCL 21E A summary of the mechanical design of the boiler plate nacelle for the QCSEE over the wing (OTW) engine is presented. Sets of under the wing (UTWI engine reduction gears and The nacelle, which features a 0-shaped nozzle/thrust reverser sets of over the wing (OTW( engine reduction gears were fabricated and interchangeable hard wall and acoustic panels, is utilized in for rig testing and subsequent installation in engines. The UTVi/ the engine testing to establish the aerodynamic and acoustic engine reduction gears which have a ratio of 2.465:1 and a design rating of 9712 kW at 3157 rpm fan speed were operated requirements for nozzles and reversers of this type. J.M.S. at up to 105% s feed at 60% torque and 100% speed at 125% torque. The OTW engine reduction gears which have a ratio of N801510O*# General Electric Co.. Cincinnati, Ohio. Aircraft 2062 1 and a design rating of 12.6 15 kW at 3861 rpm fan Engine Group. speed were operated at up to 95% speed at 50% torque and QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE 80% speed at 109% torque. Satisfactory operation was demon- (QCSEE) UNDER-THE-WING (UTW) COMPOSITE NACELLE strated at powers up to 12.172 kW, mechanical efficiency up SUBSYSTEM TEST REPORT to 99.1% UTW. and a maximum gear pitch line velocity of C. L. Stotler, Jr., E. A. Johnston, and D. S. Freeman Jul. 1977 112 rn/s (22.300 fprn( with a corresponding star gear spherical 83 p refs roller bearing ON of 850.00 01W. Oil and star gear baring (Contract NAS3-18021) temperatures, oil churning, heat rejection, and vibratory character- (NASA-CR- 135075; R76AEG42O( Avail: NTIS istics were acceptable for engine installation. ACT. HC AO5/MF AOl CSCL 21E The element and subcomponent testing conducted to verity the under the wing composite nacelle design is reported. This composite nacelle consists of an inlet. Outer cowl doors, inner cowl doors, and a variable fan nozzle. The element tests provided N80. 15104*# General Electric Co., Cincinnati, Ohio. Advanced the mechanical properties used in the nacelle design. The Engineering and Technology Programs Dept. subcomponent tests verified that the critical panel and joint areas QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE of the nacelle had adequate structural integrity. JM.S. (QCSEE) CLEAN COMBUSTOR TEST REPORT Oct. 1975 66 p refs (Contract NAS3-18021) N80-15101# General Electric Co.. Cincinnati. Ohio. Advanced (NASA-CR- 134916: A75AEG449( Avail: NTIS Engineering and Technology Programs Dept. HC AO4/MF AOl CSCL 21E QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE A component pressure test was conducted on a F1O1 PFRT (QCSEE). BALL SPLINE PITCH CHANGE MECHANISM combustor to evaluate the emissions levels of this combustor DESIGN REPORT design at selected under the wing and over the wing operating Apr. 1978 73 p refs conditions for the quiet clean short haul experimental engine (Contract NAS3-18O21) (QCSEE(. Emissions reduction techniques were evaluated which (NASA-CR- 134873; R77AEG327( Avail: NTIS included compressor discharge bleed and sector burning in the HC AO4/MF AOl CSCL 21E combustor. The results of this test were utilized to compare the Detailed design parameters are presented for a variable-pitch expected QCSEE emissions levels with the emission goals of change mechanism. The mechanism is a mechanical system the OCSEE engine program. A.C.T

133 N80-15105

N80- 1 5105*// Curtiss-Wright Corp.. Wood- Ridge. N.J. N8O-15109t# General Electric Co.. Cincinnati. Ohio. Aircraft QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE Engine Group. (QCSEE) MAIN REDUCTION GEARS BEARING DEVELOP- QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE MENT PROGRAM Final Report (QCSEE): THE AERODYNAMIC AND MECHANICAL Dec. 1975 40 p DESIGN OF THE QCSEE UNDER-THE-WING FAN (Contract NAS3-18021) Mar. 1977 144 p (NASA-CR-134890) Avail: NTIS HC A03/MF AOl CSCL (Contract NAS3-18021) 21E (NASA-CR- 135009; R75AEG484( Avail: NTIS The viability of proposed bearing designs to operate at HC A07/MF AOl CSCL 21E application conditions is described. Heat rejection variables were The design. fabrication. and testing of two experimental high defined for the test conditions. Results indicate that there is bypass geared turbofan engines and propulsion systems for short potential for satisfactory operation of spherical roller bearing in haul passenger aircraft are described. The aerodynamic and the QCSEE main reduction gear application. R.C.T. mechanical design of a variable pitch 1.34 pressure ratio fan for the under the wing (UTW( engine are included. The UTW fan was designed to permit rotation of the 18 composite fan Curtiss-Wright Corp.. Wood-Ridge. N.J. N8O-15106*fl blades into the reverse thrust mode of operation through both QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE flat pitch and stall pitch directions. R.C.T. (QCSEE) MAIN REDUCTION GEARS DETAILED DESIGN REPORT Final Report A. Defeo and M. Kulina Jul 1977 221 p N8O1511O*# General Electric Co.. Cincinnati, Ohio. (Contract NAS3-18021) QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE (NASA-CR- 134872: CW-WR-77-024) Avail: NTIS (QCSEE) COMPOSITE FAN FRAME DESIGN REPORT HC A10/MF AOl CSCL 21E S C Mitchell Sep. 1978 97 p refs Lightweight turbine engines with geared slower speed fans (Contract NAS3-18O21( are considered. The design of two similar but different gear (NASA-CR- 135278: R77AEG439( Avail: NTIS ratio, minimum weight. epicyclic star configuration main reduction HC AO4/MF AOl CSCL 21E gears for the under the wing (UTW( and over the wing (OT\N( An advanced composite frame which is flight-weight and engines is discussed The UT\N engine reduction gear has a integrates the functions of several structures was developed for ratio of 2.465:1 and a 100% power design rating of 9885 kW the over the wing (01W) engine and for the under the wing (13.256 hp) at 3143 rpm fan speed. The OTW engine reduction (UTW( engine. The composite material system selected as the gear has a ratio of 2.062:1 and a 100% power design rating of basic material for the frame is Type AS graphite fiber in a 1 2813 kW (17183 hp) at 3861 rpm fan speed. Details of Hercules 3501 epoxy resin matrix. The frame was analyzed using configuration, stresses, deflections, and lubrication are pre- a finite element digital computer program. This program was sented J.M,S, used in an iterative fashion to arrive at practical thicknesses and ply orientations to achieve a final design that met all strength and stiffness requirements for critical conditions Using N8O151O7*# Hamilton Standard. Windsor Locks. Conn. Aircraft this information, the detail design of each of the individual parts Systems Dept. QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE of the frame was completed and released. On the basis of these designs, the required tooling was designed to fabricate the various (QCSEE): HAMILTON STANDARD CAM/HARMONIC component parts of the frame. To verify the structural integrity DRIVE VARIABLE PITCH FAN ACTUATION SYSTEM of the critical joint areas, a full-scale test was conducted on the DETAIL DESIGN REPORT frame before engine testing The testing of the frame established Mar. 1976 159 p critical spring constants and subjected the frame to three critical (Contract NAS3-18021) load cases. The successful static load test was followed by (NASA-CR- 134852; HSER-7001( Avail: NTIS 153 and 58 hours respectively of successful running on the HC A08/MF AOl CSCL 21E UTW and OTW engines. J M S. A variable pitch fan actuation system was designed which incorporates a remote nacelle-mounted blade angle regulator. The regulator drives a rotating fan-mounted mechanical actuator through a flexible shaft and differential gear train. The actuator incorporates a high ratio harmonic drive attached to a multitrack spherical cam which changes blade pitch through individual cam N80- 15111 General Electric Co., Cincinnati, Ohio. Advanced follower arms attached to each blade trunnion. Detail design Engineering and Technology Programs Dept parameters of the actuation system are presented. These include QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE the following: design philosophies, operating limits, mechanical. (QCSEE) UTW FAN PRELIMINARY DESIGN hydraulic and thermal characteristics, mechanical efficiencies. Feb. 1975 107 p materials, weights, lubrication, stress analyses, reliability and (Contract NAS3-18021( failure analyses. Author (NASA-CR- 134842, R75AEG2 13) Avail. NTIS HC AO6/MF AOl CSCL 21E N8O151O8*# General Electric Co.. Cincinnati, Ohio. Advanced High bypass geared turbofan engines and propulsion systems Engineering and Technology Programs Dept. designed for short-haul passenger aircraft are described. The QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE propulsion technology required for future externally blown flap (QCSEE) UNDER-THE-WING ENGINE COMPOSITE FAN aircraft with engines located both under the wing and over the BLADE DESIGN REPORT Final Report wing is emphasized. The aerodynamic and mechanical pre- R. Ravenhall and C. T. Salemme Feb. 1977 61 p refs liminary design of the QCSEE under the wing 1.34 pressure (Contract NAS3-18O21) ratio fan with variable blade pitch is presented. Design information (NASA-CR- 135046; R77AEG 177) Avail: NTIS is given for two pitch change actuation systems which will provide HC AO4/MF AOl CSCL 21E reverse thrust. J.M.S. A total of 38 quiet clean short haul experimental engine under the wing composite fan blades were manufactured for N8O15112*// General Electric Co., Cincinnati, Ohio. Advanced various component tests, process and tooling, checkout, and use Engineering and Technology Programs Dept. in the QCSEE UTW engine. The component tests included QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE frequency characterization, strain distribution, bench fatigue. (QCSEE): THE AERODYNAMIC AND PRELIMINARY platform static load. whirligig high cycle fatigue, whirligig low MECHANICAL DESIGN OF THE QCSEE 01W FAN cycle fatigue, whirligig strain distribution, and whirligig over- Feb 1975 80 p speed. All tests were successfully completed. All blades planned (Contract NAS3-18O21( for use in the engine were subjected to and passed a whirligig (NASA-CR- 134841; R75AEG38 1 ( Avail. NTIS proof spin test. . R.C.T. HC A05/MF AOl CSCL 21E

134 N80-1 5120

The aerodynamic and mechanical preliminary design of the The mechanical design of the boiler plate nacelle and core QCSEE over the wing 1.36 pressure ratio fan is presented. Design exhaust nozzle for the QCSEE under the wing engine is presented. information is given for both the experimental and flight The nacelle, which features interchangeable hard-wall and acoustic designs. J.M.S. panels, is to be utilized in the initial engine testing to establish acoustic requirements for the subsequent composite nacelle as N80-15113t fl General Electric Co.. Cincinnati. Ohio. Advanced well as in the QCSEE over the wing engine configuration.J.M.S. Engineering and Technology Programs Dept. QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE N80-15117*# Hamilton Standard, Windsor Locks, Conn. (QCSEE) UNDER-THE-WING ENGINE COMPOSITE FAN QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE BLADE DESIGN (QCSEE) WHIRL TEST OF CAM/HARMONIC PITCH May 1975 57 p CHANGE ACTUATION SYSTEM Contractor Report. 10 Nov. (Contract NAS3- 18021 1975 - 16 Feb, 1976 (NASA-CR- 134840; R75AEG278( Avail: NTIS Apr. 1976 208 p refs HC A04/MF AOl CSCL 21E (Contract NAS3-18O21( The design and analysis of a composite fan blade for the (NASA-CR- 135140, HSER-7002( Avail: NTIS under the wing IUTW( QCSEE is presented. The blade is designed HC A1O/MF AOl CSCL 21E for a variable pitch. 18 bladed rotor and is constructed from a A variable pitch fan actuation system. which incorporates a hybrid composite combination of materials consisting of Kevlar-49. remote nacelle mounted blade angle regulator. was tested: The type AS graphite, boron, and S-glass fibers in a PR288 epoxy regulator drives a rotating fan mounted mechanical actuator resin matrix. The blade has an attached platform which is through a flexible shaft and differential gear train. The actuator constructed of AS-graphite, PR278 epoxy resin matrix and incorporates a high ratio harmonic drive attached to a multitrack aluminum honeycomb The blade is designed to satisfy aerostability spherical cam which changes blade pitch through individual and cyclic life and strength requirements with a light weight cam follower arms attached to each blade trunnion Testing of construction. The attached platform is designed for a fail-safe the actuator on a whirl rig. is reported. Results of tests conducted condition in that it is retainable by the blade, under centrifugal to verify that the unit satisfied thd design requirements and force loading, even in the event of blade to platform bond was structurally adequate for use in an engine test are pre- separation. Details of the blade design and the results of stress, sented. J.M.S vibration, and impact analysis are included. ,J.M,S. N8015118*# General Electric Co., Cincinnati, Ohio N80- 151 14*# General Electric Co., Cincinnati. Ohio. Advanced QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE Engineering and Technology Programs Dept. (QCSEE) OVER-THE-WING (OTW) PROPULSION SYSTEMS QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE TEST REPORT. VOLUME 4: ACOUSTIC PERFORMANCE (QCSEE) OVER-THE-WING ENGINE AND CONTROL D. L. Stimpert Feb. 1979 144 p refs SIMULATION RESULTS (Contract NAS3- 18021) Oct. 1978 107 p refs NASA-CR- 135326, R77AEG476-Vol-4( Avail: NTIS (Contract NAS3-18021( HC AO7/MF AOl CSCL 21E (NASA-CR- 135049; R76AEG2 18) Avail. NTIS A series of acoustic tests were conducted on the over the HC A06/MF AOl CSCL 21E wing engine. These tests evaluated the fully suppressed noise A hybrid-computer simulation of the over the wing turbofan levels in forward and reverse thrust Operation and provided insight engine was constructed to develop the dynamic design of the into the component noise sources of the engine plus the control. This engine and control system includes a full authority suppression achieved by various components. System noise digital electronic control using compressor stator reset to achieve levels using the contract specified calculation procedure indicate fast thrust response and a modified Kalman filter to correct for that the in-flight noise level on a 152 m sideline at takeoff and sensor failures. Fast thrust response for powered-lift operations approach are 97.2 and 94.6 EPNdB. respectively, compared to and accurate. fast responding. steady state control of the engine a goal of 95.0 EPNdB. In reverse thrust, the system noise level is provided. Simulation results for throttle bursts from 62 to was 106.1 PNdB compared to a goal of 100 PNdB. Baseline 100 percent takeoff thrust predict that the engine will accelerate source noise levels agreed very well with pretest predictions. from 62 to 95 percent takeoff thrust in one second. J.M.S. Inlet-radiated noise suppression of 14 PNdB was demonstrated with the high throat Mach number inlet at 0.79 throat Mach number R.E.S. N80, 15115*# General Electric Co., Cincinnati, Ohio. Aircraft Engine Group. N80-151 19*# General Electric Co - Cincinnati, Ohio. Advanced QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE Engineering and Technology Programs Dept (QCSEE) BALL SPLINE PITCH-CHANGE MECHANISM QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE WHIRLIGIG TEST REPORT (QCSEE) U NDER-THE-WING (UTW) COMPOSITE NACE LLE Sep. 1978 64 p refs Final Design Report (Contract NAS3-18O21( E. A. Johnston Aug 1978 128 p (NASA-CR- 135354; R77AEG394( Avail; NTIS (Contract NAS3-18O21( HC A04/MF AOl CSCL 21E (NASA-CR- 135352; R77AEG588( Avail: NTIS The component testing of a ball spline variable pitch HC AO7/MF AOl CSCL 21E mechanism is described including a whirligig test. The variable The detail design of the under the wing experimental pitch actuator successfully completed all planned whirligig tests composite nacelle components is summarized. Analysis of an including a fifty cycle endurance test at actuation rates up to inlet, fan bypass duct doors, core cowl doors, and variable fan 125 deg per second at up to 102 percent fan speed nozzle are given. The required technology to meet propulsion (3400 rpm(. J.M.S. system performance, weight, and operational characteristics is discussed. The materials, design, and fabrication technology for N80-151 16*# General Electric Co.. Cincinnati, Ohio. Advanced quiet propulsion systems which will yield installed thrust to weight Engineering and Technology Programs Dept. ratios greater than 3.5 to 1 are described. R.C.T. QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE (QCSEE) UNDER-THE-WING (UTW) BOILER PLATE NACELLE AND CORE EXHAUST NOZZLE DESIGN RE- PORT Oct. 1976 104 p N80-151205 # General Electric Co., Cincinnati, Ohio. Aircraft (Contract NAS3-18O21( Engine Group. (NASA-CR- 135008; R76AEG222( Avail; NTIS QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE HC AO6/MF AOl CSCL 21E (QCSEE) Final Report

135 N80-15121

William S. Willis Aug. 1979 408 p refs N8O15124*// General Electric Co.. Cincinnati. Ohio. Advanced (Contract NAS3-18021) Engineering and Technology Programs Dept. (NASA-CR-i 59473; R79AEG478) Avail: NTIS QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE HC A18/MF AOl CSCL 21E (QCSEE). PRELIMINARY ANALYSES AND DESIGN The design, fabrication, and testing of two experimental REPORT. VOLUME 2 propulsion systems for powered lift transport aircraft are given. Oct. 1974 330 p The under the wing (UT'iN) engine was intended for installation (Contract NAS3- 18021 in an externally blown flap configuration and the over the wing (NASA-CR- 134839; R74AEG479-Vol-2( Avail: NTIS (OT\N( engine for use in an upper surface blowing aircraft. The HC A15/MF AOl CSCL 21E LJTW engine included variable pitch composite fan blades, main The experimental and flight propulsion systems are pre- reduction gear, composite fan frame and nacelle, and a digital sented. The following areas are discussed: engine core and low control system. The OTW engine included a fixed pitch fan, pressure turbine design; bearings and seals design; controls and composite fan frame, boilerplate nacelle, and a full authority accessories design: nacelle aerodynamic design: nacelle mechani- digital control. Many acoustic, pollution, performance, and weight cal design; weight: and aircraft systems design. R.E.S. goals were demonstrated. R.C.T. N8O15125*// General Electric Co.. Cincinnati. Ohio. Advanced N80.15121*// General Electric Co.. Cincinnati. Ohio. Advanced Engineering and Technology Programs Dept. Engineering and Technology Programs Dept. QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE (QCSEE) OVER-THE-WING (01W) PROPULSION SYSTEM (QCSEE). DOUBLE-ANNULAR CLEAN COMBUSTOR TEST REPORT. VOLUME 1: SUMMARY REPORT TECHNOLOGY DEVELOPMENT REPORT Jan. 1978 67 p 0. W Bahr. D. L. Burrus. and P. E. Sabla May 1979 . 149 p (Contract NAS3-18O21( refs (NASA-CR- 135323: R77AEG473-VoI . 1( Avail' NTIS (Contract NAS3- 18021( HC AO4/MF AOl CSCL 21E (NASA-CR- 159483: R79AEG397( Avail: NTIS Sea level, static, ground testing of the over-the-wing engine HC A07/MF AOl CSCL 21E and boilerplate nacelle components was performed. The equipment A sector combustor technology development program was tested and the test facility are described. Summaries of the conducted to define an advanced double annular dome combustor instrumentations, the chronological history of the tests, and the sized for use in the quiet clean short haul experimental engine test results are presented. R.E.S, (QCSEE( A design which meets the emission goals. and combustor performance goals of the QCSEE engine program was developed. N8O15126*// General Electric Co., Cincinnati. Ohio. Advanced Key design features were identified which resulted, in substantial Engineering and Technology Programs Dept. reduction in carbon monoxide and unburned hydrocarbon emission QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE levels at ground idle operating conditions, in addition to very (QCSEE) OVER-THE WING (01W) PROPULSION SYSTEM low nitric oxide emission levels at high power operating conditions. TEST REPORT. VOLUME 3: MECHANICAL PERFOR- ACT. Their significant results are reported. MANCE Feb. 1978 121 p (Contract NAS3-18021( N8O15122*// General Electric Co. Cincinnati. Ohio. Aircraft (NASA-CR- 135325: A77AEG475-Vol-3( Avail. NTIS Engine Group. HC AO6/MF AOl CSCL 21E QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE The mechanical performance of the over-the-wing engine is (QCSEE); ACOUSTIC TREATMENT DEVELOPMENT AND described with emphasis on the advanced technology components. DESIGN The overall dynamic response of the engine was excellent,A.E,S. Art Clemons May 1979 353 p refs (Contract NAS3-18021( (NASA-CR- 135266: R76AEG379- 1( Avail: NTIS N8O15127*# National Aeronautics and Space Administration. HC A16/MF AOl CSCL 21E Lewis Research Center. Cleveland, Ohio Acoustic treatment designs for the quiet clean short-haul QUIET POWERED-LIFT PROPULSION experimental engines are defined, The procedures used in the 1979 426 p refs Conf held at Cleveland. Ohio. 14-15 Nov. development of each noise-source suppressor device are presented 1978 and discussed in detail. A complete description of all treatment (NASA-CP-2077; E-99O6( Avail' NTIS HC A19/MF AOl CSCL concepts considered and the test facilities utilized in obtaining 21E background data used iii treatment development are also Latest results of programs exploring new propulsion technol- described. Additional supporting investigations that are comple- ogy for powered-lift aircraft systems are presented Topics mentary to the treatment development work are presented The discussed include results from the 'quiet clean short-haul expected suppression results for each treatment configuration experimental engine' program and progress reports on the 'quiet are given in terms of delta SPL versus frequency and in terms short-haul research aircraft' and 'tilt-rotor research aircraft' of delta PNdB. R.E.S programs. In addition to-these NASA programs, the Air Force AMST YC 14 and YC 15 programs were reviewed, R,E.S.

N8O15123*// General Electric Co.. Cincinnati. Ohio Advanced N80- 15128*// National Aeronautics and Space Administration. Engineering and Technology Programs Dept. Lewis Research Center, Cleveland, Ohio QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE DIRECT INTEGRATION OF TRANSIENT ROTOR DYNAM- (QSCEE). PRELIMINARY ANALYSES AND DESIGN ICS REPORT. VOLUME 1 Albert F. Kascak Washington Jan. 1980 23 p refs Oct. 1974 372 p (NASA-TP-1 597; AVRADCOM-TR-79-42; E-1O1( Avail' NTIS (Contract NAS3-18021( HC A02/MF AOl CSCL 21E (NASA-CR- 134838: R74AEG479-Vol- 1( Avail: NTIS An implicit method was developed for integrating the HC A16/MF AOl CSCL 21E equations of motion for a lumped mass model of a rotor dynamics The experimental propulsion systems to be built and tested system. As an aside, a closed form solution to the short bearing in the 'quiet, clean, short-haul experimental engine' program are theory was also developed for a damper with arbitrary motion. presented. The flight propulsion systems are also presented. The The major conclusions are that the method is numerically stable following areas are discussed: acoustic design: emissions control: and that the computation time is proportional to the number of engine cycle and performance: fan aerodynamic design: variable- elements in the rotor dynamics model rather than to the cube pitch actuation systems: fan rotor mechanical design: fan frame of the number, This computer code allowed the simulation of a mechanical design; and reduction gear design. R.E.S. complex rotor bearing system experiencing nonlinear transient

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motion and displayed the vast amount of results in an easily N80-15134t# National Aeronautics and Space Administration. understood motion picture format - a 10 minute. 16 millimeter. Lewis Research Center. Cleveland, Ohio. color. sound motion picture supplement. An example problem AN ANALYTICAL AND EXPERIMENTAL STUDY OF A with 19 mass elements in the rotor dynamics model took SHORT S-SHAPED SUBSONIC DIFFUSER OF A SUPER- 0.7 second of central processing unit time per time step on an SONIC INLET IBM 360-67 computer in a time sharing mode. ACT. Harvey E. Neumann. Louis A. Povinelli, and Robert E. Coltrin 1980 14 p refs Presented at 18th Aerospace Sci. Meeting. Pasadena. Calif.. 14-16 Jan 1980; sponsored by AIAA N80- 151 29*# National Aeronautics and Space Administration. INASA-TM-8 1406; E-32O( Avail: NTIS HC A02/MF AOl CSCL Ames Research Center. Moffeit Field. Calif. 21E EVALUATION OF APPROXIMATE METHODS FOR THE A subscale HiMAT forebody and inlet was investigated over PREDICTION OF NOISE SHIELDING BY AIRFRAME a range of Mach numbers to 1.4. The inlet exhibited a transitory COMPONENTS separation within the diffuser but steady state data indicated Warren F. Ahtye and Geraldine McCuIIey (Inlormatics, Inc.. Palo reattachment at the diffuser exit. A finite difference procedure Alto. Calif.) Washington Jan. 1980 106 p refs for turbulent compressible flow in axisymmetric ducts was used )NA5A-TP-1004;A-6961) Avail: NTIS HC A06/MF AOl CSCL to successfully model the HiMAT duct flow. The analysis technique 21E was further used to estimate the initiation of separation and An evaluation of some approximate methods for the prediction delineate the steady and unsteady flow regimes in similar S-shaped of shielding of monochromatic sound and broadband noise by ducts. ACT. aircraft components is reported. Anechoic-chamber measurements of the shielding of a point source by various simple geometric N80. 15135# Boeing Aerospace Co.. Seattle. Wash. shapes were made and the measured values compared with those calculated by the superposition of asymptotic closed-form AN EXTENSION OF ENGINE WEIGHT ESTIMATION TECHNIQUES TO COMPUTE ENGINE PRODUCTION COST solutions for the shielding by a semi-infinite plane barrier. The Final Report shields used in the measurements consisted of rectangular plates. E. Onat and F. F. TolIe 31 Aug. 1979 38 refs a circular cylinder, and a rectangular plate attached to the cylinder p (Contract N62269-78-C-0286) to simulate a wing-body combination. The normalized frequency. (AD-A074454; NADC-78 103-60) defined as a product of the acoustic wave number and either Avail: NTIS HC A03/MF AOl CSCL 05/1 the plate width or cylinder diameter, ranged from 4.6 to 114. As a follow-on to previously developed engine weight Microphone traverses in front of the rectangular plates and estimation work, a preliminary design engine cost estimating cylinders generally showed a series of diffraction bands that code has been produced. The code relies on engine thermodynamic matched those predicted by the approximate methods, except characteristics and weight as computed by earlier developed codes for differences in the magnitudes of the attenuation minima which to select raw material types and quantities required to produce can be attributed to experimental inaccuracies. The shielding of wing-body combinations was predicted by modifications of the the engine. An existing Navy technique is then used to convert this data into engine cost. The code was used to predict the approximations used for rectangular and cylindrical shielding. cost of three existing engines; errors ranged form 1 to 8% of Although the approximations failed to predict diffraction patterns actual costs as reported to NADC. in certain regions, they did predict the average level of wing-body GRA shielding with an average deviation of less than 3 dB. M.M.M. N80-15136# Kentucky Univ., Lexington Dept. of Engineering Mechanics. N80.15132*# National Aeronautics and Space Administration. THERMO-MECHANICAL STRESS ANALYSIS OF AD- Lewis Research Center. Cleveland. Ohio. VANCED TURBINE BLADE COOLING CONFIGURATION COMPUTER SIMULATION OF ENGINE SYSTEMS Final Report. 1 May 1975 - 15 Jul. 1979 L. H. Fishback 1980 26 p refs Presented at the 18th F. J. Rizzo and D. J. Shippy Jul. 1974 68 p refs Aerospace Sci. Meeting. Pasadena. Calif.. 14-16 Jan. 1980; (Grant AF-AFOSR-2824-79; AF Proj. 2307) sponsored by AIAA IAD-A074O98. U KY-TAll 1-79-EM17, AFOSR-79-0953TR( (NASA-TM-79290; E-234) Avail. NTIS HC A03/MF AOl CSCL Avail: NTIS HC A04/MF AOl CSCL 20/11 21E A thermo-mechanical stress analysis capability, based on the The use of computerized simulations of the steady state Boundary Integral Equation Method (BIE) is developed and and transient performance of jet engines throughout the flight described. The capability is used to provide a thermoelastic analysis regime is discussed. In addition, installation effects on thrust of Stress in the vicinity of cooling holes in turbojet blades with and specific fuel consumption is accounted for as well as engine transpiration or film cooling. Details involved in the formulation. weight, dimensions and cost The availability throughout the numerical procedures, mathematical modelling, and data from government and industry of analytical methods for calculating solved problems are presented. GRA these quantities are pointed out. M M.M. N80-15137# TRW Equipment Labs.. Cleveland. Ohio. Materials N8O15133*// National Aeronautics and Space Administration Technology Dept. Lewis Research Center. Cleveland, Ohio. FRS COMPOSITES FOR ADVANCED GAS TURBINE IMPACT OF NEW INSTRUMENTATION ON ADVANCED ENGINE COMPONENTS Final Report TURBINE RESEARCH D. M, ESsock May 1979 46 p refs Robert 'iN. Graham Mar 1980 25 p refs Proposed for (Contract N62269 . 77-C-02l7; SF54592201) presentation at the 1980 Spring Ann. Meeting. New Orleans, (AD-A074287, ER-7969-F; NADC-77O1 5-30) Avail: NTIS 5-13 Mar. 1980; sponsored by ASME I-IC A03/MF AOl CSCL 20/5 (NASA-TM-793O1. E-25t) Avail: NTIS HC A02/MF AOl CSCL A number of FRS design concepts involve use of varying 21E volume fraction of fiber, varying fiber diameter, and cross-ply A description is presented of an orderly test program that construction, Key properties of Such composites were evaluated progresses from the simplest stationary geometry to the more to determine whether there ore any adverse effects. Based upon complex, three dimensional, rotating turbine stage. The instrumen- elevated temperature tensile. creep. and thermal fatigue testing. tation requirements for this evolution of testing are described equivalent mechanical properties are obtained if placement of The heat transfer instrumentation is emphasized. Recent plies is varied in a symmetrical Iayup. GRA progress made in devising new measurement techniques has greatly improved the development and confirmation of more accurate analytical methods for the prediction of turbine performance and heat transfer. However. there remain challenging N80- 151 38*# National Aeronautics and Space Administration. requirements for novel measurement techniques that could Ames Research Center, Moffett Field, Calif. advance the future research to be done in rotating blade rows EFFECTS OF PRIMARY ROTOR PARAMETERS ON FLAP- of turbomachines. M.M.M. PING DYNAMICS

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Robert T. N. Chen Jan. 1980 63 p refs potential for generalized application; (3) with the availability of (NASA-TP-1431; A-7777) Avail: NTIS HC A04/MF AOl CSCL more information from the data buss and the power of the O1A computational capability, the multi-variable design techniques The effects of flapping dynamics of four main rotor design are offering significant potential for improving system performance features that influence the agility, stability, and operational safety and reducing equipment complexity; and (4) there is a strong of helicopters are studied. The parameters include flapping hinge need for fundamental studies in functional architecture that can offset, flapping hinge restraint, pitch-flap coupling, and blade employ microprocessors and still retain standards that permit lock number. First, the flapping equations of motion are derived the application of emerging electronic technology without that explicitly contain the design parameters. The dynamic restructuring the total system. R.E.S. equations are then developJ for the tip-path plane, and the influence of individual and combined variations in the design N8O-15141// Advisory Group for Aerospace Research and parameters determined. The steady state flapping response is Development. Neuilly-Sur-Seine (France). examined with respect to control input and aircraft angular rate LOW COST AIRCRAFT FLUTTER CLEARANCE which leads to a feedforward control law for control decoupling Sep. 1979 110 p Papers presented at the 48th Meeting of through cross feed, and a feedback control law to decouple the the Structures and Mater. Panel. Williamsburg. Va., 4 Apr. steady state flapping response. The condition for achieving perfect 1979 decoupling of the flapping response due to aircraft pitch and )AGA R 0- CP- 278; ISBN -92-835-0245-0) Avail: NTIS roll rates without using feedback control is also found for the HC A06/MF AOl hover case. It is indicated that the frequency of the regressing An evaluation of the usage of low cost aircraft flutter clearance flapping mode of the rotor system can become low enough to procedures is presented. Some results occurring from such require consideration in the assessment of handling characteris- procedures (weight efficiency, safety. flight incidents. and overall tics. J.M.S. costs) were discussed relative to those from methods using advanced state of the art. The relative technological-financial position of the small light weight aircraft manufacturer was also Calspan Advanced Technology Center. Buffalo, N80-15139# discussed. N.Y. DESIGN CRITERIA FOR OPTIMAL FLIGHT CONTROL SYSTEMS Final Report. Jan. - Nov. 1978 K. S. Govindara, E. G. Rynaski. and A T Fam 7 Sep. 1979 95 p refs Prepared in cooperation with the State Univ. of New York at Buffalo N80-15142# Lockheed-Georgia Co., Marietta. (Contract N00014-78-C.0155) COMPARISON OF INTERNATIONAL FLUTTER REQUIRE- )AD-A074092: CALSPAN-6248-F- 1 ONR-CR-2 15-259-1 F) MENTS AND FLUTTER FREEDOM SUBSTANTIATION OF Avail: NTIS HC A05/MF AOl CSCL 01/3 LIGHT AIRCRAFT IN THE USA Discussed is the application of linear optimal control to the H. F. Hunter and G. E. Goodblood (FAA) In AGARD Low design of a multicontroller feedback system to satisfy aircraft Cost Aircraft Flutter Clearance Sep. 1979 10 p refs flying qualities criteria. The problem addressed is that of relating the performance index weighting matrices to the poles and zeros Avail: NTIS HC A06/MF AOl of the closed-loop transfer functions. Two sequential design A comparison of Current flutter specification requirements procedures, one computing the Riccati solution from a set of for light aircraft produced by NATO and other free-world countries linear equations and the other computing the closed-loop is presented as well as an overview of flutter substantiation eigenvectors. are presented that determine, at each step, the procedures presently used in the USA by the Federal Aviation pole-zero movements of the closed-loop transfer functions as Administration. Current flutter assessment procedures for light the weighting matrix on the states is varied for a given aircraft parallel very nearly those for transport-type aircraft. weighting matrix on the controls. The performance index matrix Significant deviations could occur because specific requirements constructed at each step to move the poles and zeros is added for follow-on flight verification are lacking. The lack of such to get a final performance index matrix that moves the open-loop requirements has not created a great problem. since certain poles and zeros to more desirable locations. A control system elements of the flight structure call for flight demonstration, in design example with the X . 22A V/STOL aircraft as the model. most cases. The body of data acquired may be something less and using the first sequential design procedures, is presented. than that derived for a transport program. The attempt is made. Two alternative design techniques are also presented. The first however. to acquire sufficient data to validate the analysis from is based upon the Riccati equation solution and the control a safety standpoint. M.M.M weighting matrix rather than on the weighting matrices on the states and control, and in the second design technique, the change in the pole-zero locations is determined under perturba- tions in the performance index matrices. GRA N80-15143# Beech Aircraft Corp., Wichita, Kans. Structural Dynamics Dept. THE STATE-OF-THE-ART OF FLUTTER SUBSTANTIATION PROCEDURES AMONG US GENERAL AVIATION MANU- N80-15140# Advisory Group for Aerospace Research and FACTURERS Development. Neuilly-Sur-Seine (France). E. H. Hooper In AGARD Low Cost Aircraft Flutter Clearance TECHNICAL EVALUATION REPORT ON THE 28TH GUID- Sep. 1979 19 p ref ANCE AND CONTROL PANEL SYMPOSIUM ON ADVANCES IN GUIDANCE AND CONTROL SYSTEMS USING DIGITAL Avail: NTIS HC AO6/MF AOl TECHNIQUES An overview is presented of the state of the art of flutter Morris A. Ostgaard (AFFDL. Wright-Patterson AFB. Ohio) Nov. substantiation procedures among U.S general aviation manufac- 1979 14 p Symp. held at Ottawa, 8-1 1 May 1979 turers to serve as a guide to the small plane designer in the (AGARD-AR- 148; ISBN-92-835- 13 14-X) Avail: NTIS prevention of flutter. aileron reversal. and wing divergence. The HC A02/MF AOl material presented relies upon (1) a statistical study of the A summary of the conclusions and recommendations resulting geometric, inertia, and elastic properties of those airplanes which from audience comments and participation and technical had experienced flutter in flight. and the methods used to eliminate assessment of the papers and the meeting is presented Some the flutter. (2) limited wind-tunnel tests conducted with semi-rigid of the conclusions are as follows: (1) there is a rapid emergence models. These were solid models of high rigidity with motion of digital processor application to guidance and control that controlled at the root by springs to simulate wing bending and represent integration opportunities heretofore unavailable in analog torsion. Springs at the control surface were used to simulate systems; (2) there appears to be a proliferation of microprocessor rotation; and (3) analytic studies based on the two dimensional device application and architectures that, by themselves. limit study of a representative section of an airfoil, M.M.M

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N80-15144# Deutsche Forschungs- und Versuchsanstalt fuer N80-15148# British Aerospace Aircraft Group. Weybridge Luft- und Raumfahrt. Goettingen (West Germany). (England). Weybridge-Bristol Div. AN EMPIRICAL APPROACH FOR CHECKING FLUTTER THE MINIMUM COST APPROACH TO FLUTTER CLEAR- STABILITY OF GLIDERS AND LIGHT AIRCRAFT ANCE F. Kiessling in AGARD Low Cost Aircraft Flutter Clearance B. W. Payne and R. E. J. Brazier in AGARD Low Cost Aircraft Sep. 1979 17 p refs Flutter Clearance Sep. 1979 11 p

Avail: NTIS HC A06/MF AOl Avail: NTIS HC AO6/MF AOl Data of flutter accidents and computations of gliders and Flutter prediction methods are assessed using criteria and light aircraft are presented, and the empirical rules of a simplified simple flutter analyses. The difference in cost of these alternative flutter investigation are applied. A procedure for checking the approaches is no longer great, and the better data. available flutter stability of small airplanes is proposed, which takes into from the flutter analysis. answer far more of the questions which account the varying levels of knowledge with conventional and arise when obtaining a flutter clearance. Current regulations. unconventional designs. M.M.M. although not making flutter calculations mandatory, do insist on ground and flight resonance testing. Data from a flutter analysis N80-15145# Office National d'Etudes et de Recherches can allow a substantial saving in flight test time It is concluded Aerospatiales. Paris (France). that flutter calculations provide the swiftest, surest and safest DYNAMIC IDENTIFICATION OF LIGHT AIRCRAFT STRUC- route to flutter clearance of the orthodox design and the only TURES AND THEIR FLUTTER CERTIFICATION route for the unorthodox. Author Gerard Piazzoli and Jean- Louis Meurzec in AGARD Low Cost refs In FRENCH; Aircraft Flutter Clearance Sep. 1979 19 p N80-15149# Advisory Group for Aerospace Research and ENGLISH summary Development, Neuilly-Sur-Seine (France). AERODYNAMIC CHARACTERISTICS OF CONTROLS Avail: NTIS HC A06/MF AOl Sep. 1979 510 p Presented at the Fluid Dyn. Panel Symp.. Within the framework of the general orientation of the Pozzuoli, Italy. 14-17 May 1979 treatment of the light aircraft structures, and with a view to (AGA R D- CP- 262. IS B N-9 2-835-0252-3) Avail: NTIS determining specifications for their aeroelastic certification, the HC A22/MF AOl following points are discussed: (1) application of fast identification The rapidly expanding flight envelopes of aircraft, the methods and of technological means to be implemented during growing applications of active control technology (ACT) and the the tests; (2) exploitation of flutter onset calculations, coupled associated development of control configured vehicles (CCV) are on the computer with the experimental data, making it possible. considered. Conventional and novel methods of control, prediction in most cases, to define in situ a remedy (such as a new mass methods, experimental data derived from wind tunnel and flight balance of the control surface) and to check its efficiency; measurements, and flight experience of ACT and CCV are included. 13) development of mixed methods, based on the theoretical definition of the participation of the control surfaces in the structural modes revealed by the test, with a view to palliating the possible orthogonally defects of the experimental modal basis N80- 151 50# Deutsche Forschungs- und Versuchsanstalt fuer on which the definitive flutter prediction calculations are Luft- und Raumfahrt, Brunswick (West Germany), Inst. for established; and (4) methods and techniques used during the Design Aerodynamics. aeroelastic flight test, carried Out in the particular cases where THEORETICAL AERODYNAMIC METHODS FOR ACTIVE flutter certification cannot be based only on the calculation file CONTROL DEVICES because of insufficient safety margins. M.M.M. Horst Koerner in AGARD Aerodyn. Characteristics of Controls Sep. 1979 28 p refs

Avail. NTIS HC A22/MF AOl N80- 151 46# Deutsche Forschungs- und Versuchsanstalt fuer The theoretical aerodynamic aspects of active control devices Luft- und Raumfahrt. Goettingen (West Germany) A SIMPLIFIED GROUND VIBRATION TEST PROCEDURE are surveyed. Various calculation methods for subsonic. transonic, FOR SAILPLANES AND LIGHT AIRCRAFT and supersonic attached flow are reviewed followed by comments on separated flow, Typical correlations between theoretical and N. Niedbal in AGARD Low Cost Aircraft Flutter Clearance experimental results for steady and unsteady characteristics of Sep 1979 11 p refs control are presented along with the shortcomings of the theoretical approaches and some recommendations for future Avail NTIS HC A06/MF AOl efforts J MS. A test procedure to obtain all characteristic modal data for an aeroelastic analysis is presented. It is shown that by taking into consideration the beam-like structural behaviour of such aircraft, and the comparatively small bandwidth of the design variables, substantial simplifications are possible when the N80-1 51 51# Royal Aircraft Establishment, Farnborough dynamic behavior of similar aircraft structures is known The (England). mechanical steering mechanism of the control surfaces causes A SURVEY OF EXPERIMENTAL DATA ON THE AERODY- high damping and nonlinear effects, which require a separate NAMICS OF CONTROLS. IN THE LIGHT OF FUTURE examination and analysis of the control surfaces. M.M M. NEEDS A. Jean Ross and H. H. B. M. Thomas in AGARD Aerodyn. N80-15147# Royal Aircraft Establishment. Farnborough Characteristics of Controls Sep. 1979 48 p refs (England). Structures Dept. A FLUTTER-SPEED FORMULA FOR WINGS OF HIGH Avail: NTIS HC A22/MF AOl ASPECT RATIO Control data for current aircraft are used to provide material LI. T Niblelt in AGARD Low Cost Aircraft Flutter Clearance for discussion. principally to describe trends and to highlight Sep. 1979 14 p refs gaps in knowledge. Both direct and indirect effects for a range of conventional and unconventional motivators are included. Avail: NTIS HC AO6/MF AOl Maximum control power at the extremes of the flight envelope Flutter-speed formulae for uriswept wings of high aspect is particularly emphasized, since that available at high angle of ratio and not carrying concentrated masses are derived. A high attack and high subsonic speed is likely to be the critical design aspect ratio wing was defined as one whose fundamental torsional case. The indirect and coupling effects are also more marked at frequency is well above its first overtone flexural frequency. high angle of attack and/or high control deflection, and are of Because of the comparative fewness of the factors governing importance in the control system design. Hinge moment the flutter of such wings, flutter-speed formulae aimed at giving characteristics are described. although experimental data published a lower bound for the flutter speed is of simple form. M.M.M. recently are sparse. Some thought is given to the means of

139 N80- 15152

generating required control powers for aircraft configurations made ments indicate that an aft-tail controller concept will be superior possible by Active Control Technology, and to the integration of to canard and tailless delta configurations. The latter configurations the motivators in the control system. J.M.S. suffer controllability limitations that compromise the ability to achieve design goals for maneuverability and efficient supersonic cruise. Thrust vectoring was explored as a means of improving N80-15152# McDonnell Aircraft Co.. St. Louis, Mo. maneuver load factor capability. R ES CORRELATION OF F-15 FLIGHT AND WIND TUNNEL TEST CONTROL EFFECTIVENESS J. W. Agnew and J. F. Mello In AGARD Aerodyn. Characteristics of Controls Sep. 1979 ii p refs N80-15155# Dornier-Werke G,m.b.H., Friedrichshafen (West Germariy(. Avail: NTIS HC A22/MF AOl WIND TUNNEL MEASUREMENTS AND ANALYSIS OF The F-i 5 aerodynamic configuration and control system SOME UNUSUAL CONTROL SURFACES ON TWO SWEPT development relied on data obtained in an extensive wind tunnel WING FIGHTER CONFIGURATIONS test program. Subsequently, a large body of flight test data was 0. Welte and S. Ehekircher In AGARO Aerodyn, Characteristics obtained. Control surface effectiveness characteristics were derived of Controls Sep. 1979 10 p from flight test data and were compared with the data obtained in the wind tunnel test program. Data correlations are available Avail NTIS HC A22/MF AOl for the ailerons, rudders, and stabilators. The latter surfaces are Force measurements were made in a low speed and in a deflected symmetrically for longitudinal control and are deflected high speed wind tunnel with a 1:20 scale. 35 deg swept wing differentially for roll control: Primary axis effectiveness is addressed fighter configuration model. Surfaces which are deflected for for each of these control surfaces. Significant secondary axis longitudinal trim are: horizontal tail, leading. and trailing-edge contributions (e.g.. yawing moments due to aileron dellection( flaps, a strake and a strake leading-edge flap. For lateral control are also addressed. In addition to the conventional control surfaces, the following surfaces are deflected: ailerons. tiperons, flaperons the longitudinal control effectiveness of the F- 15 movable inlet and a strake leading-edge flap. The main conclusions are: ramp is discussed. As a result of the excellent resistance to (1) trailing edge flaps are very useful to trim an unstable departure from controlled flight, the spin resistance and spin configuration and have minimum drag; (21 tiperons are very recovery characteristics of the F- 1 5. it was possible to flight effective means for roll-yaw control up to very high angles of test and to obtain control effectiveness data to 90 deg angle of attack; and (31 differentially deflected leading edge flaps and a attack at low speeds and to approximately 40 deg at transonic vortex fin, positioned on the wing upper surface, decrease the speeds. Thus, the correlation of control effectiveness is addressed directional instability at high angles of attack. In addition, low for a large range of conditions. J.M.S. speed tests were made with a new wing concept for a future fighter configuration, so called supersonic biplane. to investigate the effectiveness of the upper- and lower-wing trailing edge N80-15153# Royal Aircraft Establishment. Farnborough flaps. As supplement to the wind tunnel measurements some (Englandl. flight mechanical maneuver calculations were made to check SOME WIND TUNNEL MEASUREMENTS OF THE EFFEC- the suitability and to compare the effectiveness of the different TIVENESS AT LOW SPEEDS OF COMBINED LIFT AND controls. ROLL CONTROLS R E S D. S. Woodward, R. F. A. Keating, and C. S. Barnes In AGARD N80- 151 56# Aerodyn. Characteristics of Controls Sep. 1979 36 refs Deutsche Forschungs- und Versuchsanstalt fuer p Luft- und Raumfahrt. Brunswick (West Germany(. Avail: NTIS HC A22/MF AOl ROLL CONTROL BY DIGITALLY CONTROLLED SEGMENT SPOILERS Using a half-model technique, measurements were made, at low speeds, of the effectiveness of spoilers for direct lift or roll Klaus Jonas (Dornier-Werke G.m.b.H,(, Horst Wuennenberg (Dornier-Werke G.m,b,H,(, and Karl-Heinz Horstmann control, with high lift devices deployed. The wing planform was In AGARD Aerodyn. Characteristics of Controls Sep. 1979 8 representative of that of a transport aircraft outboard of the p refs trailing edge crank. Results are presented which show that Avail: NTIS HC A22/MF AOl appropriate venting beneath the leading edge of hinged plate spoilers, together with venting through the flap shroud, achieved To realize total wing span flaps for improving the maneuvering acceptably linear spoiler characteristics. Similarly. linear character- and landing performances of a combat aircraft the roll control istics were obtained for a vented spoiler formed by moving the has to be realized by spoilers. To overcome the nonlinearity and rear of the flap shroud. No reversal of spoiler effectiveness was control reversal problems at low deflections, the continuously found at any test condition within the normal operating range deflected spoiler is replaced by a certain set of digitally controlled of incidence. In the same way, measurements were made of single spoilers, which provide only three discrete deflections. It the maximum lift and roll performance of a typical swing wing was found by simulator tests that by a proper combination of fighter aircraft, for which the design of the leading and trailing these segment spoilers it is possible to provide a roll control, edge controls was totally determined by the need to maximize which is judged as Continuous by the pilot, with a relatively low the maneuverability at high speed. The maximum lift performance number of single spoilers. Wind tunnel programs were performed is compared with that obtainable from conventional slate and to investigate system efficiency and aerodynamic effectiveness. slotted flaps. Somewhat surprisingly, it is found that adequate Several roll spoiler configurations were tested in two and three rolling moments can be obtained by using full-span plain flaps dimensional configurations with and without landing flaps at different spanwise positions. spoiler deflections and -spans. It is differentially about a basic drooped position of 30 deg. J.M.S, shown that the effectiveness related to the deflection is linear for flaps-up and highly nonlinear for flaps-down configurations. The spoiler span is of no more influence at a certain value and N80-15154# Boeing Military Airplane Development. Seattle. the Optimum spanwise location is about 0.8 of the semispan. Wash. Flight Control Technology. Furthermore the effectiveness and the influence on lift and pitching FLIGHT CONTROL AND CONFIGURATION DESIGN moment for a possible test aircraft are shown. The practical CONSIDERATIONS FOR HIGHLY MANEUVERABLE application within an intended flight test program is discussed. AIRCRAFT R.E.S. William T. Kehrer In AGARD Aerodyn. Characteristics of Controls N8O-15157# Sep 1979 lip Boeing Aerospace Co., Seattle. Wash. Avail NTIS HC A22/MF AOl THE YC-14 UPPER SURFACE BLOWN FLAP: A UNIQUE CONTROL SURFACE Working within wing geometry and other design constraints. Alan H. Lee In the controllable limits of instability and the maneuver capabilities AGARD Aerodyn. Characteristics of Controls Sep. 1979 8 p refs of various design approaches were investigated. Preliminary studies conducted to evaluate competitive configuration arrange- Avail: NTIS HC A22/MF AOl

140 N80- 151 64

The application of powered-lift technology applied to the without sacrificing roll performance and to avoid deep stall trim. Boeing YC-14 is assessed. The YC-14 can be controlled during For situations where the high angle of attack pitch control short takeoff landings using conventional pilot techniques. That requirement is not met, control laws were ,developed to inhibit capability stems from the use of its upper surface blown )(JSB} the departure and to allow deep stall recovery. However, these flaps as control surfaces. The USB flaps are used to help control schemes involve limiting airplane roll capability and therefore aircraft lift and airspeed. They are positioned automatically by can potentially compromise maneuverability. M.M.M. the flight control system to eliminate undesired lift changes caused by thrust changes or external disturbances and to work with N80-15161# British Aerospace Aircraft Group. Brough (England). the autothrottle to attain and hold a selected airspeed. The FIN DESIGN WITH ACT IN THE PRESENCE OF STRAKES aerodynamic and physical characteristics of USB flaps are 0. J. Walker In AGARD Aerodyn Characteristics of Controls described. R.E.S. Sep. 1979 6 p Avail: NTIS HC A22/MF AOl N80-15158# Northrop Corp.. Los Angeles, Calif. Wind tunnel tests on a combat aircraft model are reported FLAPERON CONTROL: THE VERSATILE SURFACE FOR in which the effect of fin size and various types of fin controls FIGHTER AIRCRAFT were investigated, It was shown that a rudder Irather than an John F. Moynes and Wallace E. Nelson. Jr. In AGARD Aerodyn. all moving fin) using active control technology is probably the Characteristics of Controls Sep. 1979 18 p refs best solution for incidences of up to about 50 deg. Also the use of such a system would allow a 20% reduction in the size Avail: NTIS HC A22/MF AOl of the basic fin. M.M.M. The versatility of a flaperon .is presented for roll performance and for several longitudinal active control .modes. Particular emphasis is given to the advantages of a segmented flaperon N8O-15162# McDonnell Aircraft Co.. St. Louis. Mo. over a full span for a YF- 17 type aircraft. The areas of ride CONTROL INTEGRATION TECHNOLOGY IMPACT smoothing, direct lift, pitch pointing, vertical flight path control Charles A. Scolatti In AGARD Aerodyn. Characteristics of Controls and flight control system reconfiguration are addressed for the Sep. 1979 6 p refs active longitudinal control modes. The effect of flaperon pitching moment on the implementation of these modes is Avail: NTIS HC A22/MF AOl discussed. Author Some of the essential elements of an integrated technology development program are presented. The integrated flight and N80-15159# Air Force Flight Dynamics Lab.. Wright-Patterson fire control system programs, called IFFC I/FIREFLY Ill, is used AFB. Ohio. as an example. The operational relevance of the example is AFFOL EXPERIENCE IN ACTIVE CONTROL TECHNOLOGY discussed. The major problems in air-to-ground attack, and the Robert P. Johannes and Robert A. Whitmoyer In AGARD introduction of maneuvering weapon delivery (with IFFC mechani- Aerodyn. Characteristics of Controls Sep. 1979 20 p refs zation required to achieve bombing solutions), are covered. The impact of this IFFC technology, and its extension on other areas Avail: NTIS HC A22/MF AOl of technology, such as aerodynamics, is indicated. M.M.M. The evolution of active control technology (ACT) from the viewpoint of the Air Force Flight Dynamics Laboratory (AFFDL) N80- 151 63# Dornier-Werke G.m.b. H., Friedrichshafen IWest is presented. Emphasis is placed on the aerodynamic control Germany). forces necessary to exploit ACT and in describing A FFD L DIRECT SIDE FORCE AND DRAG CONTROL WITH THE development programs which merge these two disciplines and AID OF PYLON SPLIT FLAPS transition technology into operational flight equipment. Specific Peter Each and Horst Wuennenberg In AGARD Aerodyn. ACT programs described are: (1) the LAMS program: (2) the Characteristics of Controls Sep. 1979 9 refs CCV B-52 program: 13) the SFCS F-4 program: 141 the CCV/PACT p F-4 programs; (5) the Variable Stability NT-33 program: 161 the Avail: NTIS HC A22JMF AOl CCV YF-16 program; 171 the A-7D Digital Multimode program; Two configurations of split flaps are examined. a long one 18) the IFFC I/FIREFLY Ill program; and (9) the AFTI-16 program. with small deflections and a short one with large deflections. Experiences indicating areas of need for extension of fluid dynamics The short one led to the same effectiveness at reduced values M.M.M. technology are also discussed. of hinge moments and cross coupling effects. Due to high interference effects it was not possible to get the effects of all flaps by superposition of the single flap results. The angle of N8O1516O*# National Aeronautics and Space Administration. attack. the landing flap setting and the lateral projection area of Langley Research Center, Hampton. Va the external stores have a significant influence on the effective- CONTROL CONSIDERATIONS FOR CCV FIGHTERS AT ness whereas the Mach number is less important. The examination HIGH ANGLES OF ATTACK of the wind tunnel results led to the necessary control laws for the operation of the flaps and the compensation equipment. Luat T. Nguyen. William P. Gilbert. and Sue B. Grafton In AGARD Aerodyn. Characteristics of Controls Sep. 1979 10 p The flight test program with an Alpha Jet preproduction aircraft ref is expected to start in 1980. M.M.M. Avail: NTIS HC A22/MF AOl CSCL O1C Wind tunnel and piloted simulation studies were conducted to investigate the potential high angle of attack control problems N8O15164*# National Aeronautics and Space Administration. that are introduced by the use of the CCV concept of relaxed Ames Research Center. Moffett Field, Calif. static pitch stability IRSS) on fighter aircraft. A conventional CONTROL OF FOREBODY THREE-DIMENSIONAL FLOW wing/aft tail design incorporating modest levels of static SEPARATIONS instability and a close-coupled canard/wing design exhibiting very David J. Peake and F. Kevin Owen (Owen Intern., Inc.. Palo high levels of instability was investigated. Two types of high Alto. Calif.) In AGARD Aerodyn. Characteristics of Controls angle of attack control problems can result from the use of Sep. 1979 49 p refs RSS: pitch departures caused by coupling and deep stall trim. Avoidance of these problems requires that the airplane have Avail' NTIS HC A22/MF AOl CSCL O1C sufficient nose-down pitch control at high angles of attack. The The development of the turbulent symmetric and asymmetric effectiveness of several pitch control configurations were vortex flow about the lee side of a 5 deg semiangle conical investigated including conventional aft-mounted stabilators. forebody at high relative incidence was investigated. The cone wing-mounted elevators, canard-mounted flaps, and all-moveable was immersed in a Mach 0.6 airstream at a Reynolds number canards. Varying the incidence of the canards was the most of 13.5 x 10 to the 6th power based on the 1.4 m axial length effective scheme; however, very large deflections may be required of the cone. Small amounts of air injected normally or tangentially on highly unstable configurations to prevent pitch departure to the cone surface, but on one side of the leeward meridian

141 N80-1 5165

and beneath the vortex farthest from the wall, were effective in [EFFETS INSTATIONNAIRES DUNE GOUVERNE EN biasing the asymmetry. With this reorientation of the forebody ECOULEMENT BIDIMENSIONNEL SUBSONIQUE ET vortices, the amplitude of the side force could be reduced to TRANSSONIQUE] the point where its direction was reversed. This phenomenon Richard Grenon. Andre Desopper, and Jacques Sides In AGARD was obtained either by changing the blowing rate at constant Aerodyn. Characteristics of Controls Sep. 1979 14 p refs In incidence or by changing incidence at constant blowing rate. FRENCH: ENGLISH summary Normal injection appeared more effective than tangential injection. The contrarotating vortices in the penetrating jet flow were of Avail; NTIS NC A22/MF AOl opposite hand to the rotational directions of the forebody The unsteady effects of an oscillating surface are studied. vortices. A distinctively organized and stable flow structure The experimental results of steady and unsteady pressure emerged with the jet vortices positioned above the forebody measurements carried out fl subsonic and transonic flow on a vortices. K.L. 16% relative thickness supercritical airfoil, equipped with a trailing edge flap, are compared with those obtained by various methods N80-15165# Deutsche Forschungs- und Versuchsanstalt fuer of steady and unsteady inviscid flow calculations. Calculation Luft- und Raumfahrt. Brunswick (West Germany). results are presented in which viscous effects have been taken IN-FLIGHT MEASURED CHARACTERISTICS OF COM- into account, for both steady and unsteady flows. K.L. BINED FLAP-SPOILER DIRECT LIFT CONTROLS 0. Rix and D. Hanke In AGARD Aerodyn. characteristics of N80- 151 69# Royal Aircraft Establishment, Bedford (England). Controls Sep. 1979 22 p refs Structures Dept. AERODYNAMIC CHARACTERISTICS OF MOVING TRAIL- Avail: NTIS NC A22/MF AOl ING-EDGE CONTROLS AT SUBSONIC AND TRANSONIC The influence of direct lift control on longitudinal aircraft SPEEDS dynamics and the requirements for the characteristics of direct D G. Mabey, 0. M. McOwat, and B. L. Welsh In AGARD lift controls for large transport aircraft in the landing approach Aerodyn. Characteristics of Controls Sep. 1979 26 p refs phase are discussed. The characteristics of flaps, spoilers, and the influence of surface rate on aircraft behavior are also described. Avail. NTIS HC A22/MF AOl Flight tests were carried Out with the DFVLR HFB 320 lnFIight Oscillatory pressures calculated and measured at high Simulator to determine in-flight flap and spoiler characteristics subsonic speeds for a swept back wing of aspect ratio 6 with a and the characteristics of simultaneously deflected flaps and part span trailing edge flap were compared. The flap was driven spoilers as L)LC device. The results show that flap and spoiler at frequencies of 1 Hz (quasi-steady) and 90 Hz at Mach characteristics can be described by linear models for flap and numbers from 0.40 to 0.95 with both fixed and free transition spoiler inputs up to + or - 10 deg and + or - 30 deg. over a range of Reynolds numbers from 1 million to 4 million. respectively, and relatively high surface rates of 10 deg/sec and The measured oscillatory pressures depended strongly on the 62 deg/sec. In addition, combined flap-spoiler deflections show boundary layer displacement thickness at the hinge line. no nonlinear or unsteady effects and the aircraft response is Extrapolation from model to full scale required great care. In described by simple linear modelling. The spoiler derivatives valid subsonic flow, tests with free transition gave the thinnest turbulent for combined flap-spoiler deflections are identified. K.L. boundary layer at the hinge line and come nearest to full scale. At transonic speeds, transition was fixed at a safe distance upstream of the most forward excursion of the shock wave to N80-1 5166# Messerschmitt-Boelkow-Blohm G.m.b.H., Munich obtain results appropriate to higher Reynolds number. Tests with (West Germany). flap driven simultaneously at two frequencies (90 Hz and WIND TUNNEL INVESTIGATION OF CONTROLS FOR DF 131 Hz( at subsonic and transonic speeds produced the same ON A FIGHTER-TYPE CONFIGURATION OF HIGHER oscillatory pressures at 131 Hz as when driven independently. ANGLES OF ATTACK The principle of superposition applies, at least for small amplitude Wolfgang Sonnleitner In AGARD Aerodyn. Characteristics of motions with attached flows R.C.T. Controls Sep. 1979 11 p refs

Avail; NTIS HC A22/MF AOl N80-15170# Queen Mary CoIl., London (England). Dept. of Stability and control characteristics of a fighter-type model Aeronautical Engineering. were investigated at incidences up to 40 deg. Isolated and UNSTEADY AERODYNAMICS OF TWO-DIMENSIONAL combined effects of different control shapes and control in different SPOILERS AT LOW SPEEDS positions were demonstrated. K.L. S. R. Siddalingappa and G. J. Hancock In AGARD Aerodynam. Characteristics of Controls Sep. 1979 13 p refs N80-15167// Office National d'Etudes et de Recherches Aerospatiales, Paris (France). Avail; NTIS HC A22/MF AOl PROBLEMS OF UNSTEADY AERODYNAMICS RAISED BY Complementary aspects of spoiler behavior are reviewed. The emphasis is on the understanding of the local flow about a THE USE OF CONTROL SURFACES AS ACTIVE CONTROLS [PROBLEMES DAERODYNAMIQUE INSTATIONNAIRE spoiler. A two dimensional spoiler on the floor of a small blower POSES PAR LUTILISATION DES GOUVERNES DANS LE tunnel (solid floor, and side walls but open at the top) was CONTROLE ACTIF] investigated. Steady pressures were measured along the tunnel floor for various steady spoiler angles and gap sizes between Roger Destuynder In AGARD Aerodyn. Characteristics of Controls the bottom of the spoiler and the tunnel floor. Transient pressures Sep. 1979 17 p refs In FRENCH; ENGLISH summary were recorded following sudden changes in spoiler angle and Avail; NTIS HC A22/MF AOl for oscillating spoilers. A two dimensional spoiler attached to a The unsteady aerodynamic forces created by spoilers or two dimensional airfoil was investigated, The manner in which auxiliary surfaces are investigated. Control problems concerning the spoiler affects the overall pressure distribution on the airfoil turbulence, gust control, and flutter phenomena are studied plus spoiler combination was emphasized. Both the airfoil and considering both subcritical and supercritical flows. Theoretical the spoiler were pressure plotted. The results of steady pressures. and mixed methods based on corrections defined after wind transient pressures following rapid and slower ramp changes in spoiler angle, and transient pressures when the spoiler is moving tunnel tests are applied. K.L. in simple harmonic motion are included. . ACT.

N80-15171# Rome Univ. (Italy). School of Aerospace N80-15168# Office National d'Etudes et de Recherches Engineering. Aerospatiales. Paris (France). TRAJECTORY BEHAVIOUR OF A CONTROL CONFIG- UNSTEADY EFFECTS OF A CONTROL SURFACE IN TWO URATED AIRCRAFT SUBJECTED TO RANDOM DISTUR- DIMENSIONAL SUBSONIC AND TRANSONIC FLOW BANCES

142 N80-15178

Achille Danesi, Scott Smolka (Boston Univ.). and Francesco Borrini N80-15174# Ruhr Univ., Bochum (West Germany). In AGARD Aerodyn. Characteristics of Controls Sep. 1979 ON THE EFFECT OF WING WAKE ON TAIL CHARACTERIS- 17 p rets TICS Avail: NTIS HC A22/MF AOl K. Gersten and 0. Glueck I,, AGARD Aerodyn. Characteristics The longitudinal behavior of a Boeing V-747 aircraft with of Controls Sep. 1979 8 p rets some of its original aerodynamic etfectors operating as active controllers in addition to the conventional elevators were studied. Avail: NTIS HC A22/MF AOl The ailerons were collectively used as outboard active flaps and A nonlinear theory was developed to calculate lift and moment the inboard section of the high lift triple slotted flaps was employed forces for airfoils in a two dimensional flow field. The oncoming as inboard active flaps. The flight control system structure was velocity distribution is approximated by a series of step functions implemented as an optimal model following system in which which results in a flow field composed of a number of potential the optimal feedback gains were computed to minimize the integral flow fields. The potential flow fields are matched properly at performance index. Errors in dynamical response, in wing root several dividing streamlines where the total pressure changes bending moment, and in aerodynamic drag computed as deviations discontinuously. The solution of the problem is determined by from the same quantities related to a specified model responding using vortex distributions on both the contour of the airfoil and satisfactorily to disturbances with zero increments in wing root the dividing streamlines. A special approach makes it possible bending moment and aerodynamic drag in flight maneuver at to calculate the flow field when one of the dividing streamlines given load factor, were considered. At the same time the minimum merges with the profile. A comparison between theoretical and effectors activity was included as a design objective. A lighter experimental results for the aerodynamic characteristics of a tail wing structure was realized as the result of wing loads reduction unit placed in the wake of a wing is presented. A prediction and further weight saving )reduced tail size) was obtained by method for the tail characteristics at high angles of attack (super taking advantage of the beneficial effect of the active controller stall) is discussed. A.W.H. activity in reducing the elevator deflections required in the pull up maneuver. R.C.T. N80-15175# Office National dEtudes et de Recherches Aerospatiales. Paris (France). AERODYNAMIC INTERACTION ON A CLOSE-COUPLED N80-15172# Northrop Corp., Hawthorne. Calif. Aircraft CANARD WING CONFIGURATION [INTERACTION Group AERODYNAMIQUE ENTRE UN CANARD PROCHE ET UNE FOREBODY VORTEX BLOWING: A NOVEL CONTROL VOILUREJ CONCEPT TO ENHANCE DEPARTURE/SPIN RECOVERY Yves Brocard and Volker Schmitt In AGARO Aerodyn. CHARACTERISTICS OF FIGHTER AND TRAINER AIR. Characteristics of Controls Sep. 1979 11 p refs In FRENCH: CRAFT ENGLISH summary Andrew M. Skow, William A. Moore, and Dale J. Lorincz In AGARD Aerodyn. Characteristics of Controls Sep. 1979 17 p Avail: NTIS HC A22/MF AOl refs Half model tests performed on a close coupled canard wing Avail NTIS HC A22/MF AOl configuration in a low speed, pressurized wind tunnel are Active blowing concepts which control the asymmetric discussed. Results are presented in terms of longitudinal orientation of the vortex system emanating from an aircraft aerodynamic characteristics and pressure distribution on the main forebody at high angles of attack are described. The side force wing. 'The effects of canard deflection and of Reynolds number generated by the asymmetric nature of the vortices was utilized. variation are investigated. Surface oil flow pattern on the wind The choice between these two preferred positions was influ- tunnel model and water tunnel visualization on a smaller model enced strongly by very small geometric imperfections in an are examined. Comparisons between the experimental results otherwise symmetric model and by small asymmetries in the and theoretical predictions are presented. A.W.H. upsteam flow such as are caused by flow angularity or turbulent eddies in the free stream. The magnitude of the side force was NBO-15176# Queen Mary CoIl.. London (England). Dept. of very large due to the fluid amplification afforded by the vortex Aeronautical Engineering. growth. The results of water tunnel flow visualization studies ON THE EFFECTS OF GAPS ON CONTROL SURFACE and a wind tunnel test program are presented which bear Out CHARACTERISTICS this assumption and show that tangential blowing can effectively C. Michael and G. J. Hancock In AGARD Aerodyn Characteristics alter the forebody vortex system at angles of attack between of Controls Sep. 1979 13 p ref 25 and 55 deg. and can generate yawing moments comparable to those produced by a conventional rudder at low angles of Avail: NTIS HC A22/MF AOl attack. The results of a six deg of freedom digital simulation A two dimensional airfoil comprising an elliptic nose, parallel are presented which show that this concept can substantially section of 5% t/c ratio, and a 20% trailing edge control surface enhance departure recovery characteristics and could have was investigated at low speeds. Three different geometries of potential as a departure inhibitor for some aircraft. The results the rear of the main airfoil were investigated Gaps were created of a preliminary system design indicate that such a system could by moving the control surface aft of the main airfoil. Extensive be applied to aircraft. R.C.T. pressure plotting is presented for the above range of gaps and control surface angular deflections up to 8 degrees and a range of measurements of mean boundary layer profiles in the N80-15113# Neilsen Engineering and Research, Inc.. Mountain View, Calif. neighborhood of the gap are discussed, The variations of the NONLINEAR AERODYNAMICS OF ALL-MOVABLE CON- overall lift coefficient with control angle and gap size for the TROLS three geometries are reported. A.W.H. Charles A. Smith and Jack N. Nielsen In AGARD Aerodyn. Characteristics of Controls Sep. 1979 20 p refs

(Contract N00014-74-C-0050) N80- 151 18# Messerschmitt-Boelkow-Blohm G,m.b H., Hamburg Avail: NTIS HC A22/MF AOl (West Germany). Commercial Aircraft Div. The nonlinear effects and their consequences on control SOME INVESTIGATIONS CONCERNING THE EFFECTS OF effectiveness are described. Both independent control effectiveness GAPS AND VORTEX GENERATORS ON ELEVATOR (e.g.. pitch control) as well as control cross coupling (e.g.. pitch EFFICIENCY AND OF LANDING FLAP SWEEP ON AERODY- control in the presence of yaw control) are discussed. It is shown NAMIC CHARACTERISTICS that, at sufficiently high angles of attack, the presence of these Herbert Neppert and Richard Sanderson In AGARD Aerodyn. nonlinearities can completely dominate control effectiveness. The Characteristics of Controls Sep. 1979 12 p refs current status of techniques to predict control effects using both analytical and data correlation techniques are reviewed R.C.T. Avail NTIS HC A22/MF AOl

143 N80- 15179

The effect of gaps and vortex generators on elevator and a combination suction/axial aerowindow are examined. The effectiveness and drag is exam,ined. The effect of single rudder combination suction/axial aerowindow is recommended due to deflection on the effectiveness of a split rudder is discussed. the estimated leakage rate and the projected cost. DOE Wind tunnel results and proposals for improving the aerodynamic characteristics of a tailplane by means of a reduction in the sweep on the landing flap hinge line are described. A.W.H. N80-15183# General Applied Science Labs.. Inc.. Westbury, N. V. N80-15179 t fl National Aeronautics and Space Administration. CONCEPTUAL DESIGN AND PERFORMANCE ESTIMATES John F. Kennedy Space Center. Cocoa Beach. Fla. FOR A SUPERSONIC AERODYNAMIC WINDOW FOR THE LOX/GOX MECHANICAL IMPACT TESTER ASSESSMENT ATA VACUUM SYSTEM APERTURE Final Report J. W. Bransford (NASA. Marshall Space Flight Center), C J. J. I. Erdos Jun. 1979 39 p refs Bryan. G. W. Frye (NASA. Johnson Space Center). and S. L. (Contract W-7405-eng-481 Stohler (Rocketdyne. Canoga Park. Calif.) Feb. 1980 103 p (UCRL-15051l Avail: NTIS HC A03/MF AOl refs The design of an aerodynamic window for the aperture in a (NASA-TM-74106( Avail: NTIS HC A06/MF AOl CSCL system of interconnecting cavities is discussed. Two types of 14B windows are considered and evaluated for the system. They are The performances of three existing high pressure oxygen a supersonic let operating transverse to the aperture 'axis and a mechanical impact test systems were tested at two different supersonic jet operating coaxially about the aperture. A.W.H. test sites. The systems from one test site were fabricated from the same design draving. whereas the system tested at the other site was of different design. Energy delivered to the test sample for each test system was evaluated and compared. Results N80-15265# Southwest Research Inst , San Antonio. Tex Army were compared to the reaction rates obtained. R.C.T. Fuels and Lubricants Research Lab THE PHYSICAL AND CHEMICAL CHARACTERIZATION OF TEN MILITARY TURBINE ENGINE LUBRICANTS Final N80-15180# Air Force Human Resources Lab,. Brooks AFB. Report. Jul. - Sep. 1979 Tex. Frank M. Newman and Leo L. Stavinoha Sep. 1979 32 p EFFECTS OF VARYING VISUAL DISPLAY CHARACTERIS- refs TICS OF THE T-4G, A T-37 FLIGHT SIMULATOR Final (Contract DAAK7O-79-C-0142( Report. Aug. 1974 - Dec. 1977 (AD-AO74073: AFLRL-1 15) Avail: NTIS HC A03/MF AOl Robert R. Woodruff Jun. 1979 17 p refs CSCL 11/8 (AF Proj. 1123) Four MIL-L-23699B and six MIL-L-78O8G turbine engine (AD-A07 1410: AFHRL-TR-79- 17) Avail: NTIS lubricants have been characterized from the physical properties HC A02/MF AOl CSCL 05/9 and chemical composition of their basestocks. The four MIL-L- Two experiments were conducted using the T-4G. a 23699 lubricants were found to be 100% polyol esters. Of the T-37 flight simulator, to investigate the benefit to simulation of six MIL-L-78O8 lubricants, four were mixtures of polyol esters visual displays which have color or are collimated. Thirty-two and diesters. one was 100% polyol ester. and one was 100% Air Force undergraduate pilots learned approach and landing in diester. Correlation of the chemical data is made to some of the T-4G using either black and white or colored imagery. the physical properties wherever possible. GRA Thirty-eight instructor pilots performed approach and landing with visual displays that had collimation or reduced collimation. No statistically significant differences were found in either experiment. Power analysis shows that each of these experiments N8O15299*# Old Dominion Univ. Research Foundation. Norfolk. Va. would have detected a practically significant difference, if one existed, with a probability of more than .75. There are no SOIL ANALYSES AND EVALUATIONS AT THE IMPACT psychophysical reasons to use either color or collimation. User DYNAMICS RESEARCH FACILITY FOR TWO FULL-SCALE acceptance is another thing, and if color and collimation improve AIRCRAFT CRASH TESTS Final Report. 24 May - 31 Aug. 1977 acceptance, they should be used. GRA Robert V. K. Cheng Dec. 1977 36 p refs (Contract NAS1-14193( N80-15181# Army Test and Evaluation Command, Aberdeen (NASA-CR-159199( Avail: NTIS HC AO3/MF AOl CSCL Proving Ground, Md. 08M CLIMATIC CHAMBER TESTING AIRCRAFT. ENGINES The aircraft structural crash behavior and occupant survivabil- ARMAMENT AND AVIONICS; TEST OPERATIONS PRO- ity for aircraft crashes on a soil surface was studied. The results CEDURE Final Report of placement, compaction, and maintenance of two soil test 31 Aug. 1979 35 p Supersedes MTP-7-3-521 beds are presented. The crators formed by the aircraft after (AD-A074049: TOP-7-3-521: MTP-7-3-521( Avail: NTIS each test are described. J.M.S. HC A03/MF AOl CSCL 01/3 This document provides information, guidance and methodol- ogy for planning and conducting an environmental climatic chamber developmental test of aviation materiel. Environmental N8O15364*# National Aeronautics and Space Administration. climatic chamber developmental testing in general, determines Lewis Research Center, Cleveland. Ohio, the degree to which aviation materiel meets the developmental COMPUTATION OF THREE-DIMENSIONAL FLOW IN requirements of the US Army Materiel Needs (MN) documents. TURBOFAN MIXERS AND COMPARISON WITH EXPERI- when subjected to the environmental conditions developed in MENTAL DATA the climatic chamber. GRA L. A. Povinelli. B. H. Anderson. and W. Gerstenmaier Jan. 1980 12 p refs Presented at the AIAA Aerospace Sciences Meeting. Pasadena. Calif.. 14-16 Jan. 1980 (NASA-TM-8 1410: E-324) Avail' NTIS NC A02/MF AOl CSCL N80-15182# Avco-Everett Research Lab.. Mass. 20D DESIGN STUDY FOR ATA VACUUM SYSTEM APERTURE A three dimensional, viscous computer code was used to S. Hibbs 26 Jul. 1979 24 p refs calculate the mixing downstream of a typical turbofan mixer (Contract W-7405-eng-48( geometry. Experimental data obtained using pressure and (UCRL-15050( Avail: NTIS HC A02/MF AOl temperature rakes at the lobe and nozzle exit stations were A vacuum system aperture for the advanced test accelerator used to validate the computer results. The relative importance is analyzed. An axial aerowindow. a suction type aerowindow. of turbulence in the mixing phenomenon as compared with the

144 N80-1 5983

streamwise vorticity set up by the secondary flows was determined. The observations suggest that the generation of streamwise vorticity plays a significant role in determining the temperature distribution at the nozzle esit plane. K.L.

N8O15871*# Stanford Univ.. Calif. Dept. of Aeronautics and Astronautics. AN EXPERIMENTAL STUDY OF THE STRJJCTURE AND ACOUSTIC FIELD OF A JET IN A CROSS STREAM Ivan Camelier and K. Karamcheti Jan. 1976 134 p refs (Grants NGL-05-020-526: NsG-2007) (NASA-CR- 162464: StJ-JIAA-TR-2) Avail: NTIS HC A07/MF AOl CSCL 20A The plane of symmetry of a high speed circular jet was surveyed to measure the mean and turbulent velocity fields by using constant temperature hot wire anemometry. The intensity of the noise radiated from the jet was determined in the tunnel test section by utilizing the cross-correlation at a particular time delay between the signals of two microphones suitably located along a given direction. Experimental results indicate that the turbulent intensity inside the crossflow jet increases by a factor of (1. + 1/2) as compared to the turbulent intensity of the same let under free conditions, with r indicating the ratio of the let velocity by the cross stream velocity. The peak observed in the turbulence spectra obtained inside the potential core of the let has a frequency that increases by the same factor with respect to the corresponding frequency measured in the case of the free let. The noise radiated by the jet becomes more intense as the crossflow velocity increases. The measured acoustic inten- sity of the crossflow jet is higher than the value which would be expected from the increase of the turbulent intensity only. A.R.H.

N8O15874*# National Aeronautics and Space Administration. Langley Research Center. Hampion. Va. A STUDY OF PARTIAL COHERENCE FOR IDENTIFYING INTERIOR NOISE SOURCES AND PATHS ON GENERAL AVIATION AIRCRAFT James T. Howlett Dec. 1979 17 p refs Presented at 98th Acoust. Soc. of Am. Meeting, Salt Lake City. 26-30 Nov. 1979 (NASA-TM-80197( Avail: NTIS HC A02/MF AOl CSCL 20A The partial coherence analysis method for noise source/path determination is summarized and the application to a two input. single output system with coherence between the inputs is illustrated. The augmentation of the calculations on a digital computer interfaced with a two channel, real time analyzer is also discussed. The results indicate possible sources of error in the computations and suggest procedures for avoiding these errors. M G,

N80-15983# Army Missile Research arid Development Com- mand. Redstone Arsenal, Ala. Technology Lab. AERODYNAMIC DATA BASE USERS GUIDE George M. Landingham 5 Jun. 1979 27 p (AD-A074448: DRDMI-T-79-62) Avail: NTIS HC A03/MF AOl CSCL 05/2 A data base system has been developed for storage and interactive analysis of data. This report is intended as a description of the system and as a users guide. The equipment on which the data base system is implemented is detailed. A description of the data base structure and detailed instructions for using the system are included. GRA

145 SUBJECT INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Suppl. 121) APRIL 1980

Typical Subject Index Listing

EXTENSION lIES ATIOU ACOUSTICS The analysis of wing-body combinations at moderate Quiet Clean Short-haul Experimental Engine (QCSEE) r angles of attack --- uissile bodies Over-The-Wing (OTW) propulsion systems test (AD-A07428 14] 88511040 report. Volume 4: Acoustic performance (NASA-CR-135326] 880-15118 ACTUATORS Quiet Clean Short-haul Experimental Engine REPORT (QCSRE). Ball spline pitch change mechanism NUMBER NUMBERIo IF design report Es (RASA-CR-134873] 880-15101 Quiet Clean Short-haul Experimental Engine (QCSEE) whirl test of cam/harmonic pitch change actuation system The title is used to provide a description of the subject matter. When the title is (NASA-CR-135140] 880-15117 insufficiently descriptive of the document content, a title entension is added. ADAPTIVE CONTROL separated from the title by three hyphens. The NASA or AIAA accession number Adaptive allocation of decisionmaking is included in each entry to assist the user in locating the abstract in the abstract responsibility between hunan and computer in section of this supplement. If applicable, a report number is also included as an multitask situations ASO- 18 022 aid in identifying the document. ADDITIVES Aircraft fuel system simulator tests with antimisting kerosene (jet A fuel with FH-9 additive) --- flammability tests A IAD-A073237] 880-14256 A-1O AIRCRAFT ADHESIVE BONDING Practical method of fatigue crack growth analysis Sonic fatigue design data for bonded aluminum for damage tolerance assessment of aluminum aircraft structures structure in fighter type aircraft (STAR PAPER 80-0303] 580-18304 rAISA PAPER 80-0405] A80-18346 Fatigue life prediction of a bonded splice joint Evaluation of the aerodynamic characteristics of a (AThA PAPER 80-0305] A80-18306 1/20-scale 6-10 model at Mach numbers from 0.30 AERIAL RUDDERS to 0.75 Fin design with ACT in the presence of strakes f 55-5074867] 880-15055 880-15161 ACCELEP.ATIOR (Pfl'YSICS) AEROACOUSTICS The effects of motion and 9-seat cues on pilot Estimation of noise source strengths in a gas simulator performance of three piloting tashs turbine combustor rRAsA-TP-1601] 880-15069 (BIAS PAPER 80-0034] 680-18245 ACCELERONETERS Assessment at full scale of exhaust nozzle-to-wing Nethods for strap-down attitude estimation and size on STOL-OTW acoustic characteristics navigation with accelerometers 680-20952 880-14034 Acoustic considerations of flight effects on jet ACOUSTIC ATTENUATION noise suppressor nozzles Comparison of inlet suppressor data with (AISA PAPER 80-0168] 580-20965 approximate theory based on cutoff ratio Acoustically swept rotor --- helicopter noise (AlAS PAPER 80-0100] 680-209614 reduction Evaluation of approximate methods for the RASFi-CASE-ARC-11106-1 ] 880-14107 prediction of noise shielding by airframe Applications of diffraction theory to aeroacoustics components aircraft noise rsAsA-TP-1004] 880-15129 880-14870 ACOUSTIC FATIGUE Experimental and numerical results of sound Sonic fatigue design data for bonded aluminum scattering by a body --- interaction of aircraft structures aerodynamic noise and tuselage AIAA PAPER 80-0303] 580-18304 88 0-14 873 ACOUSTIC NRA SURENEITS Aeroacoustic measuring techniques in or outside Aeroacoustic measuring techniques in or outside turbulent flows turbulent flows 880-14876 880-14 876 AERODTUANIC CNARACTERISTICS An experimental study of the structure and Concerning the information efficiency of acoustic field of a jet in a cross stream aerodynamic experiments Ames 7-ft by 10-ft wind tunnel tests 680- 17 67 1 (NASA-CR-162868] 880-15871 Analytical investigation of aerodynamic ACOUSTIC RETROFITTING characteristics of highly swept wings with Quiet Clean Short-Ratil Fxperinental Engine separated flow (QCSEE): Acoustic treatment development and A80-17 697 design Effects of the aerodynanic cross-coupling and fNASA-CR-135266] 880-15122 lateral acceleration derivatives on airplane ACOUSTIC SCATTERING dynamic characteristics Experimental and numerical results of sound (AIAA PAPER 80-01701 680-17699 scattering by a body --- interaction of Engine aerodynamic installation by numerical aerodynamic noise and fuselage simulation 880- 14873 [AIAA PAPER 80-0108] 680-18271 Experimental determination of pure rotary stability derivatives using curved and rolling flow wind tunnel (ATAA PAPER 80-0309] 680-18308

A-i

AERODYNA IIC COEPYICIENTS SUBJECT INDEX

Studies of leading-edge thrust phenomena Conceptual design and performance estimates for a (8188 PAPER 80-0325) 880-18315 supersonic aerodynamic window for the ATA vacuum Effects of non-planar strake-wing on the vortex system aperture lift characteristics of a twin-jet fighter (UCRL-15051) 880-15183 configuration AEBODYNA!IC DRAG (AIAA PAPER 80-0329) 880-18318 The minimum induced drag of aerofoils Correlation of predicted longitudinal aerodynanic (NACA-121) 880-15038 characteristics with full-scale wind tunnel data AERODYNANIC FORCES on the ATLIT airplane The aerodynamic forces on airship bulls (&IAA PAPER 80-0186) 480-18356 [NACA-184] 880-15039 Hybrid vortex method for lifting surfaces with Elements of the wing section theory and of the free-vortex flow wing theory [6188 PAPER 80-0070] 880-19307 (NACA-191] 880-15040 Assessment of analytic methods for the prediction General theory of aerodynamic instability and the of aerodynamic characteristics of arbitrary mechanism of flutter bodies at supersonic speeds [NACA-496] 880-15047 [8188 PAPER 80-0071) &80-193)8 Exploratory studies of the cruise performance or Designing light airplanes --- Russian book upper surface blown configuration: Experimental 880-19414 program, high-speed force tests Scale model performance test investigation of [NASA-Cfi-159134] 880-15070 exhaust system mixers for an Energy Efficient Exploratory studies of the cruise performance of Engine /E3/ propulsion system upper surface blown configurations: Program [8186 PAPER 80-0229] 880-20958 analysis and conclusions The quasi-vortex-lattice method for wings with (RASA-CR-159136] N80-15072 edge vortex separation AFFDL experience in active control technology [NASA-CR-162530] 880-14052 880-15159 Theoretical study of aerodynamic characteristics Problems of unsteady aerodynamics raised by the of wings having vortex flow use of control surfaces as active controls [NASA-CR-159184] 880-14053 880-15167 Quiet short-haul research aircraft familiarization AERODYNAmIC INTERFERENCE document --- SECt Two dimensional aerodynamic interference effects r NASA-TN-81149] N80-14108 on oscillating airfoils with flaps in ventilated Applications of modern hydrodynamics to subsonic wind tunnels --- computational fluid aeronautics. Part 1: Fundamental concepts and dynamics the most important theorems. Part 2: rNASA-CR-3210] 880-14047 Applications AERODYH!IC LOADS (NACA-116) 880-15034 CH-46 composite rotor blade flight stress survey Quiet Clean Short-haul Experimental Engine data. Volume 3: Plotted forward rotor blade (QCSEE). Aerodynamic and aeromechanical chord, torsion and absolute loads performance of a 50.8 cm (20 inch) diameter 1.34 (80-8075612) 880-15077 PR variable pitch fan with core flow Analysis of low-speed helicopter flioht test data INASA-CR-135017] 880-15087 [60-8074141) 880-15079 Aerodynamic characteristics of controls AERODYNAmIC NOISE con ferences Sound generation in a flow near a compliant wall fAGARD-CP-262] 880-15149 880-20 153 In-flight measured characteristics of combined Acoustically swept rotor --- helicopter noise flap-spoiler direct lift controls reduction RHO- 15165 [NASA-CASE-ARC-11106-1] 880-14107 Aerodynamic characteristics of moving Experimental and numerical results of sound trailing-edge controls at subsonic and transonic scattering by a body --- interaction of speeds aerodynamic noise and fuselage 880-15169 880-14873 Unsteady aerodynamics of two-dimensional spoilers AERODYNANIC STABILITY at low speeds Formulation of coupled rotor/fuselage equations of 880- 15 170 sotion Aerodynamic interaction on a close-coupled canard 680-17717 wing configuration Determination of the spin and recovery N8O-151 75 characteristics of a typical low-wing general On the effects of gaps on control surface aviation design characteristics [8188 PAPER 80-0169] 880-18351 880-15 176 Aircraft aerodynamics - Dynamics of longitudinal AERODYRABIC COEFFICIENTS and lateral motion --- Russian book Estimation of the accuracy of dynamic A80-19374 flight-determined coefficients Dynamic response of a Mach 2.5 axisymmetric inlet (8188 PAPER 80-0171] 880-17700 and turbojet engine with a poppet-value AERODYNAmIC CONFIGURATIONS controlled inlet stability bypass system when Theoretical study of aerodynamic characteristics subjected to internal and external airflow of wings having vortex flow transients rNAsA-cR-159184] 880-14053 INASA-TP-1531] 880-14123 Quiet Clean Short-haul Experimental Engine Flight testing of the buffeting behavior of combat (QCSEE) : The aerodynamic and mechanical design aircraft of the QCSEE under-the-wing fan IPSA-TT-523) 880-14143 (NASA-CR-135009] 880-15109 General theory of aerodynamic instability and the An analytical and experimental study of a short sechauism of flutter s-shaped subsonic diffuser of a supersonic inlet [RACA-496] 880-15047 [NASA-TM-81406] 880-15134 Control considerations for CCV fighters at high Wind tunnel measurements and analysis of some angles of attack unusual control surfaces on two swept wing N80-15 160 fighter configurations Some investigations concerning the effects of qaps 880-15155 and vortex generators on elevator efficiency and Roll control by digitally controlled segment of landing flap sweep on aerodynamic spoilers characteristics 880-15 156 880-15 178 Wind tunnel investigation of controls for OF on a AERODYNAMIC STALLING fighter-type configuration of higher angles of Reynolds number and compressibility effects on attack dynamic stall of a RACA 0012 airfoil 880-15 166 [AIAA PAPER 80-0010) 880-18238 Nonlinear aerodynamics of all-movable ccntrols 880- 15 173

A-2

SUBJECT INDEX AIR TRAFFIC CONTROL

Determination of the spin and recovery AIR FLON characteristics of a typical low-wing general Turbojet-exhaust-nozzle secondary-airflow pumping aviation design as an exit control of an inlet-stability bypass [8188 PAPER 80-0169] 880-18351 system for a Mach 2.5 axisymmetric Enhanced departure/spin recovery of fighter mixed-compression inlet --- Lewis 10- by 10-ft. aircraft through control of the forebody vortex supersonic wind tunnel test orientation [RAS8-TP-1532] 880-14124 [AIAA PAPER 80-0173] 880-18352 AIR NAVIGATION The effects of leading edge modifications on the Performance evaluation of image correlation post-stall characteristics of wings techniques --- for aircraft inertial navigation [AIAA PAPER 80-0199) 880-18375 systems A phenomenologica3. model of the dynamic stall of a 880-17534 helicopter blade profile strapdown inertial reference system for roNERA, IP NO. 1979-1891 880-20096 commercial airline use in navigation and flight High angle of attack characteristics of different control fighter configurations #80-17 558 tHBR-tTFR-1443(0) ) 980-14058 Advances in Guidance and Control Systems Using. Simulator study of stall/post-stall Digital Techniques characteristics of a fighter airplane with [AGARD-CP-272) 980-19017 relaxed longitudinal static stability --- F-16 AIR POLLUTION (N#SA-TP-1538] 980-114136 Quiet Clean Short-haul Experimental Engine (QCSEE) A parametric wing design study for a modern clean combustor test report laminar flow winq [NASA-CR-134916] 980-15104 rNAsA-TN-80154] 980-15050 AIR TO SURFACE MISSILES AERODYNAMICS Control integration technology impact --- as a Experimental study of confluence with separation basis for improving the combat effectiveness of on an afterbody of revolution all tactical aircraft [ONERA, 19 90. 1979-151) 880-20088 980-15162 Modification of axial ccnpressor streamline AIR TRAFFIC program for analysis of engine test data Air traffic density and distribution measurements [HASA-TM-79312] 980-14051 [AD-A073229] 980-114064 Aeronautical Research Laboratories AIR TRAFFIC CONTROL [8978/30107] 980-1507.6 Automation and air traffic control Theoretical aerodynamic methods for active control 880-18722 devices The economics of air traffic control 980-15 150 A80- 18723 A survey of experimental data on the aerodynamics ATC and the airborne traffic-situation display of controls, in the light of future needs ABO- 187214 980- 15151 A survey of the stochastic filtering techniques AEROELASTICITY for data processing in air-traffic control and Formulation of coupled rotor/fuselage equations of surveillance systems motion A8 0-20 867 A80-17717 State of the art for di g ital avionics and An empirical approach for checking flutter controls, 1978 stability of gliders and light aircraft 980-114 018 880-15144 Air traffic density and distribution measurements AERONAUTICAL ENGINEERING 80-8073229] 880-14064 APFOPP - message and data switching systems for On radar in air traffic control --- conference, aeronautical operations Rome, Jul. 1979 880-19 579 [FUB-11-1979) 980-14065 Aeronautical Research Laboratories Problems related to the design and construction of [9978/30107] 980-15026 a radar network AFTERBODIES 980-14066 Experimental study of confluence with separation methodology for the evaluation of a radar site on an afterbody of revolution 980-14 067 [ONFRA, TP 80. 1979-151) 880-20088 Performance evaluation methods of a secondary AIR CARGO radar network Analog aircraft weight and balance computer 880-14068 rSAVE PAPER 1283] A80-20631 Organization of an integrated global maintenance Computer simulation of an air cargo small package service --- Radar Networks sorting system 88 0-14069 880-20 866 Automation of flight on-line strategic control: Shipping by air - Is the value of your tine worth it The case of speed control on pre-established #80-2086 8 routes Models for freight access to air terminals 980-14070 #80-20869 Radar data utilization in autonating the Air cargo container utilization optimization sequencing of aircrafts in terminal areas through modeling 980-14071 480-20870 Tactical analysis of conflicts in an air traffic AIR COOLING control system: Design and implementation of a Optimization of turbine nozzle cooling by provisional model combining impingement and film injection 980-14072 tAIAA PAPER 80-0299) 480-19316 Tracking algorithms for mono and multiradar AIR DUCTS 4480-1 41 074 Experimental investigation of the characteristics A distributed processing system for radar data of pneumatic transfer lines presentation - A80-19052 880-141 075 The analysis of sound propagation in jet engine Filtering of s ynthetic radar data ducts using the finite difference method 980-14 076 rAD-A074233) 880-14853 Visual displays for air traffic control data AIR FILTERS 980-i ll 077 The transfer of carbon fibers through a commercial Implementation of air traffic control radar aircraft water separator and air cleaner receivers with fast Fourier transform processors [NASA-CR-159183) 880-1l4359 880-1408 6 An air traffic channel simulation by means of ray-tracing techniques N80-14088

A-3

AIR TRANSPORTATION SUBJECT INDEX

L-band measurements in the air traffic channel to Plight control and configuration design characterize secondary radar systems considerations for highly maneuverable aircraft 1180-14092 980-15158 Antireflection techniques for detecting false AIRCRAFT CONSTRUCTION NATEBIALS tracks in air traffic surveillance with Determination of the stress intensity factor of secondary radar composite structural members 1180-14 100 #80-17 958 Onboard collision avoidance system: Environmental Advanced materials and the Canadair Challenger influence on the tracking algorithm requirements [SAWE PAPER 12841 #80-20632 980-14 105 Protective coatings for aircraft composites in Preliminary test results cf a flight management nuclear environments algorithm for fuel conservative descents in a rAD-A074889] 080-14199 time hased metered traffic environment Composite structural materials flight tests of an algorithm to minimize fuel [NASA-CR-162578] 980-15076 consumption of aircraft based on flight time Climatic chamber testing aircraft, engines [NASA-TN-80194] 1189-19114 armament and avionics; Test operations procedure AIR TRANSPORTATION environmental test chambers and facility for Aircraft delays at major US airports can be reduced testing aircraft construction materials and [P8-299442/4] 1180-15061 engines AIRBORNE EQUIPRENT [80-8074049] 980-15181 Wire obstacle warning system /NOWS/ - A real-time AIRCRAFT CONTROL airborne sensor for automatic detection and Comment on flandling quality criterion for heading recognition of wirelike objects control - 880-17402 A80-17 698 ATC and the airborne traffic-situation display Estimation of the accuracy of dynamic 880-18724 flight-determined coefficients A light aircraft camera Pod - The Enviro-Pod (AT hA PAPER 80-0171] #80-17700 880-20251 Controllers for aircraft motion simulators Infrared sensor system performance simulations [AIAA PAPER 80-0050] A80-18252 880-20900 A statistical method applied to pilot behavior AIRBORNE/SPACEEOPN! CONPUTERS analysis in multiloop systems Redundancy management considerations for a ABO- 18537 control-configured fighter aircraft triplex Constrained optimum trajectories with specified digital fly-by-wire flight control system range 980-14026 #80-18538 The integrity of onboard computer programs: A Aircraft aerodynamics - Dynamics of longitudinal solution and lateral notion --- Russian book 980-14028 880-19374 An assessment of and approach to the validation of Recent developments in flight simulation techniques digital flight contrcl systems #80-20907 980-14036 Advances in Guidance and Control Systems T3sinq The avionics computer program: Practical Digital Techniques experiences with a methodology --- Mirage Wi and [AGARD-C p-272) 980-14017 Mirage 200 aircraft State of the art for digital avionics and 980- 14 037 controls, 1978 AIRCR APT ACCIDENT INVESTIGATION 1180-14018 Accident investigation Analyses and tests of the B-i aircraft structural 980-14636 mode control system A first look at the effect of severe rainfall upon [RASA-CR-144887] 980-15073 an aircraft lerodynamic characteristics of controls tNASA-CP-182569] 980-15058 con ferences AIRCRAFT CONMUNICATION AGARD-CP-2621 980-15149 APROPP - Nessage and data switching systems for Theoretical aerodynamic methods for active control aeronautical operations devices 880-19579 980-15150 AIRCRAFT CONPART!BNTS A survey of experimental data on the aerodynamics Simultaneous cabin and ambient ozone measurements of controls, in the light of future needs on two Poeing 747 airplanes, volume 1 980-15151 TNASA-TN-791663 980-15059 Correlation of P-15 flight and wind 1nnel test A study of partial coherence for identifying control effectiveness interior noise sources and paths on general 1180-15152 aviation aircraft Plight control and configuration design [NASA-TN-80197J 1180-158711 considerations for highly maneuverable aircraft AIRCRAFT CONFIGURATIONS 980-15 154 Application of a higher order panel method to Direct side force and drag control with the aid of realistic supersonic configurations pylon split flaps ATAA PAPER 79-0274] #80-17696 1180-15 163 Propulsion/airframe integration considerations for Wind tunnel investigation of controls for OF on a high altitude hypersonic cruise vehicles fighter-type configuration of higher angles of [AIAA PAPER 80-0111] #80-18272 attack Small ship-based VTOL aircraft - A design exercise 1180-15166 [SANE PAPER 1296] #80-20639 Problems of unsteady aerodynamics raised by the Altitude response of several airplanes during use of control surfaces as active controls landing approach --- including space shuttle 980-15 167 fNASA-TN-801861 980-14139 Forebody vortex blowing: A novel control concept Exploratory studies of the cruise performance of to enhance departure/spin recovery upper surface blown configuration: Experimental characteristics of fighter and trainer aircraft program, high-speed force tests 1180-15 172 [NASA-CR-15913 11] 980-15070 Nonlinear aerodynamics of all-movable controls Exploratory studies of the cruise performance of 1180- 15 173 upper surface blown configurations: AIRCRAFT DESIGN Experimental program, high-speed pressure tests Analytical investigation of aerodynamic rNASA-C9-159135] 980-15071 characteristics of highly swept wings with Hypersonic cruise aircraft propulsion integration separated flow study, volume 1 #80-17697 [NASA-CR-158926-VOL-1 ] 980-15074 computer simulation of engine systems --- for Hypersonic cruise aircraft propulsion integration aircraft design study, volume 2 [AIAA PAPER 80-0051) A80-18253 NASA-CR-158926-VOL-2) 980-15075

SUBJECT INDEX AIRCRAFT NODELS

Development of a vortex-lift-design method and On the use of vibration self-damping materials in application to a slender maneuver-wing the manufacture of parts for rotating machinery con figuration 880-14 135 [4144 PAPER 80-0327] #80-18316 Quiet clean Short-haul Experimental Engine An inverse transonic wing design method (QCSEE). Double-annular clean combustor [AIAA PAPER 80-0330] A80-18319 technology development report #ssessnent of analytic methods for the prediction [NASA-CR-159483] 880-15121 of aerodynamic characteristics of arbitrary Computer simulation of engine systems bodies at supersonic speeds [NASA-TM-79290] R80-15132 (#144 PAPER 80-0071] A80-19308 Climatic chamber testing aircraft, engines Designing light airplanes --- Russian book armament and avionics; Test operations procedure 480-19 414 environmental test chambers and facility for The next supersonic transport testing aircraft construction materials and A80-20 214 engines Application of 8CR guidelines to weight effective [AD-#0740 149) 880-15181 aircraft design --- Radar Cross Section AIRCRAFT EQUIPRERT !SAWR PAPER 1270] A80-20626 An overvoltage safety system for direct current Application of finite element analysis to aircraft generators derivation of structural weight 480-1905 1 [SANE PAPER 127fl 480-20627 Aircraft torque motors --- Russian book Tilt rotor - An effective V/STOL concept #80- 19 199 [SANE PAPER 1273) 480-20628 A high accuracy flight profile determining system Advanced materials and the Canadair Challenger systems analysis of inertial navigation [SAW! PAPER 1284] 480-20632 system for aircraft position determination Designing to life cycle cost in the Hornet program 880-111 0142 [SAW! PAPER 12931 480-20638 Aircraft anti-icing/de-icing Small ship-based VTCL aircraft - A design exercise [40-4074128] 880-15078 [SANE PAPER 1296] 480-20639 AIRCRAFT FUEL SYSTENS Weight Integrated Rising Evaluation /WIS!/ - A Aircraft fuel system simulator tests with tool for preliminary design antimisting kerosene (jet A fuel with ER-9 [SANE PAPER 1312] 480-20646 additive) --- flammability tests A simple design synthesis method used to estimate An-4073237] 880-14256 aircraft gross weight AIRCRAFT FUELS [SAW! PAPER 13131 #80-20647 Preliminary test results of a flight management Navy V/STOL - A continuing initiative algorithm for fuel conservative descents in a rSANE PAPER 1325] 480-20655 time based metered traffic environment Weight impact of VTOL flight tests of an algorithm to minimize fuel [SAW! PAPER 13261 480-20656 consumption of aircraft based on flight tine Quiet short-haul research aircraft familiarization rNASA-TN-80194] 880-141111 document --- STOL AIRCRAFT GUIDANCE [14ASA-T8-81149) 880-14108 Advances in Guidance and Control Systems Using Exploratory studies of the cruise performance of Digital Techniques upper surface blown configurations: Program (AGARO-cP-272] 880-14017 analysis and conclusicns AIRCRAFT BAZARDS [NASA-cR-159136] 880-15072 An evaluation of the bird/aircraft strike hazard 34-64 circulation control wing contractor flight at Barksdale Air Force Base, Louisiana (SAC) demonstration [40-4074390] 880-14063 (AD-A074888] 880-15080 Simultaneous cabin and ambient ozone measurements AIRCRAFT ENGINES on two Boeing 747 airplanes, volume 1 Preparing aircraft propulsion for a new era in NASA-TN-79166] 880-15059 energy and the envircnlnent AIRCRAFT INSTRURENTS 480- 17737 Some practical aspects of the calibration of air Regression techniques applied to parametric data systems turbine engine simulations 480- 18 865 fAIAA PAPER 80-0053] 480-18255 Experimental investigation of the characteristics Engine aerodynamic installation by numerical of pneumatic transfer lines simulation 480-19052 [AIAA PAPER 80-0108] #80-18271 Investigations of the optimal configuration of Thermal barrier coatings for aircraft gas turhines high-stability quartz oscillators for aircraft [AIAA PAPER 80-0302] 480-18303 and missiles Enqine component improvement program - Performance A80-19990 improvement AIRCRAFT LANDING [AIAA PAPER 80-0223) 480-19300 The loads at landing impact --- for aircraft Fuel conservation benefits and critical A80- 17723 technologies of recuperative and advanced What brings us down tomorrow - Landing guidance conventional cycle turboshaft engines systems for the 1980s [AIAA PAPER 80-02211] A80-19301 480-18 725 Thermal state of structural members of aircraft Altitude response of several airplanes during engines --- Russian bcck landing approach --- including space shnttle A80-19 412 fNASA-TN-801861 880-14139 Damping capacity of plastic compressor tlades Landing approach airframe noise measurements and #80-19868 anaLysis Integrated circuit characteristics at 260 C for [NASA-TP-1602] 880-15028 aircraft engine-ccntrcl applications AIRCRAFT NAIRTENANCE 480- 20 112 Study of turboprop systems reliability and Advanced technology effects on V/STOL propulsive maintenance costs system weight [RASA-cR-135192) 880-14129 (SANE PAPER 13001 480-20640 Fleet hardness variation --- to determine aircraft Preliminary weight estimation of engine section survivability due to blast loads structure [AD-A0714849] 880-15029 [SAW! PAnER 1311) #80-20645 AIRCRAFT NANNUVERS Problems associated with cargo airplanes having Sonic-boom wave-front shapes and curvatures aft mounted engines associated with maneuvering flight [SANE PAPER 1314] 480-20648 [RASA-TP-1611) 880-14045 Unification of oils for aircraft gas-turbine engines AIRCRAFT NODELS 48 0-2 0690 The criticality of engine exhaust simulations on Exhaust emission reduction for intermittent VSTOL model-mea sured ground effects combustion aircraft engines (ATAR PAPER 80-0230] A80-18276 [RASA-cR-1597571 880-111130

A-5

AIRCRAFT NOISE SUB3!CT INDEX

Quiet Clean Short-Haul Experimental Engine (QCS!E) AIRCRAFT SPIN acoustic and aerodynamic tests on a scale model Determination of the spin and recovery over-the-wing thrust reverser and forward thrust characteristics of a typical low-wing general nozzle aviation design fNASA-CR-135254] 1180-14115 [8188 PAPER 80-0169] 880-18351 Evaluation of the aerodynamic characteristics of a AIRCRAFT STABILITY 1/20-scale 8-10 model at Mach numbers from 0.30 Comment on Handling quality criterion for heading to 0.75 con trol [80-A0711867] 8180-15055 A80-17698 AIRCRAFT NOISE Effects of the aerodynamic cross-coupling and Rotational noise of helicopter rotors lateral acceleration derivatives on airplane 880-17718 dynamic characteristics Airport noise, location rent, and the market for (AIAA PAPER 80-0170] A80-17699 residential amenities Estimation of the accuracy of dynamic 880- 17770 flight-determined coefficients Assessment at full scale of exhaust nozzle-to-wing [8188 PAPER 80-0171] 880-17700 size on STOL-OTW acoustic characteristics Analysis of rotor-fuselage coupling and its effect A80- 20952 on rotorcraft stability and response Comparison of inlet suppressor data with A80- 17716 approximate theory based on cntotf ratio Enhanced departure/spin recovery of fighter [8188 PAPER 80-0100) 880-20964 aircraft through control of the forebody vortex Applications of diffraction theory to aeroacoustics orientation aircraft noise [AIAA PAPER 80-0173] 880-18352 1180-ill 870 Aircraft aerodynamics - Dynamics of longitudinal Landing approach airframe noise measurements and and lateral motion --- Russian book analysis A80- 19 3714 [NASA-TP-1602] 1180-15028 AIRCRAFT STRUCTURES Acoustic analysis of aft noise reduction Sonic fatigue design data for bonded aluminum techniques measured on a subsonic tip speed 50.8 aircraft structures cm (twenty inch) diameter fan --- quiet engine [AIAA PAPER 80-0303] 880-18304 program °ractical method of fatigue crack growth analysis rNASA-C11-134891) 1180-15102 for damage tolerance assessment of aluminum A study of partial coherence for identifying structure in fighter type aircraft interior noise sources and paths on general [AIAA PAPER 80-0405] A80-183446 aviation •aircraft Code optimization for solving large 3D N9P problems [1IASA-TM-80197] 1180-15874 electromagnetic scattering by aircraft AIRCRAFT PEPFORMAECE structures Flight certification of the Cessna TU2O6G 880-197611 amphibious floatplane Preliminary weight estimation of engine section 880-18 186 structure Multiple tactical aircraft combat performance [SAWN PAPER 1311) 880-20645 evaluation system Review of investigations into aeronautics related (8188 PAPER 80-0189] 880-18358 fatigue Federal Pepublic of Germany Tilt rotor - An effective V/STOL concept [LBF-S-142] 1180-14422 [SAWE PAPER 1273) 880-20628 Applications of modern hydrodynamics to Problems associated with cargo airplanes having aeronautics. Part 1: Fundamental concepts and aft mounted engines the most important theorems. Part 2: [sAWN PAPER 1314] 880-20648 Applications Weight impact of VIOL [NAcA-116] 1180-15034 rSAWE PAPER 1326] 880-20656 The aerodynamic forces on airship hulls A first look at the effect of severe rainfall upon rRAcA-1814] 1180-15039 an aircraft Ivaluation of approximate methods for the [I1ASA-CR-162569] 1180-15059 prediction of noise shielding by airframe AIRCRAFT RELIABILITY components Designing to life cycle cost in the Hornet program [I1ASA-TP-1004] 1180-15129 [SAWE PAPER 1293) 880-20638 Dynamic identification of light aircraft Automatic recovery after sensor failure onboard structures and their flutter certification 1180-111028 1180-15 145 AIRCRAFT SAFETY AIRCRAFT SURVIVABILITY Covariance simulation cf BCAS - An aircraft Nultiple tactical aircraft combat performance collision avoidance system evaluation system 880-20915 [AIAA PAPER 80-0189] 880-18358 Effect of weather conditions on airport operations rotective coatings for aircraft composites in 1180-18638 nuclear environments Current research on aviation weather (AD-A074889] 1180-14199 (bibliography), 1970 Fleet hardness variation --- to determine aircraft [NASA-CR-3214] 1180-18651 survivability due to blast loads NASA technical advances in aircraft occupant safety AD-A074849) 880-15029 clear air turbulence detectors, fire AIRFIELD SURFACE MOVEBENTS resistant materials, and crashworthiness Simulation of a surveillance and control system of [RASA-TM-80851 ] 1180-15060 surface traffic in an airport AIRCRAFT SPECIPICATIONS 1180-14 073 Weight Integrated Sizing Evaluation /WISE/.- A Effect of weather conditions on airport operations tool for preliminary design 1180-14638 [SAWN PAPER 1312] A80-20686 AIRFOIL PROFILES Low cost aircraft flutter clearance --- conference Experimental and computational study of transonic [AGAPS-cP-278] 1180-15141 flow about swept wings Comparison of international flutter requirements [8188 PAPER 80-0005] A80-18235 and flutter freedcm substantiation of light Conformal mapping analysis of multielement aircraft in the USA airfoils with boundary-layer corrections 11110-15142 [AIAA PAPER 80-0069] 880-18261 The state-of-the-art of flutter substantiation Studies of leading-edge thrust phenomena procedures among US general aviation manufacturers [AIAA PAPER 80-0325) 880-18315 1180-15 1113 The rational design of an airfoil for a high Dynamic identification of light aircraft performance jet trainer structures and their flutter certification [AIAA PAPER 80-0328) A80-18317 1180-15145 An inverse transonic wing design method The minimum cost approach to flutter clearance [AIAA PAPER 80-0330] 880-18319 1180-151118

A-6

SUBJECT INDEX ANTENNA DESIGN

Pressure distribution on Jonkowski wings AIRSPEED tNACA-TN-336) 880-15036 A flutter-speed formula for wings of high aspect The minimum induced drag of aerofoils ratio [NACA-121) 880-15038 880-15 147 AIRFOILS ALGORITHMS Reynolds number and compressibility effects on Automation of flight on-line strategic control: dynamic stall of a NACA 0012 airfoil The case of speed control on pre-established [ATAP. PAPER 80-0010] P.80-18238 routes Analysis of transonic flow about harmonically 880-14070 oscillating airfoils and wings Radar data utilization in automating the [ATAP. PAPER 80-0189) P.80-18367 sequencing of aircrafts in terminal areas An investigation of several f actors involved in a 880-1407 1 finite difference procedure for analyzing the Tactical analysis of conflicts in an air traffic transonic flow about harmonically oscillating control system: Design and implementation of a airfoils and wings provisional model [NASA-CR-159143] 880-14056 880-14 072 Computer program to prepare airfoil characteristic Tracking algorithms for mono and multiradar data for use in heliccpter performance 880-14078 calculations Antireflection techniques for detecting false [RASA-TN-786271 880-15031 tracks in air traffic surveillance with The minimum induced drag of aerofoils secondary radar [NACA-121] 880-15038 880-14 100 A users guide for 8344: A program using a finite Onboard collision avoidance system: Environmental difference method to analyze transonic flow over influence on the tracking algorithm requirements oscillating airfoils 880-14 105 rNASA-CR-159141] 880-15052 Preliminary test results of a flight management AIRFRAMES algorithm for fuel Conservative descents in a Landing approach airframe noise measurements and time based metered traffic environment ana lysis flight tests of an algorithm to minimize fuel [RASA-TP-1602) 880-15028 consumption of aircraft based on flight time AIRLINE OPERATIONS [RASA-TM-80194] 880-14114 Shipping by air - Is the value of your time worth it ALL-WEATHER LANDING SYSTEMS P.80-20868 What brings us down tomorrow - Landing guidance AIRPLANE PRODUCTION COSTS systems for the 1980s Application of parametric weight and cost P.80-18725 estimating relationships to future transport AlPHA JET AIRCRAFT aircraft Roll control by digitally controlled segment (SANE PAPER 12921 P.80-20637 spoilers AIRPORT PLANNING 880-15 156 An analytical method of testing pavement strength irect side force and drag control with the aid of P.80-17998 pylon split flaps Marseilles - Metamorphosis of an airport 880-15163 P.80-17999 ALTITUDE CONTROL Computer simulation of an air cargo small package Altitude response of several airplanes during sorting system landing approach --- including space shuttle 880-20866 [NASA-TM-80186) 880-14139 Methodology for the evaluation of a radar site ALUMINUM ALLOYS 880-14067 Sonic fatigue design data for bonded aluminum AIRPORT SURFACE DETECTION EQUIPMENT aircraft structures On radar in air traffic control --- conference, (AIAA PAPER 80-03031 P.80-18304 Rome, Jul. 1979 P ractical method of fatigue crack growth analysis [FUB-11-1979) 880-14065 for damage tolerance assessment of aluminum Simulation of a surveillance and control system of structure in fighter type aircraft surface traffic in an airport [AIAA PAPER 80-0405] P.80-18346 880-14073 Advanced materials and the Canadair Challenger Development trends of airport surface traffic (SAWE PAPER 12841 A80-20632 control radar AMPHIBIOUS AIRCRAFT 880-14087 Flight certification of the Cessna TU2O6G Automatic systems for airport surface mobile media amphibious floatplane surveillance based on the use of secondary media P.80-18 186 880- 18104 ANALOG COMPUTERS AIRPORTS Analog aircraft weight and balance computer Airport noise, location rent, and the market for (SANE PARER 1283] P.80-20631 residential amenities - ANECHOIC CHAMBERS P.80-17720 Evaluation of approximate methods for the Centralized ground power systems conserve energy prediction of noise shielding by airframe P.80-18300 components Models for freight access to air terminals (NAS&-TP-1004] N80-15129 880-20868 ANGLE OP ATTACK An evaluation of the bird/aircraft strike hazard Investigation of leading-edge devices for drag at Barksdale Air Force Base, Louisiana (SAC) reduction of a 60-deg. delta wing at high angles rAD-A07'43901 880-14063 of attack Reflection cracking of bituminous overlays for [AIAA PAPER 80-0310] P.80-18309 airport pavements: A state of thc art High angle of attack characteristics of different rAD-A0734841 880-14184 fighter configurations Effect of Weather conditions on airport operations NBE-UFE-1443 (0) ] 88 0-14058 880-14 63 8 Control considerations for CCV fighters at high Aircraft delays at major US airports can be reduced angles of attack rPB-299442/ q ] 880-15061 880-15 160 AIRSHIPS Wind tunnel investigation of controls for OF on a Propulsion options for the HI SflT long endurance fighter-type configuration of higher angles of drone airship attack fAO-A074598) 880-14132 880-15166 The aerodynamic forces on airship hulls Nonlinear aerodynamics of all-movable controls INACA-184) 880-15039 880- 15 173 AIRSPACE ANTENNA DESIGN Air traffic density and distribution measurements Experimental loop antenmas for 60 KHz to 200 KH2 rAD-A073229] m80-14064 (RASA-CR-162729] 880-15063

A-7

ANTIICING ADDITIVES SUBJECT INDEX

ANTIICING ADDITIVES Avionics installation (AVSTALL) cost model for Aircraft anti-icing/de-icing user equipment of RAVSTAR global positioning [AD-A074128) 880-15078 system APPROACH [Rn-A073681] 880-14106 Altitude response of several airplanes during AXISYMMETRIC BODIES landing approach --- including space shuttle Experimental study of confluence with separation [RASA-TN-801861 880-14139 on an afterbody of revolution APPROXIMATION [OREBA, TP NO. 1979-151] A80-20088 Evaluation of approximate methods for the AXISYMIETEIC PLOW prediction of noise shielding by airframe Acoustic radiation from axisymmetric ducts - A components comparison of theory and experiment (NASA-TP-1004] 880-15129 fRIAR PAPER 80-0097] A80-18268 ARCHITECTURE (COMPUTERS) Mach 3 hydrogen external/base burning A flight control system using the DAIS architecture rAIRA PAPER 80-0280] A80-19311 880-14 019 Trends in digital data processing and system architecture --- avionics applications B N80-1 4020 B-i AIRCRAFT AROMATIC COMPOUNDS Analyses and tests of the B-i aircraft structural Effect of naphthenic aromatic hydrocarbons on the mode control system oxidizability of hydrogenated jet fuel --- jet ( NASA-CR-144887) 880-15073 engine fuels BALANCE AR0-17 675 A method of simplifying weight and balance for ATLIT PROJECT small aircraft Correlation of predicted longitudinal aerodynamic (SAWE PAPER 1278] A80-20630 characteristics with full-scale wind tunnel data BASE PLOW on the ATLIT airplane Mach 3 hydrogen external/base burning (AIRA PAPER 80-0186] AR0-18356 [AIAA PAPER 80-0280] A80-i9311 ATMOSPHERIC EFFECTS BEAT FREQUENCIES Atmospheric effects on Martian ejecta emplacement valuation of the intensity of beat-induced 880-20 192 vibrations ATMOSPHERIC TURBULENCE A80-17965 Effect of spanwise gust variations BIBLIOGRAPHIES 880-14 639 Current research on aviation weather ATTITUDE INDICATORS (bibliography), 1979 Methods for strap-down attitude estimation and [NASA-CR-3214) 880-14651 navigation with accelerometers BIRD-AIRCRAFT COLLISIONS #80-14034 An evaluation of the bird/aircraft strike hazard AUTOMATIC CONTROL at Barksdale Air Force Base, Louisiana (SAC) Aircraft aerodynamics - Dynamics of longitudinal Afl-A074390] 880-14063 and lateral motion --- Russian book BLADE TIPS A80-19 374 Effect of tip planform on blade loading Failure detection, isolation and indication in characteristics for a two-bladed rotor in hover highly integrated digital guidance and control rNASA-TN-78615] 880-14049 system Laser-optical blade tip clearance measurement system 880-14 027 (NASA-TM-81376] 880-14128 Radar data utilization in automating the BLAST LOADS sequencing of aircrafts in terminal areas Fleet hardness variation --- to determine aircraft 880-14 071 survivability due to blast loads Automatic systems for airport surface mobile media [AD-A074849] 880-15029 surveillance based on the use of secondary media BODY-RING AND TAIL CONFIGURATIONS 880-14 104 Large scale model tests of a new technology V/STOL AUTOMATIC PLIGHT CONTROL concept An assessment of and approach to the validation of tAIRA PAPER 80-0233] A8O-19303 digital flight contrcl systems Righ angle of attack characteristics of different R80-14036 fighter configurations Pilot control through the TRECOS automatic flight [MBB-UPE-1443(0) ] 880-14058 control system On the effect of wing wake on tail characteristics (NASA-TM-81152] 880-14138 880- 15174 AUTOMATIC PILOTS BODY-WING CONFIGURATIONS Verification of digital autopilot microprocessor Development of a vortex-lift-design method and hardware and software via hardware-in-the-loop application to a slender maneuver-wing simulat ion configuration A 8 0-2 0 901 rAIAA PAPER 80-0327] A80-iB3i6 Pilot control through the TAFCOS automatic flight Sffects of non-planar strake-wing on the vortex control system lift characteristics of a twin-jet fighter [NASA-TN-81152] 880-14138 con figuration AUTOMATION [AIAA PAPER 80-0329] A80-18318 Automation and air traffic conttol Euler solutions for wing and wing-bod y combination A80-1 8722 at supersonic speeds with leading-edge separation AVIONICS [ATAA PAPER 80-0126] A80-18359 Modular strapdown guidance unit with embedded BOEING 747 AIRCRAFT microprocessors Simultaneous cabin and ambient ozone measurements tAIAA PAPER 78-1239] A80-18534 on two Boeing 747 airplanes, volume 1 Advances in Guidance and Control Systems Tising (RRSA-TM-79166] 880-15059 Digital Techniques BOILER PLATE (AGARO-CP-272] 880-14017 Quiet Clean Short-Haul Experimental Engine State of the art for digital avionics and (OCSEE) - tinder-the-wing (TTTW) engine controls, 1978 boilerplate Nacelle test report. Volume 2: 880-14018 Aerodynamics and performance A flight control system using the DAIS architecture [NASA-CR-135250] 880-14116 1t80-14 019 BORON REINFORCED MATERIALS Trends in digital data processing and system Determination of the stress intensity factor of architecture --- avionics applications composite structural members 880-14020 RHO- 17958 The avionics computer program: Practical experiences with a methodology --- Mirage El and Mirage 200 aircraft R80-14 937

A-8

SUBJECT INDEX COLLISION AVOIDANCE

BOUNDARY LAYER CCNTROL CENTER op GRAVITY Enhanced departure/spin recovery of fighter Problems associated with cargo airplanes having aircraft through control of the forebody vortex aft mounted engines orientatics rSAwE PAPER 1314] 480-206118 14144 PAPER 80-0173] 480-18352 CENTRIFUGAL COIPRESSORS Control of forebody three-dimensional flow On the dynamics of compressor surge separations 480- 17900 980-15164 CERANIC COATINGS BOUNDARY LAYER FLOW Thermal barrier coatinGs for aircraft gas turbines Conformal mapping analysis of multielement [AIAA PAPER 80-0302] 480-18303 airfoils with boundary-layer correcticns CERANICS 14144 PAPER 80-00691 480-18261 Technologies conceived for the utilization of The aerodynamic forces on airship hulls ceramics in turboengines (RACA-184] 880-15039 IONEBA, TP NO. 1979-132] 480-20016 BOUNDARY LAYER SEPARATION Contact stress analycis of ceramic-to-metal A numerical approach to subsonic viscous-inviscid interfaces --- in gas turbine engines interaction tAD-A07 44911 980-144417 480-19070 CERTIFICATION Separation due to shock wave-turtulent boundary Plight certification of the Cessna 1U206G layer interaction amphibious floatplane IONEBA, TV NO. 1979-146] 480-20083 480-18 186 BOUNDARY LATER TRANSITION CESSNA AIRCRAFT Applications of modern hydrodynamics to Plight certification of the Cessna TU2O6G aeronautics. Part 1: Fundamental concepts and amphibious floatplane the most important theorems. Part 2: 480-18 186 Applications CB-46 HELICOPTER [RACA-116] 880-15034 CR-46 composite rotor blade flight stress survey BOUNDARY VALUE PROBLENS data. Volume 3: Plotted forward rotor blade Application of a higher order panel method to chord, torsion and absolute loads realistic supersonic configurations [40-4075612] 980-15077 14144 PAPER 79-02711] 480-17696 CHANNEL FLOW BOXES (CONTAINERS) Separation due to shock wave-turbulent boundary Air cargo container utilization optimization layer interaction through modeling (ONEBA, TV NO. 1979-146] 480-20083 480-2 0870 CHANNELS (DATA TEANSNISSION) BUFFETING An air traffic channel simulation by means of Plight testing of the buffeting behavior of combat ray-tracing techniques aircraft 980-14088 [ESA-TT-523] 880-14143 L-band measurements in the air traffic channel to BYPASSES characterize secondary radar systems Dynamic response of a Bach 2.5 axisymmetric inlet 880-14092 and turbojet engine with a poppet-value CBENICAL ATTACK controlled inlet stability bypass system when Comparative resistance of Beta-Si3N4 solid subjected to internal and external airflow solutions to nolten silicon attack transients 480-18062 [NASA-TP-1531] 880-114123 CHENICAL PROPERTIES The physical and chemical characterization of ten r military turbine engine lubricants (40-4074073] 880-15265 C-is AIRCRAFT CIRCUIT PROTECTION Quiet powered-lift propulsion An overvoltage safety system for direct current [NASA-CP.-2077] 880-15127 aircraft generators C-135 AIRCRAFT 480-19051 The effects of motion and g-seat cues on pilot CIVIL AVIATION simulator performance of three piloting tasks AEROPP - Bessage and data switching systems for [NASA-TP-1601] 980-15069 aeronautical operations CABINS 480-19 579 Recent developments in flight simulation techniques Shipping by air - Is the value of your time worth it 480-20907 480-20868 CALIBRATING Design study of a low cost civil aviation GPS Some practical aspects of the calibration of air receiver system data systems (NASA-CR-159176] 980-15062 480-18865 CLEAR AIR TURBULENCE Determination of the repeatability of PEC NASA technical advances in aircraft occupant safety flight tests for positics error calibrating clear air turbulence detectors, fire [AETE-PR-79/36] 880-14109 resistant materials, and crashworthiness CANARD CONFIGURATIONS [NASA-TM-80851] 4480-15060 Aerodynamic interaction on a close-coupled canard COAL wing configuration Nicrobial deterioration of hydrocarbon fuels from 980-15 175 oil shale, coal, and petroleum. 1: Exploratory CANNON FIBERS experiments The transfer of carbon fibers through a commercial [40-4073761] 980-14259 aircraft water separator and air cleaner COCKPITS tNASA-CR-159183] 980-14359 Vocabulary specification tor automatic speech CARGO AIRCRAFT recognition in aircraft cockpits Problems associated with cargo airplanes having 40-4073703] 980-14303 aft mounted engines COHERENT ACOUSTIC RADIATION [SAWN PAPER 1314] 480-20648 A study of partial coherence for identifying Air cargo container utilization optimization interior noise sources and paths on general through modeling aviation aircraft 480-20870 [NASA-TN-80197] 4480-15874 CASCADE CONTROL COLLISION AVOIDANCE A statistical method applied to pilot behavior Covariance simulation of BCAS - An aircraft analysis in multiloop systems collision avoidance system 480-1853 7 480-20915 CELESTIAL REFERENCE SYSTEBS Onboard collision avoidance system: Environmental Navigation error using rate of change of signal influence on the tracking algorithm reguirements tine of arrival from space vehicles 980-14 105 480-20904

4-9

COMBAT SUBJECT INDEX

CO MB AT COMPEESSINILITY EFFECTS Multiple tactical aircraft combat performance Reynolds number and compressibility effects on evaluation system dynamic stall of a NACA 0012 airfoil [AIAA PAPER 80-01893 680-18358 rAIRA PAPER 80-00103 680-18238 COMBUSTIBLE PLOW COMPRESSIBLE FLOW Mach 3 hydrogen external/base burning Reynolds number and compressibility effects on (AIAA PAPER 80-0280) 680-19311 dynamic stall of a NACA 0012 airfoil Dispersion of sound in a combustion duct by fuel rAIAA PAPER 80-0010) A80-18238 droplets and soot particles COMPRESSOR BLADES A80-20 953 Damping capacity of plastic compressor blades COMBUSTION CHAMBERS 680-19 868 Estimation of noise source strengths in a gas COMPRESSOR EFFICIENCY turbine combustor On the influence of steady state temperature and [6166 PAPER 80-0034) 680-18245 pressure distortion on the flow characteristics Effect of degree of fuel vaporization upon in an installed multistage jet engine compressor emissions for a premixed partially vaporized A80- 17 720 combustion system --- for gas turbine engines Flow in transonic compressors [RASA-TP-1582] 880-14125 [AIAA PAPER 80-0124) 680-18357 Quiet Clean Short-haul Experimental Engine COMPUTATIONAL FLUID DYNAMICS (QCSEE). Double-annular clean combustor Application of a higher order panel method to technology development report realistic supersonic configurations rEASA-CR-159483) 880-15121 rAIAA PAPER 79-0274] 680-17696 COMBUSTION PHYSICS Euler solutions for wing and wing-body combination Mach 3 hydrogen external/base burning at supersonic speeds with leading-edge separation [6166 PAPER 80-0280) 680-19311 [AIAA PAPER 80-0126] 680-18359 COMBUSTION PRODUCTS Analysis of transonic flow about harmonically Quiet Clean Short-haul Experimental Engine (QCSEF) oscillating airfoils and wings clean combustor test report [6166 PAPER 80-0149] 680-18367 [NASA-CR-134916] 890-15104 A numerical approach to subsonic viscous-inviscjd COMMAND AND CONTROL interaction A nonlinear cbserver/command generator tracker A80-19070 approach to the 88-97 helicopter gun turret Hybrid vortex method for lifting surfaces with control law design free-vortex flow 680-20879 [6166 PAPER 80-0070) A80-19307 COMMERCIAL AIRCRAFT Two dimensional aerodynamic interference effects A strapdown inertial reference system for on oscillating airfoils with flaps in ventilated commercial airline use in navigation and flight subsonic wind tunnels --- computational fluid control dynamics 680-17558 (NA5A-CR-3210) 880-14047 The transfer of catbon fibers through a commercial COMPUTER DESIGN aircraft water separator and air cleaner Analog aircraft weight and balance computer FNASA-CR-159183) 880-14359 [SANE PAPER 1283] A80-20631 Aircraft delays at major us airports can be reduced COMPUTER IFFORMATION SECURITY [P8-299442/4] 880-15061 The integrity of onboard computer programs: A COMMUNICATION CABLES solution Recent advances in fibre optics for high integrity 88 0-14028 digital control systems COMPUTER PROGRAMMING 88 0-14025 Tactical analysis of conflicts in an air traffic COMMUNICATION NETWORKS control system: Design and implementation of a AEROPP - Message and data switching systems for provisional model aeronautical operaticms 88 0-14072 690-19579 COMPUTER PROGRAMS COMPARISON A computer code to model swept wings in an Implementation of air traffic control radar adaptive wall transonic wind tunnel receivers with fast Fourier transform processors (AIAA PAPER 80-0156) 680-19287 880-14 086 The integrity of onboard computer proGrams: A COMPLEX SYSTEMS solution A method of evaluation of gas turbine engines 88 0-14028 680-20064 The avionics computer program: Practical COMPONENT RELIABILITY experiences with a methodology --- Mirage El and The CF6 jet engine performance improvement: new Nirage 200 aircraft front mount 880-14 037 [NAsA-CR-159639) 880-14127 Modification of axial compressor streamline COMPOSITE MATERIALS program for analysis of engine test data Damping capacity of plastic compressor blades [RASA-TN-79312] 880-14051 680-19868 A computerized method for calculating flutter Protective coatings for aircraft composites in characteristics of a system characterized by two nuclear environments degrees of freedom [AD-A074889) 880-14199 [NASA-TN-80153) 880-14055 Composite structural materials An adaptation and validation of a primitive [NASA-CR-162578) 880-15076 variable mathematical model for predicting the Quiet Clean Short-haul Experimental Engine (QCSER) flows in turbojet test cells and solid fuel Under-The-wing (UTR) composite nacelle subsystem ran jets test report --- to verify strength of selected A0-8074187) 880-14133 composite materials Linear systems analysis program, L22L1 (Qlfl. Volume [NASA-CR-135075] 880-15100 1: Engineering and usage Quiet Clean short-haul Experimental Engine (QCSEE) (RA5A-CR-2861] 880-14137 'Inder-The-wing (01W) composite nacelle Computer program to prepare airfoil characteristic [NAsA-CR-135352] 880-15119 data for use in helicopter performance COMPOSITE STRUCTURES calculations Feasibility of SiC compcsite structures for 1644 K (NA5A-TN-78627) 880-15031 (2500 F) gas turbine seal application Data reduction software for 10868-C flight test rNASA-CR-159597] 880-14122 evaluation Composite structural materials RASA-CR-162730] 880- 15064 [NASA-CR-162578) 880-15076 COMPUTER SYSTEMS DESIGN Quiet Clean short-haul Experimental Engine (QCSEE) Modular strapdown guidance unit with embedded under-the-wing engine composite fan blade design microprocessors report [AIAA PAPER 78-1239) 880-18534 [NASA-CR-135046] 880-15108

6-10

SUBJECT INDEX CONTROL SURFACES

Automation and air traffic control CONFERENCES 880-18722 Advances in Guidance and Control Systems Using Experience in producing software for the ground Digital 'Techniques station of a remotely piloted helicopter system AGABD-CP-272] 880-14017 880-14038 On radar in air traffic control --- conference, COMPUTER SYSTEMS PROGRAMS Rome, Jul. 1979 An assessment of and approach to the validation of (FUB-11-1979) 880-14065 digital flight control systems Quiet powered-lift propulsion 880-14036 (NASA-CP-2077] 880-15127 COMPUTER TECREIQUES Technical evaluation report on the 28th Guidance Adaptive allocation of decisionmaking and Control Panel Symposium on Advances in responsibility between human and computer in Guidance and Control Systems Using Digital ,nultitask situations Techniques 880- 18022 [AGARD-Afi-148] 880-15140 Recent developments in flight simulation techniques Low cost aircraft flutter clearance --- conference 880-20907 [AGARD-CP-278] N80-15141 An extension of engine weight estimation Aerodynamic characteristics of controls techniques to compute engine producticn cost con ferences (AD-A074454) 880-15135 [AGARD-CP-262] 880-15149 COMPUTERIZED DESIGN CONFIGURATION MANAGEMENT An analytical method of testing pavement strength Weight Integrated Sizing Evaluation /WISE/ - A A80- 17 998 tool for preliminary design 'The rational design of an airfoil for a high [SANE PAPER 1312] A80-20646 performance jet trainer CONFORMAL MAPPING [8188 PAPER 80-0328] 880-18317 Conformal mapping analysis of multielement A pre-design code for predicting engine airfoils with boundary-layer corrections acquisition costs [AIAA PAPER 80-0069] 880-18261 [8188 PAPER 80-0055] 880-19269 CONTOURS Assessment of analytic methods for the prediction Ron-contacting electro-optical contouring of of aerodynamic characteristics of arbitrary helicopter rotor blades bodies at supersonic speeds [ADA0'0806] 880-14111 (AIAA PAPEM 80-0071) 880-19308 CONTROL Weight Integrated Sizing Evaluation /WISE/ - A Linear systems analysis program, L22L1(QR). Volume tool for preliminary design 1: Engineering and usage (SANE PAPER 1312) 890-20646 (RASA-CR-2861 ] 880-14137 Optimized aerodynamic design prccess for subsonic Technical evaluation report on the 28th Guidance transport wing fitted with winglets --- wind and Control Panel Symposium on Advances in tunnel model Guidance and Control Systems Using Digital (NASA-CR-159180] 880-14054 Techniques Composite structural materials [AGARD-AR-148] 880-15140 [NASA-CB-162578) N80-15076 CONTROL CONFIGURED VERICLES COMPUTERIZED SIMULATION Redundancy management considerations for a Computer simulation of engine systems --- for control-configured fighter aircraft triplex aircraft design digital fly-by-wire flight control system 1AIAA PAPER 80-0051] 880-18253 880-14026 Regression techniques applied to parametric Control considerations for CCV fighters at high turbine engine simulations angles of attack [8188 PAPER 80-0053] 880-18255 880- 15160 Acoustic radiation from axisymmetric ducts - A Trajectory behaviour of a control configurated comparison of theory and experiment aircraft subjected to random disturbances [AIAA PAPER 80-0097) 880-18268 R80-15 171 Correlation of predicted longitudinal aerodynamic COITROL EQUIPMENT characteristics with full-scale wind tunnel data Aircraft torgue motors --- Russian book on the ATLIT airplane 880-19 199 IAIAA PAPER 80-0186] 880-18356 CONTROL SIMULATION Eultiple tactical aircraft combat performance A statistical method applied to pilot behavior evaluation system analysis in multiloop systems fAIAA PAPER 80-0189] 880-18358 880- 18 537 Code optimization for solving large 3D ERR problems Infrared sensor system performance simulations electromagnetic scattering by aircraft 880-20 90 0 structures Verification of digital autopilot microprocessor 880-19 764 hardware and software via hardware-in-the-loop A simple design synthesis method used to estimate simulation aircraft gross weight 880-20901 (SANE PAPER 1313] 880-20647 Recent developments in flight simulation techniques Computer simulation of an air cargo small package A80-20 907 sorting system A flight control system using the OATS architecture 880-20866 880-140 19 Covariance simulaticn of ECAS - An aircraft Ouiet clean Short-haul Experimental Engine (QCSEE) collision avoidance system over-the-wing engine and control simulation 880-20915 results Numerical simulation of supersonic inlets using a (NASA-CR-135049] R80-15114 three-dimensional viscous flow analysis CONTROL SURFACES (AIAA PAPER 80-0384] 880-20969 Comment on Handling quality criterion for heading Simulation of a surveillance and control system of control' surface traffic in an airport 880- 17 698 880-14 073 Applications of modern hydrodynamics to An air traffic channel simulation by means of aeronautics. Part 1: Fundamental concepts and ray-tracing technigues the most important theorems. Part 2: N80-14 088 Applications Pilot control through the TAFCOS automatic flight (RAcA-116] 880-15034 control system Aerodynamic characteristics of controls rNASA-TM-81152] 880-14138 conferences Quiet Clean Short-haul Experimental Engine (QCSEE) AGABD-CP-262) 880-15 149 under-the-wing engine simulation report 'Theoretical aerodynamic methods for active control rSASA-cR-134914] 880-15091 devices Computer simulation of engine systems 880-15150 [NASA-T8-79290) 880-15132

A-il

CONTROLLABILITY SUBJECT INDEX

A survey of experimental data on the aerodynamics CRACK PROPAGATION of controls, in the light of future needs Practical method of fatigue crack growth analysis 4480-15151 for damage tolerance assessment of aluminum Correlation of F-iS flight and wind tunnel test structure in fighter type aircraft control effectiveness [AIAA PAPER 80-0405] A80-18346 880-15 152 Model 540 rotor blade crack propagation Wind tunnel measurements and analysis of some investigation unusual control surfaces on two swept wing (80-8074734] 880-15081 fighter configurations CRACKING (FRACTURING) 880-15 155 Ref lection cracking of bituminous overlays for Problems of unsteady aerodynamics raised by the airport pavements: A state of the art use of control surfaces as active controls (AD-A073488) 880-141144 480-15 167 CRASH LANDING On the effects of gaps on control snrface Soil analyses and evaluations at the impact characteristics dynamics research facility for two full-scale 880-15176 aircraft crash tests CONTROLLABILITY (NASA-CB-159199] 880-15299 Pilot control through the TATCOS automatic flight CRATER lEG control system Atmospheric effects on Martian ejecta emplacement (NAsA-TM-81152] 880-14138 A80-20192 CONTROLLERS Soil analyses and evaluations at the impact Controllers for aircraft motion simulators dynamics research facility for two full-scale (AIAA PAPER 80-0050] 880-18252 aircraft crash tests COOLING SYSTEMS (NASA-CR-159199) 4180-15299 Thermal state of structural members o aircraft CROSS CORRELATION engines --- Russian bcok Guidance system position update by multiple 880-19 '4i 2 subarea correlation CORE FLOW 1.80-17518 Effect of the relative area of the flow core on CROSS COUPLING the performance of a hypersonic wind tunnel Effects of the aerodynamic cross-coupling and 8130- 17673 lateral acceleration derivatives on airplane Quiet Clean Short-haul Experimental ingine dynamic characteristics (QCSEE). Aerodynamic and aeromechanical [AIAA PAPER 80-0170] 880-17699 performance of a 50.8 cm (20 inch) diameter 1.34 CROSS FLOW PR variable pitch fan with core flow An experimental study of the structure and rNASW-CR-135017] 880-15087 acoustic field of a jet in a cross stream CORROSION TESTS Ames 7-ft by 10-ft wind tunnel tests Comparative resistance of Beta-Si3N4 solid [NASA-CR-162 1464] 880-15871 solutions to molten silicon attack CRUDE OIL 880- 18062 Microbial deterioration of hydrocarbon fuels from COSMOS SATELLITES oil shale, coal, and petroleum. 1: Exploratory The Russian satellite navigation system experiments 880-20 982 rAD-8073761] 4480-14259 COST ANALYSIS CRUISING FLIGHT shipping by air - Is the value of your time worth it Exploratory studies of the cruise performance of 880-20868 upper surface blown configuration: Experimental Problems related to the design and construction of program, high-speed force tests a radar network (NASA-CR-15913 4$] 880-15070 880- 14 06 6 Exploratory studies of the cruise performance of Avionics installation (AVSTALL) Cost model for upper surface blown configurations: user equipment of NAVSTAR global positioning Experimental program, high-speed pressure tests system fNAsA-CR-159135] 880-15071 [AD-A073681] 880-14106 13xploratory studies of the cruise pertornance of COST ESTIMATES upper surface blown configurations: Program A pre-design code tot predicting engine analysis and conclusions acquisition costs [RLSA-CR-159136] 880-15072 (8188 PAPER 80-0055] 880-19269 CRYSTAL OSCILLATORS The nodular life cycle cost model - An overview Investigations of the optimal configuration of ISAWE PAPER 1290] 880-20636 high-stability quartz oscillators for aircraft Application of parametric weight and cost and missiles estimating relationships to future transport A80-19 990 aircraft CURVATURE (SANE PAPER 1292] 880-20637 Sonic-boom wave-front shapes and curvatures Study of turboprop systems reliability and associated with maneuvering flight maintenance costs (NASA-TP-1611l 880-14045 tNASA-cR-1351921 880-14129 An extension of engine weight estimation techniques to compute engine production cost D (AD-8074454] 880-15135 DASSAULT AIRCRAFT COST REDUCTION The avionics computer program: Practical The modular life cycle cost model - An overview experiences with a methodology --- Mirage Fl and (SANE PAPER 12901 880-20636 Mirage 200 aircraft - COSTS 88 0-14037 An extension of engine weight estimation DATA ACQUISITION techniques to compute engine production cost Concerning the information efficiency of (AD-A074454] 880-15135 aerodynamic experiments COUPLING A80-1767 1 Analysis of rotor-fuselage coupling and its effect Analysis of low-speed helicopter fli q ht test data on rotorcraft stability and response tAD-A074141] 880-15079 880-17716 DATA BASES COVARIANCY Aerodynamic data base users guide Covariance simulation of SCAR - An aircraft 80-8074 4448] 88 0-15983 collision avoidance system DATA PROCESSING 880- 20915 A distributed processing system for radar data COWLINGS presentation Quiet Clean Short-Haul Experimental Engine (QCSEE) 880-14 075 Under-The-Wing (TJTW) graphite/PRR cowl development INASA-CP-135279] 880-114119

A-i 2

SUEJECT INDEX DRAG REDUCTION

DATA PROCESSING TERHINALS DIGITAL COMPUTERS APROPP - Hessage and data switching systems for An observer system for sensor failure detection aeronautical operations and isolation in digital flight control systems #80- 19579 880-14023 DATA RECORDERS DIGITAL FILTERS Application of the SIRS concept to Navy helicopters Filtering of synthetic radar data systems analysis of flight data recorders of 880-14076 flight conditons of helicopters for structural DIGITAL NAVIGATION analysis Verification of digital autopilot microprocessor [80-8074801) 880-15030 hardware and software via hardware-in-the-loop DATA SEDUCTION simulation Excitation and analysis technique for flight 880- 20 90 1 flutter tests DIGITAL SYSTEMS IEBB-TTP-1446(o) ] 880-14140 Redundancy management considerations for a Data reduction software for LORAN-C flight test control-configured fighter aircraft triplex evaluation digital fly-by-wire flight control system INASA-CR-162730] 880-15064 N80-14026 DATA STORAGE ailure detection, isolation and indication in Aerodynamic data base users guide highly integrated digital guidance and control rAD-A074448] 880-15983 system DATA SYSTEMS 880-14 021 Some practical aspects of the calibraticn of air An assessment of and approach to the validation of data systems digital flight control systems 880-18865 880-14036 DECISION MAEING Integration of flight and fire control --- systems Adaptive allocation of decisionmaking analysis of digital controlled integrated flight responsibility between human and computer in and fire control systems mnititask situations 880-14 043 880-18022 Digital system for dynamic turbine engine blade DEGREES OF FREEDOM displacement measurements A computerized method for calculating flutter rNASA-T8-81382] 880-14113 characteristics of a system characterized by two Loran digital phase-locked loop and RE front-end degrees of freedom system error analysis [NASA-TN-80153) 880-14055 [NASA-CR-162731] 880-15065 DEICING ruiet Clean Short-haul Experimental Engine (QCSEE) Aircraft anti-icing/do-icing under-the-wing engine digital control system [AD-8074128] 880-15078 design report DELAY (NASA-CR-1349201 880-15090 Aircraft delays at major US airports can he reduced Quiet Clean Short-haul Experimental Engine (QCSEE) [P8-299442/8 880-15061 over-the-wing control system design report DELTA WINGS [RASA-CR-135337] 880-15092 Analytical investigation of aerodynamic DIGITAL TECHNIQUES characteristics of highly swept wings with Advances in Guidance and Control Systems Using separated flow Digital Techniques 880-17697 IAGARD-CP-272] 880-1(4017 Investigation of leading-edge devices for drag State of the art for digital avionics and reduction of a 60-deg. delta wing at high angles controls, 1978 of attack 880-14018 18188 PARR 80-0310] #80-18309 A flight control system using the DAIS architecture Euler solutions for wing and wing-body combination 880-140 19 at supersonic speeds with leading-edge separation Trends in digital data processing and system [8188 PAPER 80-0126] 880-18359 architecture --- avionics applications Streamwise development of the flow over a delta wing 880- 1'4 020 [8188 PAPER 80-0200] #80-18376 Recent advances in fibre optics for high integrity DENSITY MEASUREMENT digital control systems Air traffic density and distribution measurements 880-14025 tAj3-&073229] 880-14064 Technical evaluation report on the 28th Guidance DESIGN ANALYSIS and Control Panel Symposium on Advances in Weight Integrated Sizing Evaluation /WISE/ - A Guidance and Control Systems Using Digital tool for preliminary design Techniques [SANE PAPER 1312] 880-20646 (AGARD-AR-148] 880-15180 Problems related to the design and construction of DIRECT LIFT CONTROLS a radar network In-flight measured characteristics of combined 880-14 066 flap-spoiler direct lift controls Design study for ATA vacuum system aperture 880-15 165 [TTCRL-150501 880-15182 DISPLAY DEVICES DESTRUCTIVE TESTS ATC and the airborne traffic-situation display Comparative resistance of Eeta-Si38'I solid 880-18 124 solutions to molten silicon attack Infrared sensor system performance simulations 880-18062 880-20900 DETERIORATION Visual displays for air traffic control data Microbial deterioration of hydrocarbon fuels from 880-14 077 oil shale, coal, and petroleum. 1: Exploratory Design study of a low Cost civil aviation GPS experiments receiver system IAD-A073761] 880-14259 [NASA-CR-159176] 880-15062 DETONATION WAVES Effects of varying visual display characteristics Oblique detonation wave ramjet of the T-UG, a T-37 flight simulator [RASA-CR-159192] 880-14131 [80-8071410] 880-15180 DIFFUSERS DOPPLER RADAR An analytical and experimental study of a short Target tracking using Doppler-information in S-shaped subsonic diffuser of a supersonic inlet sensor oriented coordinates with a three [8188 PAPER 80-0386] 880-20970 dimensional array radar DIGITAL COMMAND SYSTEMS [RFPT-2701 880-114325 Roll control by digitaiiy controlled segment DRAG REDUCTION spoilers Propulsion/airframe integration considerations for 880-15 156 high altitude hypersonic cruise vehicles [AIAA PAPER 80-0111] 880-18272

8-13

DRONE AIRCRAFT SUBJECT INDEX

Investigation of leading-edge devices for drag EJECTORS reduction of a 60-deg. delta wing at high angles Recent development of a jet-diffuser ejector of attack (AIAA PAPER 80-0231) 480-18277 tAIAA PAPER 80-0310) A80-18309 ELASTIC PROPERTIES The minimum induced drag of aerofoils Uetermination of the stress intensity factor of (NACA-121) 880-15038 composite structural members Direct side force and drag control with the aid of ABO-17 958 pylon split flaps ELASTIC WAVES 880-15163 Yet engine combustion noise - Pressure, entropy DRONE AIRCRAFT and vorticity perturbations produced by unsteady Propulsion options for the HI SPO'T long endurance combustion or heat addition drone airship A80-20 151 [40-4074595] 880-14132 ELECTRIC POWER SUPPLIES DROPS (LIQUIDS) Centralized ground power systems conserve energy Dispersion of sound in a combustion duct by fnel 480-18 000 droplets and Soot particles ELECTRICAL RESISTIVITY 880-20953 Investigation of the wear debris content in oil by DUCTED PAN ENGINES measurements of the reluctance and eddy current The analysis of sound propagation in jet engine loss in an electric circuit ducts using the finite difference method 480-19053 (AD-A0742331 880-14853 BLECTRO-OPTICS DUCTED FANS Ron-contacting electro-optical contouring of Acoustic analysis of aft noise reduction helicopter rotor blades techniques measured on a subsonic tip speed 50.8 [AD-4070806] 880-14111 cm (twenty inch) diaseter fan --- quiet engine ELECTROMAGNETIC INTERFERENCE program Performance evaluation methods of a secondary [NASA-CP-13 148911 880-15102 radar network DUCTED PLOW 880-14068 Acoustic radiation from axisymmetric ducts - A ELECTROMAGNETIC SCATTERING comparison of theory and experiment Code optimization for solving large 3D EN? problems (4144 PAPER 80-0097] 480-18268 electromagnetic scattering by aircraft Dispersion of sound in a combustion duct by fuel structures droplets and soot particles 480- 19 764 480-20953 ELEVATORS (CONTROL SURFACES) An analytical and experimental study of a short Some investigations concerning the effects of gaps S-shaped subsonic diffuser of a supersonic inlet and vortex generators on elevator efficiency and [AIAA PAPER 80-0386] 480-20970 of landing flap sweep on aerodynamic DYNAMIC CHARACTERISTICS characteristics On the dynamics of compressor surge 880-15178 #80- 17900 ENERGY CONSERVATION Dynamic identification of light aircraft Centralized ground power systems conserve energy structures and their flutter certification A 80-18000 • N80-15145 NASA broad-specification fuels combustion DYNAMIC CONTROL technology program: Status and description Theoretical aerodynamic methods for active control [NASA-TM-79315] 880-14126 devices Impact of new instrumentation on advanced turbine 880-15 150 research A survey of experimental data on the aerodynamics rNASA-TN-79301] 880-15133 of controls, in the light of future needs ENERGY POLICY 480-15151 Microbial deterioration of hydrocarbon fuels from AFEDL experience in active control technology oil shale, coal, and petroleum. 1: Exploratory 880-15 159 experiments Pin design with AC't in the presence of strakes [#D-A073761] 880-14259 880-1516 1 ENGINE CONTROl. Control integration technology impact --- as a Integrated circuit characteristics at 260 C for basis for improving the combat effectiveness of aircraft engine-control applications all tactical aircraft 480-20112 880-15 162 Quiet Clean Short-haul Experimental Engine (QCSEE) DYNAMIC RESPONSE under-the-wing engine digital control system Linear systems analysis program, 1224(Q8). Volume design report 1: Engineering and usage [NASA-CR-1389201 880-15090 [NASA-CR-2861] 880-14137 Quiet clean Short-haul Experimental Engine (QCSEE) Unsteady flow and dynamic response analyses for under-the-wing engine simulation report helicopter rotor blades tNASA-CR-1349111) 880-15091 [NASA-CS-159190] 880-111355 Quiet clean Short-haul Experimental Engine (QCSEE) DYNAMIC STRUCTURAL ANALYSIS over-the-wing control system design report Analysis of rotor-fuselage coupling and its effect tRASA-C8-135337) 880-15092 on rotorcraft stability and response ENGINE DESIGN 480-17716 Preparing aircraft propulsion for a new era in Gas turbine carcase and accessory vibration - energy and the environment Problems of measurement and analysis 48 0-17737 A80- 17730 Computer simulation of engine systems --- for Analyses and tests of the 8-1 aircraft structural aircraft design mode control system [AIAA PAPER 80-0051) A80-18253 rRAsA-cR-1448a7] 880-15073 Multi-variable cycle optimization by gradient methods --- for variable-cycle engines (4144 PAPER 80-0052] 480-18254 E Regression techniques applied to parametric E- IIA AIRCRAFT turbine engine simulations Trajectory behaviour of a control configurated AIAA PAPER 80-00531 480-18255 aircraft subjected to random disturbances Plow in transonic compressors 880-15171 [AIAA PAPER 80-0124] 480-18357 ECONOMIC FACTORS Technology of the Rolls-Royce 88211 engine The next supersonic transport #80-18864 480- 20214 A pre-desigm code for predicting engine ECONOMICS acquisition costs The economics of air traffic control [AIAA PAPER 80-0055] 480-19269 A80- 18723

A-ill S?JB.IECT INDEX ENGINE TESTS

Installation effects on cycle selection for small Quiet Clean Short-Haul Experimental Engine turbo-fan engines (QSCEE) . Preliminary analyses and design [8188 PAPER 80-0106] 880-19280 report, volume 1 Technologies conceived for the utilization of rNASA-CR-134838] 1380-15123 ceramics in turboengines Quiet Clean Short-Haul Experimental Engine tONERA, TP NO. 1979-132] 880-20076 (QCSEE). Preliminary analyses and design Quiet, Clean, Short-Haul, Experimental Engine report, volume 2 (QCSEE) Under-The-Wing (01W) engine acoustic [NASA-CR-134839] 3380-15124 design Quiet Clean Short-Haul Experimental Engine (QCSEE) [NASA-CR-135267] N80-114117 Over-The-Wing (01W) propulsion system test Quiet, Clean, Short-Haul Experimental Engine report. Volume 1: Summary report (QCSEE) Over-The-Wing (CTW) engine acoustic design [NASA-CR-135323) 1380-15125 [NPSA-CR-135268) N80-14118 Quiet Clean Short-Haul Experimental Engine (QCSEE) Quiet Clean Short-Haul Experimental Engine (QCSEE) Over-The Wing (01W) propulsion system teat Under-The-Wing (01W) graphite/PNR cowl development report. Volume 3: Nechanical performance [NASA-CB-135279] 1380-14119 [NASA-CR-135325) 1380-15126 NASA broad-specification fuels combustion An extension of engine weight estimation technology program: Status and description techniques to compute engine production cost [NASA-TR-79315] 1380-14126 t AD-A0733454] 3380-15135 Oblique detonation wave ramjet ENS composites for advanced gas turbine engine rNASA-CR-159192) 1380-14131 components Quiet Clean Short-haul Experimental Engine (QCSEE) [80-8074287) 1380-15137 Over The Wing (01W) design report ENGINE MONITORING INSTRUMENTS rNASA-CR-134848] 1380-15086 Experimental investigation of the characteristics Quiet Clean Short-haul Experimental Engine of pneumatic transfer lines (QCSEE) . Core engine noise measurements 880-19052 [NASA-CR-135160] 1380-15093 ENGINE NOISE Quiet Clean Short-haul Experimental Engine (QCSEE) Estimation of noise source strengths in a gas Under-The-Wing (01W) engine composite nacelle turbine combustor test report. Volume 1: Summary, aerodynamic [8188 PAPER 80-0034] 880-182335 and mechanical performance Comparison of inlet suppressor data with [NASA-CE-159471 I 1380-15094 approximate theory based on cutoff ratio Quiet Clean Short-haul Experimental Engine (QCSEE) (AIAA PAPER 80-0100] 880-20964 preliminary over-the-wing flight propulsion Quiet, Clean, Short-Haul, Experimental Engine system analysis report (QCSEE) Under-The-Wing (01W) engine acoustic [NASA-CN-135296] 7380-15095 design Quiet Clean Short-haul Experimental Engine tNASA-CR-135267] W80-133117 (QCSEE) . Composite fan frame subsystem test Quiet, Clean, Short-Haul Experimental Engine report (QCSEE) Over-The-Wing (01W) engine acoustic design [NASA-CR-135010] 1380-15098 [NASA-CR-135268] 1380-14118 Quiet Clean Short-haul Experimental Engine (QCSEE) Investigation of noise hazards in the engine teat main reduction gears test program cell, CEB Baden-Soellingen [NASA-CR-134669] 1380-15103 (AD-A074391) 1380-1141137 Quiet Clean Short-haul Experimental Engine (QCSEE) Applications of diffraction theory to aeroacoustics clean combustor test report aircraft noise [NASA-CR-13 31916) 1380-15104 1380-14870 Quiet Clean Short-haul Experimental Engine (QCSEP) Quiet Clean Short-haul Experimental Engine main reduction gears detailed design report (QCSEE) . Core engine noise measurements [NASA-CR-134872] 1380-15106 [ NASA-CR-135160 ] 3380-15093 Quiet Clean Short-haul Experimental Engine ENGINE PARTS (QCSEE) : Hamiltcn Standard cam/harmonic drive Engine component improvement program - Performance variable pitch fan actuation system detail improvement design report [AIAA PAPER 80-0223] 880-19300 ENASA-CN-134852] 1380-15107 Thermal state of structural members of aircraft Quiet Clean Short-haul Experimental Engine engines --- Russian book (QCSEE): The aerodynamic and mechanical design 880-193412 of the QCSEE under-the-wing fan Advanced technology effects on V/STOL propulsive rNASA-CR-135009] 1380-15100 system weight Quiet Clean Short-haul Experimental Engine (QCSEE) [SAWE PAPEI4 1300] 880-20640 U1W fan preliminary design Preliminary weight estimation of engine section rNASA-CR-134842] 1380-15111 structure Quiet Clean Short-haul Experimental Engine rSAWF PAPER 1311] A80-20645 (QCSEE) : The aerodynamic and preliminary Quiet Clean Short-haul Experimental Engine (QCSEE) mechanical design of the QCSEE 01W fan under-the-wing engine composite fan blade design [NASA-CR-1348411 1380-15112 report Quiet Clean Short-haul Experimental Engine (QCSEE) tNASA-CR-1350461 1380-15108 under-the-wing engine composite fan blade design ENGINE TESTS [NASA-CR-134840) 1380-15113 Discontinuous registration of industrial Quiet Clean Short-haul Experimental Engine (QCSEE) radiographs using profile analysis and piecewise over-the-wing engine and control simulation correlation techniques results 880-17 521 INASA-CP-1350491 1380-151133 Gas turbine carcase and accessory vibration - Quiet Clean Short-Haul Experimental Engine (QCSEE) Problems of measurement and analysis ball spline pitch-change mechanism whirligig 880-17730 test report A method of evaluation of gas turbine engines [NASA-CE-1353531] 1380-15115 880-20064 Quiet Clean Short-haul Experimental Engine (QCSEE) Scale model performance test investigation of Under-The-Wing (171W) boiler plate nacelle and exhaust system mixers for an EmergE Efficient core exhaust nozzle design report Engine /E3/ propulsion system INASA-CR-135008] 7380-15116 tAIAA PAPER 80-0229] 880-20968 Quiet Clean Short-haul Experimental Engine (QCSEE) Nodification of axial compressor streamline whirl test of cam/harmonic pitch change program for analysis of engine test data actuation system (NASA-1N-79312) 1380-14051 INASA-CP-135140] 38O-15117 Quiet Clean Short-Haul Experimental Engine (QCSEN) Quiet Clean Short-haul Experimental Engine Over-The-Wing (01W) propulsion system test (QCSEE) . Double-annular clean combustor report. Volume 2: Aerodynamics and performance technology development report engine performance tests to define [NASA-CP-159483] 1380-15121 propulsion system performance on turbofan engines CNASR-CR-135324] 7380-14120

8-15

ENTROPY SUBJECT INDEX

Investigation of noise hazards in the engine test OOiet Clean Short-haul Experimental Engine (QCSEE) cell, CPB faden-Soellingen (NASA-CR-159473) 880-15120 [AD-A074391] 880-14147 EXHAUST NOZZLES Quiet Clean Short-Haul Experimental Engine (QCS!?) An experimental model investigation of turbofan Over-The-Ning (OTW) propulsion system test engine internal exhaust gas mixer configurations report. Volume 1: Summary report [AIAA PAPER 80-0228] 880-19302 [NASA-CR-135323] 880-15125 Assessment at full scale of exhaust nozzle-to-wing ENTROPY size on STOL-OTN acoustic characteristics Jet engine combustion noise - Pressure, entropy 880-20952 and vorticity perturbations produced by unsteady Scale model performance test investigation of combustion or heat addition exhaust system mixers for an Fnergy Efficient #80-20151 Engine /83/ propulsion system ENVIRONRERT PROTECTION [ATAA PAPER 80-0229] 880-20968 Preparing aircraft propulsion for a new era in Turbojet-exhaust-nozzle secondar y -airflow pumping energy and the environment as an exit control of an inlet-stability bypass 880-17737 system for a Each 2.5 axisymmetric ENVIRONMENTAL NONITORING mixed-compression inlet --- Lewis 10- by 10-ft. A light aircraft camera Pod - The Enviro-Pod supersonic wind tunnel test 880-20 251 [RASA-TP-1532] 880-14128 ENFIRONNENTAL TESTS Quiet Clean Short-haul Experimental Engine (QCSEF) Climatic chamber testing aircraft, engines u nder-The-Wing (UTW) boiler plate nacelle and armament and avionics; Test operations procedure core exhaust nozzle design report environmental test chambers and facility for [NASA-CR-135008] 880-15116 testing aircraft construction materials and EXHAUST SISTERS engines Static test-stand performance of the TP-102 (80-80740491 N80-15181 turbofan engine with several exhaust EQUATIONS OF NOTION configurations for the Quiet Short-Haul Research Formulation of coupled rotor/fuselage equations of Aircraft (0588) motion (NASA-TP-1556] 880-14121 #80-17717 EXPERINENTAL DESIGN Ringed vehicle equations of motion Concerning the information efficiency of [8188 PAPER 80-0364] 880-18336 aerodynamic experiments ERROR ANALYSIS 880-17671 Navigation error using rate of c5ange of signal An experimental model investigation of turbofan time of arrival from space vehicles engine internal exhaust gas mixer configurations 880-20908 [AIAA PAPER 80-0228) 880-19302 Tactical analysis of conflicts in an air traffic EXTERNALLY BLOWN FLAPS control system: Design and implementation of a The YC-14 upper surface blown flap: A unique provisional model control surface 880-14 072 N80-15 157 Antireflect ion techniques for detecting false tracks in air traffic surveillance with secondary radar F 880-14 100 F-15 AIRCRAFT Determination of the repeatability of PEC Application of finite element analysis to flight tests for position error calibrating derivation of structural weight [AETE-PR-79/36i 880-14109 [SANE PAPER 1271] A80-20€27 Loran digital phase-locked loop and HP front-end Correlation of F-is flight and wind tunnel test system error analysis control effectiveness [NASA-CB-162731] 880-15065 880-15 152 ERROR DETECTION CODES P-16 AIRCRAFT Pailure detection, isolation and indication in Simulator study of stall/post-stall highly integrated digital guidance and control characteristics of a fighter airplane with system relaxed longitudinal static stability --- P-16 R80-14 027 [NASA-TP-1538) 880-14136 ESCAPE SYSTENS P-18 AIRCRAFT Aeronautical systems technology needs: Escape, Designing to life cycle cost in the Hornet program rescue and survival [SANE PAPER 1293) 880-20638 [ 80-8074906) 880-14061 F-104 AIRCRAFT ESTINATING Stability and control aspects of the CCV-8104G A simple design synthesis method used to estimate I MBB-UPE-i447 (0)1 880-14141 aircraft gross weight FAIL-SAFE SYSTENS [SANE PAPER 1313] 880-20647 Failure detection, isolation and indication in EXHAUST DIFFUSERS highly integrated digital guidance and control Recent development of a jet-diffuser ejector system [AIAA PAPER 80-0231] 880-18277 880-14027 EXHAUST ENISSION FAILURE Exhaust emission reduction for intermittent Automatic recovery after sensor failure onboard combustion aircraft engines 880- 14028 [NASA-CR-159757] 880-14130 PAR FIELDS EXHAUST FLOE SINULATION Rotational noise of helicopter rotors Scale model performance test investigation of 880-17718 exhaust system mixers for an Energy Efficient Comparison of inlet suppressor data with Engine /83/ propulsion system approximate theory based on cutoff ratio IAIAA PAPER 80-0229] 880-20968 [AIAA PAPER 80-0100] 880-20964 EXHAUST GASES FATIGUE (NATERIALS) An experimental nodel investigation of turbofan Review of investigations into aeronautics related engine internal exhaust gas mixer configurations fatigue Federal Republic of Germany [AIAA PAPER 80-02281 #80-19302 [LRF-S-142] 880-14422 Dispersion of sound in a combustion duct by fuel FATIGUE LIFE droplets and soot particles Fatigue life prediction of a bonded splice joint #80-20953 (AIAA PAPER 80-0305] 880-18306 Effect of degree of fuel vaporization upon Practical method of fatigue crack growth analysis emissions for a premixed partially vaporized for danage tolerance assessment of aluminum combustion s y stem --- for gas turbine engines structure in fighter type aircraft [NASA-TP-1582] 880-14125 (8188 PAPER 80-0405] A80-18346 Quiet Clean Short-haul Experimental Engine (QCSEE) clean combustor test report (NASA-CR-134916] 880-15108

8-16

SUBJECT INDEX FLIGHT CONDITIONS

FATIGUE TESTS The analysis of sound propagation in jet engine Practical method of fatigue crack growth analysis ducts using the finite difference method for damage tolerance assessment of aluminum rAD-A074233) 880-11*853 structure in fighter type aircraft A users guide for 8344: A program using a finite F 8188 PAPER 80-0405] 880-18346 difference method to analyze transonic flow over Nodel 540 rotor blade crack propagation oscillating airfoils invest igat ion (NASA-cR-159141] 880-15052 [80-807473*11 1*80-15081 FINITE ELERENT NETBOD FEASIBILITY ANALYSIS Application of finite element analysis to Automatic systems for airport surface mobile media derivation of structural weight surveillance based on the use of secondary media (SANE PAPER 1271) 880-20627 880-14104 FINNED BODIES FEEDBACK CONTROL 'in design with ACT in the presence of strakes Design criteria for optimal flight control systems 880-15 16 1 study of optimal flight control systems FIRE CONTROL engineering for feedback control A nonlinear observer/command generator tracker tAD-A0740921 880-1513° approach to the 18-97 helicopter gun turret FIBER CONPOSITES control law design FRS composites for advanced gas turbine engine 880- 20 87 9 components Integration of flight and fire control --- systems (AD-A074287] 880-15137 analysis of digital controlled integrated flight FIBER OPTICS and fire control systems Recent advances in fibre optics for high integrity N$0-UOLI3 digital ccntrol systems Control integration technology impact --- as a 880-14025 basis for improving the combat effectiveness of FIGHTER AIRCRAFT all tactical aircraft Experimental determination of pure rotary 880-15 162 stability derivatives using curved and rolling FIREPROOFING flow wind tunnel NASA technical advances in aircraft occupant safety (8188 PAPER 80-0309] 880-18308 clear air turbulence detectors, fire Effects of non-planar strake-wing on the vortex resistant materials, and crashworthiness lift characteristics of a twin-jet fighter (NASA-TN-80851] 880-15060 con figuration FLANNABILITY (8188 PAPER 80-0329] 880-18318 Aircraft fuel system simulator tests with Enhanced departure/spin recovery of fighter antimisting kerosene (jet A fuel with P8-9 aircraft through control of the forebody vortex additive) --- flammability tests orientation [AD- 8073237] 880-14256 [8188 PAPER 80-01131 A80-18352 FLAPPING HINGES Nultiple tactical aircraft combat performance Effects of primary rotor parameters on flapping evaluat ion system dynamics (AIAA PAPER 80-0189] 880-18358 [NASA-TP-1431) 880-15138 Redundancy management considerations for a FLAPS (CONTROL SURFACES) control-configured fighter aircraft triplex Direct side force and drag control with the aid of digital fly-by-wire flight control system pylon split flaps 880- 14 026 880-15 163 High angle of attack characteristics of different In-flight measured characteristics of combined fighter configurations flap-spoiler direct lift controls [NBB-T1F!-1l*t*3(0) 1 880-14058 880-15 165 Pliqht testing of the buffeting behavior of combat Some investigations concerning the effects of gaps aircraft and vortex generators on elevator efficiency and [ESA-TT-523] 880-14143 of landing flap sweep on aerodynamic Wind tunnel measurements and analysis of some characteristics unusual control surfaces on two swept wing 880-15 178 fighter configurations FLEXIBLE BODIES 880- 13155 Surface conforming thermal/pressure seal --- for Flaperon control: The versatile surface for control devices in space vehicles fighter aircraft (NASA-cASE-IISc-18422-1 I N80-141*00 880-15 158 FLEXIBLE WINGS Control considerations for C(V fighters at high Analyses and tests of the 8-1 aircraft structural angles of attack mode control system 880-15 160 7IASA-CR-144887] 880-15073 Yin design with ACT in the presence of strakes FLIGHT CHARACTERISTICS 880- 15161 Designing light airplanes --- Russian book Wind tunnel investigation of controls for DY on a A80-191*11* fighter-type configuration of higher angles of Acoustic considerations of flight effects on jet att ack noise suppressor nozzles 880-15166 (AIAA PAPER 80-0164] 880-20965 Forebody vortex blowing: *1 novel control concept Investigation of the oscillatory and flight to enhance departure/spin recovery behavior of rotor systems in relation with characteristics of fighter and trainer aircraft atmospheric turbulence 880-15172 RB YG-YB 81-79-5] 880-14 142 FILE COOLING Comparison of international tlutter requirements Optimization of turbine nozzle cooling by and flutter freedom substantiation of light combining impingement and film injection aircraft in the USA FAIAA PAPER 80-0299] 880-19316 880-15142 Therino-mechanical stress analysis of advanced Control integration technology impact --- as a turbine blade cooling configuration basis for improving the combat effectiveness of [AD-A074098] 880-15136 all tactical aircraft FINITE DIFFERENCE THEORY 880-15 162 Summary of advanced methods for predicting high FLIGHT CONDITIONS speed propeller performance Application of the SIRS concept to Navy helicopters [AIAA PAPER 80-0225] 880-20966 systems analysis of flight data recorders of An investigation of several factors involved in a flight conditons of helicopters for structural finite difference procedure for analyzing the analysis transonic flow about harmonically oscillating [AD-A074801] N8O-15030 airfoils and wings [NASA-CR-159143] 880-14056

8-17

FLIGHT COETHOL SUB3ECT INDEX

FLIGHT CONTHOL Determination of the repeatability of PEC A strapdown inertial reference system for flight tests for position error calibrating commercial airline use in navigation and flight [AETE-PR-79/36] 880-14109 control Preliminary test results of a flight management #80-17558 algorithm for fuel conservative descents in a An integrated strapdown guidance and control time based metered traffic environment system for launch vehicle application flight tests of an algorithm to minimize fuel #80-17 559 consumption of aircraft based on flight tine Adaptive allocation of decisionnaking [NASA-TN-80194] 880-14114 responsibility between human and computer in Flight testing of the buffeting behavior of combat nultitask situations aircraft A80-18022 (ESA-TT-523] 880-14143 Advances in Guidance and Control Systems Using Data reduction software for LORAN-C flight test Digital Techniques evaluation (AGARD-CP-272) 880-14017 [NASA-CB-162730] 880-15064 State of the art for digital avionics and CH-46 composite rotor blade flight stress survey controls, 1978 data. Volume 3: Plotted forward rotor blade 880-19 018 chord, torsion and absolute loads A flight control system using the DAIS architecture [#0-4075612] 880-15077 880-18019 Analysis of low-speed helicopter flight test data An observer system for sensor failure detection (AD-A0744141] 880-15079 and isolation in digital flight control systems 34-64 circulation control wing contractor tlight 880-18023 demonstration Automatic recovery after sensor failure onboard [AD-A074888] 880-15080 880-14024 Correlation of F-is flight and wind tunnel test Recent advances in fibre optics for high integrity control effectiveness digital control systems 880-15152 880-114025 PLIGHT TINE Integration of flight and fire control --- systems Preliminary test results of a flight management analysis of digital controlled integrated flight algorithm for fuel conservative descents in a and fire control systems time based metered traffic environment 880- 144 043 flight tests of an algorithm to minimize fuel Design criteria for optimal flight control systems consumption of aircraft based on flight time study of optimal flight control systems [NASA-TN-80194] 880-14114 engineering for feedback control FLIGHT VEHICLES [AD-A074092] 880-15139 hinged vehicle equations of motion Plight control and configuration design [4144 PAPFR 80-0364] #80-18336 considerations for highly maneuverable aircraft PLOW CHABACTEBISTICS 880-15 154 On the influence of steady state temperature and FLIGHT PATHS pressure distortion on the flow characteristics Constrained optimum trajectories with specified in an installed multistage jet engine compressor range #80-17724 480-18538 Separation due to shock wave-turbulent boundary FLIGHT BECORDEBS layer interaction Application of the SIRS concept to Navy helicopters [ONFRA, TP NO. 1979-146] #80-20083 systems analysis of flight data recorders of FLOW DISTORTION flight conditons of helicopters for structural On the influence of steady state temperature and analysis pressure distortion on the flow characteristics (AD-A074801] 880-15030 in an installed multistage jet engine compressor FLIGHT SAFETY A80-17724 An evaluation of the bird/aircraft strike hazard FLOW DISTRIBUTIOI at Barksdale Air Force Base, Louisiana (SAC) Improved numerical simulation of high speed inlets [AD-A074390] 880-14063 using the Navier-Stokes equations FLIGHT SI!ULATION [AIAA PAPER 80-0383] #80-18340 Computer simulation of engine systems --- for Flow in transonic compressors aircraft design AIAA PAPPE 80-0124) A80-18357 (AIAA PAEB 80-0051] #90-18253 Streamvise development of the flow over a delta wino Recent developments in flight simulation techniques .AIAA PAPER 80-0200] A80-18376 #8 0-2 0 907 Theoretical study of aerodynamic characteristics Covariance simulation of ECAS - An aircraft of wings having vortex flow collision avoidance system [8#SA-CR-159184) 880-14053 #80-20915 An adaptation and validation of a primitive Simulator study of stall/post-stall variable mathematical model for predicting the characteristics of a fighter airplane with flows in turbojet test cells and solid fuel relaxed longitudinal static stability --- F-16 ran jets [NASA-TP-1538] 880-14136 [AD-A074187) 1480-14133 The effects of motion and 9-seat cues on pilot Aerodynamic interaction on a close-coupled canard simulator performance of three piloting tasks wing configuration tNASA-TP-1601] 880-15069 880-15 175 FLIGHT SI!ULATOBS On the effects of gaps on control surface Controllers for aircraft motion simulators characteristics [AIAA PAPER 80-0050] 480-18252 880-15176 Effects of varying visual display characteristics FLOW GEOHETHY of the T-4G, a T-37 flight simulator An analytical and experimental study of a short f#D-A071 4410) 880-15180 S-shaped subsonic diffuser of a supersonic inlet FLIGHT STABILITY TESTS [AXAA PAPER 80-0386) 480-20970 Stability and control aspects of the CCV-F1O4G Computation of three-dimensional flow in turbofan [NHP-UF!-1447(0) ] 880-19141 mixers and comparison with experimental data FLIGHT TESTS [NASA-TIl-81410] 1480-15368 Estimation of the accuracy of dynamic FLOW NEASUBENENT flight-determined coefficients Photon correlation laser velocimeter measurements [AIAA PAPER 80-0171] AR0-17700 in highly turbulent flow fields Flight certification of the Cessna T0206G [AIAA PAPER 80-0344) #80-18328 amphibious floatplane Sffect of tip planforin on blade loading 480-18186 characteristics for a two-bladed rotor in hover Flight and wind tunnel test results of the [NASA-TM-78615] 4480-19049 mechanical jet noise suppressor nozzle FLOW STABILITY [AIAA PAPER 80-0165] #80-20971 Sound generation in a flow near a compliant wall 480-20153

4-18

SUBJECT INDEX GAPS

FLOW VELOCITY FREQUENCY STABILITY Streamwise development of the flow over a delta wing Investigations of the optimal configuration of (AIAA PADER 80-0200] #80-18376 high-stability quartz oscillators for aircraft FLUID DYNAMICS and missiles APFDL experience in active control technology #80-19990 880-15159 FRICTION MEASUREMENT FL UTTER An improved sensing element for skin-friction General theory of aerodynamic instability and the balance measurements --- supersonic drag mechanism of flutter measuring instrument [NACA-496] 880-15087 (AIAA PAPER 80-0049] #80-18251 Comparison of international flutter requirements Investigation of the wear debris content in oil by and flutter freedom substantiation of light measurements of the reluctance and eddy current aircraft in the USA loss in an electric circuit 880-15142 #80-19053 FLUTTER ANALYSIS FUEL COMBUSTION Evaluation of the intensity of beat-induced Jet engine combustion noise - Pressure, entropy vibrations and vorticity perturbations produced by unsteady 880-17965 combustion or heat addition A computerized method for calculating flutter #80-20 151 characteristics of a system characterized by two NASA broad-specification fuels combustion degrees of freedom technology program: Status and description fNASA-TM-80153] 880-14055 [NASA-TN-79315) - P80-14126 Excitation and analysis technique for flight Exhaust emission reduction for intermittent flutter tests combustion aircraft engines [MBB-T1F-1446(0) ] 880-14140 tRASA-CR-159757] 880-14130 Low cost aircraft flutter clearance --- conference FUEL CONSUMPTION (AGARD-CP-278] 880-15141 Preparing aircraft propulsion for a new era in The state-of-the-art of flutter substantiation energy and the environment procedures among US general aviation manufacturers 880-17 737 880-15143 Technology of the Rolls-Royce R8211 engine An empirical approach for checking flutter #80-18 864 stability of gliders and light aircraft Engine component improvement program - Performance 880-15144 improvement Dynamic identification of light aircraft (AIAA PAPER 80-0223] 880-19300 structures and their flutter certification Fuel conservation benefits and critical P80-15 145 technologies of recuperative and advanced flutter-speed formula for wings of high aspect conventional cycle turboshaft engines ratio (8188 PAPER 80-0224] #80-19301 880-15147 The next supersonic transport The minimum cost approach to f lutter clearance #80-20214 PRO- 15148 Preliminary test resnits of a flight management FLY BY WIRE CONEPOL algorithm for fuel conservative descents in a Redundancy management considerations for a time based metered traffic environment control-configured fighter aircraft triplex flight tests of an algorithm to minimize fuel digital fly-by-wire flight control system consumption of aircraft based on flight time 880-14026 (NASA-TP-80194] P80-14114 Stability and control aspects of the CCV-?104G FUEL CORROSION rMRp-uFr-1447(o) ] 880-14141 Bfect of naphthenic aromatic hydrocarbons on the Flaperon control: The versatile surface for oxidizability of hydrogenated jet fuel --- jet fighter aircraft en g ine fuels 880-15 158 #80-17675 FOREBODIES FUEL INJECTION Enhanced departure/spin recovery of fighter Mach 3 hydrogen external/base burning aircraft through control of the forebody vortex [AtAA PAPER 80-0280] #80-19311 orientation FUEL-AIR RATIO (8186 PAPER 80-0173] 880-18352 Effect of degree of fuel vaporization upon An analytical and experimental study of a short emissions for a premixed partially vaporized S-shaped subsonic diffuser of a supersonic inlet combustion system --- for gas turbine engines rATAA PAPER 80-03861 880-20970 (NASA-TP-1582] 880-14125 Forebody vortex blowing: A novel control concept FULL SCALE TESTS to enhance departure/spin recovery Assessment at full scale of exhaust nozzle-to-wing characteristics of fighter and trainer aircraft size on STOL-OTW acoustic characteristics 880-15172 880-20952 FOURIER TRANSPOBMITION FUSELAGES Map-matching -techniques for terminal guidance Analysis of rotor-fuselage coupling and its effect using Fourier phase information on rotorcraft stability and response 880-17517 #80- 17716 Implementation of air traffic control radar Formulation of coupled rotor/fuselage equations of receivers with fast Fourier transform processors motion 880-14 086 880-17717 FRACTURE MECHANICS Experimental and numerical results of sound Determination of the stress intensity factor of scattering by a body --- interaction of composite structural members aerodynamic noise and fuselage 880_ 11958 P80-14873 Fatigue life prediction of a bonded splice joint (AIAA PAPER 80-0305] 880-18306 FRANCE 0 Marseilles - Iletamorphosis of an airport GAPS A80-l799 On the effects of gaps on control surface FREE FLOW characteristics Rybrid vortex method for 1ifting surfaces with 880-15176 free-vortex flow Some investigations concerning the effects of gaps (#188 PAPER 80-0070] #80-19307 and vortex generators on elevator efficiency and FREE JETS of landing flap sweep on aerodynamic Photon correlation laser velocimeter measurements - characteristics in highly turbulent flow fields 880-15 178 IAIAA PAPER 80-0344] A80-18328

8-19

GAS INJECTION SUBJECT INDEX

GAS INJECTION The state-of-the-art of flutter substantiation Optimization of turbine nozzle cooling by procedures among US general aviation manutacturers combining impingement and film injection 880-15143 [8188 PAPER 80-0299] 880-19316 GLIDE PATHS GAS MIXTURES A comparison of first and second order techniques Effect of degree of fuel vaporization upon for computing optimal horizontal gliding emissions for a premixed partially vaporized trajectories --- for low level wea pons delivery combustion system --- for gas turbine engines [8188 PAPER 80-0061] 880-18260 [NASA-TP-1582] 880-14125 GLIDERS GAS TURBINE ENGINES Low cost aircraft flutter clearance --- conference Gas turbine carcase and accessory vibration - rAGAND-CP-278) 880-15141 Problems of measurement and analysis An empirical approach for checking flutter 880-17730 stability of gliders and light aircraft Evaluation of the intensity of beat-induced 880-15144 vibrat ions A simplified ground vibration test procedure for 880-17965 sailpianes and light aircraft Estimation of noise source strengths in a gas 880-15 146 turbine coabustor GLOBAL ATMOSPHERIC RESEARCH PROGRAN [8188 pAVER 80-0034) 880-18245 Simultaneous cabin and ambient ozone measurements Regression techniques applied to parametric on two Hoeing 747 airplanes, volume 1 turbine engine simulations [NASA-TN-79166] 880-15059 [8188 PAPER 80-0053) 880-18255 GLOBAL POSITIONING SYSTEM Thermal barrier coatings for aircraft gas turbines Navigation error using rate of change of signal 1AIAA PAPER 80-0302) 880-18303 time of arrival from space vehicles Thermal state of structural members of aircraft 880-20904 engines --- Russian book The Global Positioning System 880-19412 88 0-2 0992 A method of evaluation of gas turbine engines Development of aiding GPS/strapdown inertial 880-20064 navigation system Unification of oils for aircraft gas-turbine engines 880-1403 1 880-20690 Avionics installation (AVSTALL) cost model for Dig it a]. system for dynamic turbine engine blade user equipment of NAVSTAR global positioning displacement measurements system [NASA-T8--81382] 880-14113 [80-8073681] N80-14106 Effect of degree of fuel vaporizaticn upon 7esign study of a low cost civil aviation UPS emissions for a premixed partially vaporized receiver system combustion system --- for gas turbine engines [NASA-CR-159176] 880-15062 [NASA-TP-15821 880-14125 GRAPHITE-EPDXY COMPOSITE MATERIALS NASA broad-specification fuels combustion Quiet Clean Short-Haul Experimental ngine (QCSPE) technology program: Status and description Under-The-Wing (018) graphite/PNR cowl development [NASA-T-79315] 880-14126 [NASA-CE-135279] 880-14119 Laser-optical blade tip clearance measurement system Quiet Clean Short-haul Experimental Engine [NASA-Tfl-81376) 880-14128 (QCSEE) Composite fan frame subsystem test Contact stress analysis of ceramic-to-metal report interfaces --- in gas turbine engines [NASA-CR-135010] 880-15098 [80-8074491] 880-14417 Quiet Clean Short-haul Experimental En gine (QCSEE) Impact of new instrumentation on advanced turbine composite fan frame design report research [NASA-CR-135278] 880-15110 [NASA-TN-79301 ] 880-15 133 GROUND EFFECT (AERODYNAMICS) Thermo-mechanical stress analysis of advanced The criticality of engine exhaust simulations on turbine blade cooling configuration VSTOL model-measured ground effects [AD-8074098) 880-15136 rAIAA PAPER 80-0230] 880-18276 ENS composites for advanced gas turbine engine GROUND HANDLING components Computer simulaticn of an air cargo small package [80-8074287) 880-15137 sorting system GAS TURBINES AS 0-20866 Feasibility of SiC composite structures for 1644 K Nodels for freight access to air terminals (2500 F) gas turbine seal application 880-20 869 [NASA-CB-159597) 880-14122 Air cargo container utilization optimization GASEOUS FUELS through modeling Jet engine combustion mcise - Pressure, entropy A80-20 870 and vorticity perturbations produced by unsteady GROUND STATIONS combustion or heat addition Experience in producing software for the ground 880- 20 151 station of a remotely piloted helicopter system GE AN S 880-14038 Quiet Clean Short-haul Experimental Engine (QCSEE) GROUND TESTS main reduction gears test program A simplified ground vibration test procedure for [NASA-CR-134669) 880-15103 sailpianes and light aircraft Quiet Clean Short-haul Experimental Engine (QCSEE) 880-15 146 main reduction gears bearing development program l'he minimum cost approach to flutter clearance rNASA-CE-134890] 880-15105 880-1514 8 Quiet Clean Short-haul Experimental Engine (QCSEN) GUIDANCE (MOTION) main reduction gears detailed design report Technical evaluation report on the 28th Guidance INASA-CB-134872] 880-15106 and Control Panel Symposium on Advances in GENERAL AVIATION AIRCRAFT Guidance and Control Systems Using Digital Determination of the spin and recovery Techniques characteristics of a typical low-wing general AGARD-AR-148) 880-15140 aviation design GUIDANCE SENSORS [8188 PAPER 80-0169] 880-18351 An observer system for sensor failure detection Designing light airplanes --- Russian book and isolation in digital flight control systems 880- 19414 880-14023 Heteorological input to general aviation pilot Automatic recovery after sensor failure onboard training 880-14024 880-14634 GUN TURRETS Accident investigation A nonlinear observer/command generator tracker 880-14636 approach to the 58-97 helicopter gum turret Design stud y o a low cost civil aviation GPS control law design receiver system 88 0-20 879 fNASA-cR-159176] 880-15062

8-20

SUBJECT INDEX HYPERSONIC WIND TUNNELS

GUST LOADS Experience in producing software for the ground Effect of spanwise gust variations station of a remotely piloted helicopter system 880-14639 880-14038 GUSTS Application of the SIRS concept to Navy helicopters Investigation of the oscillatory and flight systems analysis of flight data recorders of behavior of rotor systems in relation with flight conditons of helicopters for structural atmospheric turbulence analysis [BNVG-FHWT-79-5] 880-14142 (80-8074801] 880-15030 C! ROCO H PA SSE S HIGH ALTITUDE ENVIRONNENTS Development aspects of a dynamically tuned gyro Propulsion/airframe integration considerations for for strapdown - AHRS -- Attitude and Reading high altitude hypersonic cruise vehicles Reference System tAIAA PAPER 80-0111] 880-18272 880-17 553 HIGH ASPECT RATIO GYROSCOPIC STABILITY A flutter-speed formula for wings of high aspect Development aspects of a dynamically tuned gyro ratio for strapdown - AHRS --- Attitude and Heading 880-15 147 Reference System HIGH PRESSURE OXYGEN A80- 17553 LOX/GOX mechanical impact tester assessment A strapdown inertial reference system for [RASA-Tt9-74106] 880-15179 commercial airline use in navigation and flight HIGH TENPERATURE ENVIRONHENTS control Feasibility of Sic composite structures for 1694 K 880-17538 (2500 F) gas turbine seal application An integrated strapdown guidance and control [NASA-CR-159597] 880-14122 system for launch vehicle application HINGES 880-17559 Hinged vehicle equations cf notion [#IAA PAPER 80-0364] 880-18336 HISTORIES AFFDL experience in active control technology HAIL 880-15 139 The T-28 thunder/hailstorm penetration aircraft HORIZONTAL FLIGHT 880-14690 A comparison of first and second order techniques HA ADNE S S for computing optimal horizontal gliding Fleet hardness variation --- to determine aircraft trajectories --- for low level weapons delivery survivability due to blast loads r918A PAPER 80-0061) A80-18260 [AD-8074899] 880-15029 HOVERING HARDNESS TESTS Effect of tip planforni on blade loading Fleet hardness variation --- to determine aircraft characteristics for a two-bladed rotor in hover survivability due to blast load [NASA-TN-78615] 880-14089 [80-8074849] 880-15029 HOVERING STABILITY HANIONIC EXCITATION Large scale model tests of a new technology V/SPOL Excitation and analysis technique for flight concept flutter tests tAIAA PAPER 80-0233] A80-19303 tNBR-UF-1446(0) ] 880-14140 HU!AN FACTORS ENGINEERING HARHONIC OSCILLATION NASA technical advances in aircraft occupant safety Analysis of transonic flow about harmonically clear air turbulence detectors, fire oscillating airfoils and wings resistant materials, and crashworthiness [8188 PAPER 80-0149] 880-18367 ENASA-TH-80851] 880-15060 An investigation of several factors involved in a HURAN TOLERANCES finite difference procedure for analyzing the Investigation of noise hazards in the engine test transonic flow about harmonically oscillating cell, CYB Raden-Soellingen airfoils and wings [AD-A074391] 880-14147 [NASA-C p-15 g 1931 880-14056 HYDROCARBON FUELS HAZARDS Effect of naphthenic aromatic hydrocarbons on the Investigation of noise hazards in the engine test oxidizability of hydrogenated jet fuel --- jet cell, CR8 Raden-Soellingen engine fuels 180-8074391] 880-19147 880-17 675 HEAT TRANSFER HYDRODYNAHICS Impact of new instrumentation on advanced turbine Applications of modern hydrodynamics to research aeronautics. Part 1: Fundamental concepts and [NASA-TN-79301] 80-15133 the most important theorems. Part 2: HELICOPTER CONTROL Applications Analysis of rotor-fuselage coupling and its effect (NACA-116] 880-15034 on rotorcraft stability and response Pressure distribution on Jonkowski wings 880-17716 [NACA-TB-336] 880-15036 HELICOPTER DESIGN HYDROGEN FUELS A nonlinear observer/command generator tracker Nach 3 hydrogen external/base burning approach to the XN-97 helicopter gum turret [AIAA PAPER 80-0280] 880-19311 control law design HYPERSONIC AIRCRAFT 880-2087 9 Propulsion/airframe integration considerations for HELICOPTER PERFORHANCE high altitude hypersonic cruise vehicles Computer program to prepare airfoil characteristic tAIAA PAPER 80-01111 880-18272 data for use in helicopter performance. Loading tests of a wing structure for a hypersonic calculations aircraft [NASA-TN-78627] 880-15031 [NASA-TP-1596] 880-15068 Effects of primary rotor parameters on flapping HYPERSONIC VEHICLES dynamics Hypersonic cruise aircraft propulsion integration (NASA-TP-14311 880-15138 study, volume 1 HELICOPTER TAIL ROTORS [NASA-CB-158926-VOL-1] 880-15074 Formulation of coupled rotor/fuselage eguations of Hypersonic cruise aircraft propulsion integration motion study, volume 2 880-17717 NASA-CR- 1589 26-VOL-2) NH 0-15075 HELICOPTERS HYPERSONIC WIND TUNNELS Rotational noise of helicopter rotors Effect of the relative area of the flow core on 880- 1771 P the performance of a hypersonic wind tunnel A phenomenological model of the dynamic stall of a 880-17673 helicopter blade profile r0NPRA, TP NO. 1979-149) 880-20086

A-2 1

IMAGE COPBELATOBS SUBJECT IRDEY

INFORMATION RETRIEVAL Aerodynamic data base users guide [AD-50711448] 1180- 15983 IMAGE CORNELATOBS INFRARED SCANNERS Discontinuous registration of industrial Infrared sensor system performance simulations radiographs using profile analysis and piecewise A80-20900 correlation techniques INLET FLOW 580-17 521 Acoustic radiation from axisymnetric ducts - A Performance evaluation of image correlation comparison of theory and experiment techniques --- for aircraft inertial navigation [AlAS PAPER 80-0097] 580-18268 systems Improved numerical simulation of high speed inlets 580-17334 using the Alavier-Stokes equations IMAGE PROCESSING (AlAS PAPER 80-0383] 580-18340 Wire obstacle warning system IWOWS/ - A real-time Numerical simulation of supersonic inlets using a airborne sensor for automatic detection and three-dimensional viscous flow analysis recognition of wirelike objects AIAA PAPER 80-0384] 580-20969 580- 17402 An analytical and experimental study of a short Nap-matching techniques for terminal guidance S-shaped subsonic diffuser of a supersonic inlet using Fourier phase information (AIAA PAPER 80-0386] 580-20970 580-17517 An analytical and experimental study of a short Guidance sy stem positicn update by multiple s-shaped subsonic diffuser of a supersonic inlet subarea correlation [NASA-TN-81406] 1180-15134 580-17518 INSTALLING IMAGE TUBES Installation effects on cycle selection for small Visual displays for air traffic control data turbo-fan engines N80-14 077 (AIAA PAPER 80-0106) 580-19280 IMAGES INSTRUMENT LARDING SYSTEMS Visual accommodation responses in a virtual image What brings us down tomorrow - Landing guidance environment systems for the 1980s [50-5074415] 1180-15082 580-18725 IMPACT DAMAGE INTEGRATED CIRCUITS Atmospheric effects on Martian ejecta emplacement Integrated circuit characteristics at 260 C for 580-20 192 aircraft engine-control applications Soil analyses and evaluations at the impact 580-20 112 dynamics research facility for two full-scale INVISCID FLOW aircraft crash tests A numerical approach to subsonic viscons-inviscid rNASA-CP-159199) N80-13299 interaction IMPACT LOADS 580-19070 The loads at landing impact --- for aircraft ITALY 580-17723 On radar in air traffic control --- conference, IMPACT RESISTANCE Some, Jul. 1979 NASA technical advances in aircraft occupant safety r SUB-11-1979] 1180-14065 clear air turbulence detectors, fire Problems related to the design and construction of resistant materials, and crashworthiness a radar network [NASA-TN-80851 ] 1180-15060 1180-14066 IMPACT TESTING MACHINES Organization of an integrated global maintenance LOX/GOX mechanical impact tester assessment service --- Padar Networks [NASA-TM-74106] N80-15179 1180-1(4 069 IN-PLIGHT MONITORING In-flight measured characteristics of combined flap-spoiler direct lift controls J 1180-15165 JET AIRCRAFT INDICATING IWSERUMEJIS The rational design of an airfoil for a high Some practical aspects of the calibration of air performance jet trainer data systems (AIAA PAPER 80-0328] 580-18317 580-18865 Effects of non-planar strake-wing on the vortex INERTIAL GUIDANCE lift characteristics of a twin-jet fighter Guidance sy stem position update by multiple configuration subarea correlation fAIAA PAPER 80-0329) A80-18318 580-17518 JET AIRCRAFT NOISE INERTIAL NAVIGATION Acoustic radiation from axisvmnetric ducts - A Development aspects of a dynamically tuned gyro comparison of theory and experiment for stradown - ARES --- Attitude and Reading (AT AS PAPEII 80-0097] 580-18268 Reference System Jet engine combustion noise - Pressure, entropy 580-17533 and vorticity perturbations produced by unsteady A strapdown inertial reference system for combustion or heat addition commercial airline use in navigation and flight A80-20 151 control Acoustic considerations of flight effects on jet 580-17558 noise suppressor nozzles An integrated strapdown gnidance and control (AISA PAPEB 80-0164] A8O-20965 system for launch vehicle application Quiet Clean Short-Haul Experimental Engine (QCSPF) 580-17359 acoustic and aerodynamic tests on a scale model Development of aiding GPS/strapdown inertial over-the-wing thrust reverser and forward thrust navigation system nozzle 1180-1403 1 tNASA-CR-1352541 1180-14115 Methods for strap-down attitude estimation and Quiet Clean Short-haul Experimental Engine (QCSEE) navigation with accelerometers Over-The-Wing (0111) propulsion systems test N80- 14034 report. Volume LI: Aconstid performance A high accuracy flight profile determining system (NASA-CB-135326] 1180-15118 systems analysis of inertial navigation An experimental study of the structure and system for aircraft position determination acoustic field of a jet in a cross stream 1180-14042 Ames 7-ft by 10-ft wind tunnel tests INERTIAL REFERENCE SYSTEMS [NASA-Cfl-162464] 1180-15871 A strapdown inertial reference system for JET ENGINE FUELS commercial airline use in navigation and flight Effect of naphthenic aromatic hydrocarbons on the control oxidizability of hydrogenated jet fuel --- jet 580-17558 engine fuels 580-17 675

5-22

SUBJECT INDEX LOAD TESTS

Aircraft fuel system simulator tests vith LATERAL STABILITY antimisting kerosene (jet A fuel vith FN-9 Effects of the aerodynamic cross-coupling and additive) --- flammability tests lateral acceleration derivatives on airplane (Ar-A073237] 880-144256 d ynamic characteristics JET ENGINES [AIAA PAPER 80-0170] 880-17699 On the influence of steady state temperature and Aircraft aerodynamics - Dynamics of longitudinal pressure distortion on the flow characteristics and lateral motion --- Russian book in an installed multistage jet engine compressor 880-19374 A80-17724 LATTICES (EATHEMATICS) Acoustic radiation from axisymmetric ducts - A The quasi-vortex-lattice method for wings with comparison of theory and experiment edge vortex separation [AIAA PAPER 80-0097] A80-18268 [NASA-CR-162530] 880-144052 Computer simulation of engine systems LAUNCH VEHICLES [NASA-TN-79290] 880-15132 An integrated strapdown guidance and control JET EXHAUST system for launch vehicle application The criticality of engine exhaust simulations on #80-17 559 VSTOL model-measured ground effects LEADING EDGES [AIAA PAPER 80-0230] A80-18276 Investigation of leading-edge devices for drag JET BIXING PLOW reduction of a 60-deg. delta wing at high angles Recent development of a jet-diffuser ejector of attack [AIAA PAPER 80-0231) A80-18277 18188 PAPER 80-0310] A80-18309 Photon correlation laser velocimeter measurements Studies of leading-edge thrust phenomena in highly turbulent flow fields [AIAA PAPER 80-0325) A80-18315 [AIAA PAPER 80-03841 880-18328 The effects of leading edge modifications on the An experimental model investigation of turbofan post-stall characteristics of wings engine internal exhaust gas mixer configurations [AIAA PAPER 80-0199] #80-18375 [AIAA PAPER 80-0228] 880-19302 Streamwise development of the flow over a delta wing Scale model performance test investigation of IAIAA PAPER 80-0200] A80-18376 exhaust system mixers for an Energy Efficient The quasi-vortex-lattice method for wings with Engine /83/ propulsion system edge vortex separation rAIAA PAPER 80-02291 880-20968 rNASA-CR-162530) 880-14052 JOUI1OWSKI TRANSPORHATION LIFE CYCLE COSTS Pressure distribution on Jonkowski wings The modular life cycle cost model - An overview [NACA-TN-3361 880-15036 [SANE PAPER 1290] 880-20636 Designing to life cycle cost in the Hornet program !SAWE PAPER 1293] #80-20638 LZI LIFE SUPPORT SYSTENS KEROSENE Aeronautical systems technology needs: Escape, Aircraft fuel system simulator tests with rescue and survival antimisting kerosene (jet A fuel with P8-9 (AD-A074906] 880-144061 additive) --- flanimabilitv tests LIFT [AD-A073237] 880-18256 Development of a vortex-lift-design method and KINETIC THEORY application to a slender maneuver-wing Elements of the wing section theory and of the con figuration wing theory [AIAA PAPER 80-03271 880-18316 [NAcA-i g i) 880-15040 Some wind tunnel measurements of the effectiveness at. low speeds of combined lift and roll controls 880-15 153 L LIGHT AIRCRAFT LAHINAR FLOW Designing light airplanes --- Russian book Reynolds number and compressibility effects on 880-19 44144 dynamic stall of a RACA 0012 airfoil A light aircraft camera Pod - The Enviro-Pod [AIAA PAPER 80-0010] 880-18238 #8 0-20 25 1 LARINAR PLOW AIRFOILS A method of simplifying weight and balance for A parametric win g design study for a modern small aircraft laminar flow wing ISAWE PAPER 1278] #80-20630 1NASA-T8-80154] 880-15050 Tow cost aircraft flutter clearance --- conference LANINATES (AGARC-CP-278] R80-15141 Determination of the stress intensity factor of Comparison of international flutter reguirements composite structural members and flutter freedom substantiation of light A80-17 958 aircraft in the USA Advanced materials and the Canadair Challenger 880-15 142 [SAWE PAPER 1284] 880-20632 The state-of-the-art of flutter substantiation LANDING GEAR procedures among US general aviation manufacturers The loads at landing impact --- for aircraft 880-15143 A80-17723 An empirical approach for checking flutter LANDING LOADS stability of gliders and light aircraft The loads at landing impact --- for aircraft 880-15 14414 A80-17723 Dynamic identification of light aircraft LASER APPLICATIONS structures and their flutter certification Laser-optical blade tip clearance measurement systes 4180-15 145 rNASA-TN-81376] 880-14128 A simplified ground vibration test procedure for LASER DOPPLER VYLOCINETENS sailpianes and light aircraft Photon correlation laser velocimeter measurements 880-15 196 in highly turbulent flow fields The minimum cost approach to flutter clearance [8188 PAPER 80-034 44] A80-18328 4480-15 1448 LATERAL CONTROL LINEAR SYSTENS Some wind tunnel measurements of the effectiveness Linear systems analysis program, 1224 (QP) . Volume at low speeds of combined lift and roll controls 1: Engineering and usage 880-15 153 (NASA-CR-2961] 880-14137 Poll control by digitally controlled segment LIQUID OXYGEN spoilers 101,/GOT mechanical impact tester assessment 4180-15156 INASA-T11-74106) 880-15179 Flaperon control: The versatile surface for LOAD TESTS fighter aircraft Loading tests of a wing structure for a hypersonic 880-15158 aircraft [R&SA-TP-1596] 880-15068

A-2 3

LONGITUDINAL STABILITY SUBJECT INDEX

LONGITUDINAL STABILITY BARS ATMOSPHERE Aircraft aerodynamics - Dynamics of longitudinal Atmospheric effects on Martian ejecta emplacement and lateral motion --- Russian took A80-20 192 A80-19 374 BARS SURFACE Simulator study of stall/post-stall Atmospheric effects on Nartian ejecta emplacement characteristics of a fighter airplane with A80-20 192 relaxed longitudinal static stability --- F-16 MATHEMATICAL MODELS rNASA-TR-1538] 880-14136 Models for freight access to air terminals LOOP ANTENNAS A80-20869 Experimental loop antennas for 60 KHZ to 200 Hz Air cargo container utilization optimization [NASA-CR-162729] 1180-15063 through modeling A80-20870 LORAN Loran digital phase-locked loop and 8? front-end Avionics installation (AVSTALL) cost model for system error analysis user equipment of NAVSTAR global positioning IRASA-CR-162731 ] 1180-15065 system LORAN C [AD-A073681] 1180-14106 Experimental loop antennas for 60 KHZ to 200 KHz hpplication of the multistage axial-flow fNASA-CB-162729] 880-15063 compressor time-dependent mathematical modeling Data reduction software for LORAN-C flight test technique to the TF41-A-1 modified block 75 evaluation compressor fNASA-CR-162730] 880-15064 tAD-A0744781 880-14134 LOW ASPECT RATIO Pressure distribution on loukowski wings Low-aspect-ratio limit of the toroidal reactor - [RACA-TN-336] 1180-15036 The spbercmak A flutter-speed formula for wings of high aspect A80- 17876 ratio LOW COST 880-15147 The minimum cost approach to flutter clearance MEASURING INSTRUMENTS 880-15148 An improved sensing element for skin-friction LOW SPEED balance measurements --- supersonic drag Some wind tunnel measurements of the effectiveness, measuring instrument at low speeds of combined lift and roll controls [AIAA PAPFR 80-0049] A80-18251 880-15153 MECHANICAL PROPERTIES unsteady aerodynamics of two-dimensional spoilers The physical and chemical characterization of ten at low speeds military turbine engine lubricants 880-15170 (A13-A074013] 1180-15265 LUBRICANTS METAL FATIGUE The physical and chemical characterization of ten Sonic fatigue design data for bonded aluminum military turbine engine lubricants aircraft structures [AD-A074073] 880-15265 (AIRA PAP?R 80-0303] A80-18304 LUBRICATING OILS Fatigue life prediction of a bonded splice joint Investigation of the wear debris content in Oil by (AIAA PAPER 80-0305] A80-18306 measurements of the reluctance and eddy current METAL JOINTS loss in an electric circuit Fatigue life prediction of a bonded splice joint A80- 19053 (AIAA PAPER 80-0305) A80-18306 1nification of oils for aircraft gas-turbine engines METAL MATRIX COMPOSITES A80-20690 FRS composites for advanced gas turbine engine components (AD-A074287] 880-15137 iv' METAL PARTICLES MAGNETONYDRODYJABIC STABILITY Investigation of the wear debris content in oil by Low-aspect-ratio limit cf the toroidal reactor - measurements of the reluctance and eddy current The spberctiak loss in an electric circuit A80- 17876 A80-19 053 MAINTENANCE METAL SURFACES Organization of an integrated global maintenance Contact stress analysis of ceramic-to-metal service --- Radar Networks interfaces --- in gas turbine engines 88f)-14 069 rAD-A074491] 880-14417 MAN MACHINE SYSTEMS BETBOBOLOGICAL INSTRUMENTS Adaptive allocation of decisionmaking Current research on aviation weather responsibility between human and computer in (bibliography) , 1979 multitask situations [NASA-CE-3214] 880-14651 A80- 18022 METEOROLOGICAL RADAR A statistical method applied to pilot behavior Weather detection using airport surveillance radar analysis in multiloc systems A80-19 129 A80-18 537 METEOROLOGY Automation and air traffic control Meteorological input to general aviation pilot A80-18722 training Vocabulary specification for automatic speech 880-14634 recognition in aircraft cockpits MICROOEGANISMS [AD-A073703J 880-14303 Microbial deterioration of hydrocarbon fuels from MANUAL CONTROL oil shale, coal, and petroleum. 1: Exploratory Pilot control through the TAI'COS automatic flight experiments control system (AD-A073761] 880-14259 (NASA-TN-81152] 880-14138 MICROPROCESSORS MANUFACTURING Nodular strapdown guidance unit with embedded The state-of-the-art of flutter substantiation microprocessors procedures among US general aviation manufacturers [ATAA PAPER 78-1239] A80-18534 880-15143 Verification of digital autopilot microprocessor MAP BATCHING GUIDANCE hardware and software via hardware-in-the-loop Nap-matching techniques for terminal guidance simulation using Fourier phase information A80-20901 A80-17 517 MICROWAVE FREQUENCIES Guidance system position update by multiple Development trends of airport surface traffic subarea correlatics control radar A80-1751 8 880-14 087 MARKET RESEARCE MICROWAVE LANDING SYSTEMS Airport noise, location rent, and the market for What brings us down tomorrow - Landing guidance residential amenities systems for the 1980s A80- 17120 A80-18725

A-2 U

SUBJECT INDEX NOISE REDUCTION

MILITARY AIRCEAFT Quiet Clean Short-haul Experimental Engine (QCSEE) Application of RCS guidelines to weight effective Under-The-Wing (GIN) composite nacelle aircraft design --- Fadar Cross Section [NASA-CR-135352] 880-15119 [SAW! PAPR 1270) A80-20626 NASA P!OGBA!S The nodular life cycle cost model - An overview Engine component improvement prograffi - Performance [SAW! PAP!! 1290] 480-20636 improvement AFFDL experience in active control technology [AIAA PAPER 80-0223] A80-19300 N80-15 159 NASA broad-specification fuels combustion MILITARY BELICOPTEES technology program: Status and description Analysis of low-speed helicopter flight test data (NASA-TM-79315] 880-14126 [AD-A074141) 880-15079 NASA technical advances in aircraft occupant safety MILITARY TECHNOLOGY clear air turbulence detectors, fire Wavy V/STOL - A continuing initiative resistant materials, and crashworthiness [SAW! PAP!! 1325] 480-20655 [NASA-TM-80851] N80-15060 AFPDL experience in active control technology Quiet powered-lift propulsion N80-1159 [NASA-CP-2077) !80-15127 Control integration technology impact --- as a IAVIER-STOSES EQUATION basis for improving the combat effectiveness of Improved numerical simulation of high speed inlets all tactical aircraft using the Navier-Stokes equations 880-15 162 (AIAA PAPER 80-0383] A80-18340 NISSILE CONTEOL NAVIGATION AIDS Modular strapdown guidance unit with embedded Performance evaluation of image correlation microprocessors techniques --- for aircraft inertial navigation [AIAA PAP!! 78-1239] 480-18534 systems Verification of digital autopilot microprocessor A80-17534 hardware and software via hardware-in-the-loop NAVIGATION SATELLITES simulation Navigation error using rate of change of signal A80-20901 time of arrival from space vehicles MISSILE DESIGN A80-20904 Assessment of analytic methods for the prediction NAVST*R SATELLITES of aerodynamic characteristics of arbitrary The Global Positioning System bodies at superscnic speeds 480-20992 [AIAA PAP!! 80-0071) A80-19308 NEAR PIELDS NODAL RESPONSE Rotational noise of helicopter rotors Analyses and tests of the B-i aircraft structural A80-17718 mode control system NOISE GENERATORS [SASA-C!-144887] N80-15073 Sound generation in a flow near a compliant wall MODELS 480-20153 Model 540 rotor blade crack propagation An experimental study of the structure and investigation acoustic field of a jet in a cross stream [AD-A0747341 880-15081 Ames 7-ft by 10-ft wind tunnel tests MOMENTUM [NASA-CR-1624611] 880-15871 Elements of the wing section theory and of the NOISE INTEISIT! wing theory Estimation of noise source strengths in a gas [NACA-191] 880-15040 turbine combustor NOTION SIMULATORS [AIAA PAPER 80-0034] 480-18245 Controllers for aircraft motion simulators NOISE NEASIJEEMENT [AIAA PAP!! 80-0050] A80-18252 Estimation of noise source strengths in a gas The effects of motion and g-seat cues on pilot turbine combustor simulator performance of three piloting tasks [AIAA PAPER 80-0034] 480-18245 fNASA-TP-16011 880-15069 Landing approach airframe noise measurements and NT!? analysis Designing to life cycle cost in the Hornet program (NASA-TP-1602] 880-15028 (SAWS PAP!! 1293] 480-20638 Quiet Clean Short-haul Experimental Engine (QCSE!) - Core engine noise measurements [NASA-CR-135160] N80-15093 N A study of partial coherence for identifying NACELIES interior noise sources and paths on general Preliminary weight estimation of engine section aviation aircraft structure (NASA-T8-801971 880-15874 [SAP! PAP!! 1311) 480-20645 NOISE POLLUTION Quiet Clean Short-haul Experimental Engine (QCSEE) Airport noise, location rent, and the market for preliminary under the wing flight propulsion residential amenities system analysis report 480- 17720 [NASA-C!-134868] 880-15088 NOISE P!EDICTION (AIRCRAFT) Quiet Clean Short-haul Experimental Engine Rotational noise of helicopter rotors (QCS!E). Under-The-Wing (UTW) engine hcilerplate 480-177 18 nacelle test report, voluoe 1 Acoustic considerations of flight effects on jet [NASA-CR-135249] N80-15096 noise suppressor nozzles Quiet Clean Short-haul Experimental Engine [AIAA PAP!! 80-0164) 480-20965 (QCSE!) . Under-The-Wing (UTW) engine hoilerplate NOISE PROPAGATION nacelle test report. Volume 3: Mechanical comparison of inlet suppressor data with performance approximate theory based on cutoff ratio [NASA-CB-135251 ] 880-15097 [AIAR PAPER 80-0100] A80-20964 Quiet Clean Short-haul Experimental Engine (QCS!E) A study of partial coherence for identifying Over-The-Wing (OTW) bcilerplate nacelle design interior noise sources and paths on general report aviation aircraft (HASA-C!-135168] 880-15099 [NASA-T8-80197] N80-15874 Quiet Clean Short-haul Experimental Engine (QCSEE) NOISE REDUCTION Under-The-Wing (UTW) composite nacelle subsystem Structural parameters that influence the noise test report --- to verify strength of selected reduction characteristics of typical general composite materials aviation materials [N&SA-C!-135075] 880-15100 [AIAA PAP!! 80-0038) 480-18248 Quiet Clean Short-haul Experimental Engine (QCSEE) Comparison of inlet suPpressor data with Under-The-Wing (GIN) toiler plate nacelle and approximate theory based on cutoff ratio core exhaust nozzle design report (4144 PAP!! 80-0100] 480-20964 [NASA-CR-135008] 880-15116 Acoustic considerations of flight effects on jet noise suppressor nozzles [RIAA PAPE! 80-0164] A80-20965

A-25

NO MOO B A PH S SUBJECT INDEX

ylight and wind tunnel test results of the NUMERICAL PLOW VISUALIZATION mechanical jet noise suppressor nozzle Reynolds number and compressibility effects on [AIAA PAPER 80-01651 880-20971 dynamic stall of a RACA 0012 airfoil Acoustically swept rotor --- helicopter noise [8188 PAPER 80-0010] 880-18238 reduction Pngine aetodynamic installation by numerical NASA-CASE-ARC-11106-1 J 880-14107 simulation Quiet short-haul research aircraft familiarization [8188 PAPER 80-0108] 880-18271 document --- STOL Improved numerical simulation of high speed inlets [NASA-T#-81149] 880-14108 using the Navier-Stokes equations - Demonstration of short-haul aircraft aft noise [8188 PAPER 80-0383] 880-18340 reduction techniques on a twenty inch (50.8 cm) Humerical simulation of supersonic inlets using a diameter fan, volume 1 three-dimensional viscous flow analysis [NAsA-cR-134849) 880-15083 [818* PAPER 80-0384) 880-20969 Demonstration of short-haul aircraft aft noise NUMERICAL INTEGRATION reduction techniques on a twenty inch (50.8) Direct integration of transient rotor dynamics diameter fan, volume 2 [NASA-TP-1597) 880-15128 rllAsA-CR-134850] 880-15084 DeBonstration of short haul aircraft aft noise reduction techniques on a twenty inch (50.8 cm) 0 diameter fan, volume 3 OBLIQUE SHOCE WAVES [NASA-CR-134851 ] N80-15085 Oblique detonation wave ranjet Acoustic analysis of aft noise reduction [NASA-CR-159192] 880-14131 techniques measured on a subsonic tip speed 50.8 OMEGA NAVIGATION SYSTEM cm (twenty inch) diameter fan --- quiet engine The Omega radio navigation system --- Russian book program 880- 19 413 [8ASA-CN-134891] 880-15102 OPERATING SYSTEMS (COMPUTERS) Quiet clean Short-Haul Experimental Engine The integrity of onboard computer programs: A (QCSEE) : Acoustic treatment development and solution design 88 0-14028 [NASA-CE-135266] 880-15122 The avionics computer program: Practical Evaluation of approximate methods for the experiences with a methodology --- Nirage Fl and prediction of noise shielding by airframe Mirage 200 aircraft components - 880-14037 (NASA-TP-1004] 880-15129 OPTIMAL CONTROL MONOGRAPHS Controllers for aircraft motion simulators A method of amplifying weight and balance for [8188 PAPER 80-0050] 880-18252 small aircraft Constrained optimum trajectories with specified rSAwE PAPER 1278] #80-20630 range NONDESTRUCTIVE TESTS 880-18 538 Discontinuous registration of industrial 1 nonlinear observer/command generator tracker radiographs using profile analysis and piecewise approach to the XN-97 helicopter gun turret correlation techniques control law design 880-1752 1 880-20 879 NOSE PINS Design criteria for optimal flight control systems Effects of non-planar strake-wing on the vortex study of optimal flight control systems lift characteristics of a twin-jet fighter engineering for feedback control configuration [80-8014092] 880-15139 [8188 PAPER 80-03291 880-18318 OPTIMIZATION NOSES (PORERODIPS) Nulti-variable cycle Optimization by gradient Control of forebody three-dimensional flow methods --- for variable-cycle engines separat ions [8188 PAPER 80-0052] 880-18254 880-15 164 Optimization of turbine nozzle cooling by NOZZLE DESIGN combining impingement and film injection Acoustic considerations of flight effects on jet [AIAA PAPER 80-0299) 880-19316 noise suppressor nozzles Code optimization for solving large 3D EEP problems [8188 PAPER 80-0164] 880-20965 electromagnetic scattering by aircraft Flight and wind tunnel test results of the structures mechanical jet noise suppressor nozzle 880-19764 [8188 PAPER 80-0165] 880-20971 Advanced technology effects on V,'STOL propulsive NOZZLE FLOW system weight Photon correlation laser velocimeter measurements [SANE PAPER 1300] 880-20640 in highly turbulent flow fields Air cargo container utilization optimization fAIAA PAPER 80-0344) 880-18328 through modeling Computation of three-dimensional flow in turbofan 88 0-2 0 870 mixers and comparison with experimental data ORBITAL POSITION ESTIMATION rNASA-TM-81410] 880-15364 The Russian satellite navigation system NOZZLE GEOMETRY 880-20982 Static test-stand performance of the !F-102 OXIDATION turbofan engine with several exhaust Effect of naphthenic aromatic hydrocarbons on the configurations for the Quiet Short-Haul Research ozidizability of hydrogenated jet fuel --- jet Aircraft (QSRA) engine fuels [NASA-TP-1556] 880-14121 A80-17 675 NUCLEAR EXPLOSICE EPPICT OZONE Protective coatings for aircraft composites in Simultaneous cabin and ambient ozone measurements nuclear environments on two Boeing 747 airplanes, volume 1 [80-8074889] 880-14199 [NASA-TM-79166] 880-15059 NUMERICAL ANALYSIS A comparison of first and second order techniques for computing optimal horizontal gliding P trajectories --- for low level weapons delivery PANORAMIC CAMERAS [8188 PAPER 80-0061) 880-18260 A light aircraft camera Pod - The Enviro-Pod The minimum cost approach to flutter clearance 880-20251 880-15 148 PARTICLE SIZE DISTRIBUTIOB NUMERICAL CONTROL Investigation of the wear debris content in oil by Nodular strapdown guidance unit with embedded measurements of the reluctance and eddy current microprocessors loss in an electric circuit [8188 PAPER 78-1239] 880-18534 880-19053

8-26

SURJECT INDEX POWERED LIFT AIRCRAFT

PASSENGERS Effects of varying visual display characteristics NASA technical advances in aircraft occupant safety of the T-4G a 1-37 flight simulator clear air turbulence detectors, fire (AD-A071810) 880-15180 resistant materials, and crashworthiness PILOT TRAINING [NASA-TN-80851 3 N80-15060 Reteorological input to general aviation pilot PA7NNENTS training An analytical method of testing pavement strength 880-18 634 880- 17998 PISTON ENGINES Reflection cracking of bituminous overlays for Experimental investigation of the characteristics airport pavements: A state of the art of pneumatic transfer lines rAn-Ao734e41 N80-1141L14 880-19052 PENALTY FUNCTION Exhaust emission reduction for intermittent A first look at the effect of severe rainfall upon combustion aircraft engines an aircraft [NASA-CR-159757] 880-18130 (NASA-CR-162569] !180-15058 PITCH (INCLINATION) PERFORMANCE PREDICTION Quiet Clean Short-haul Experimental Engine Analytical investigation of aerodynamic (QCSEE) . Rail spline pitch change mechanism characteristics of highly swept wings with design report separated flow rNASA-CR-134873] R80-15101 880-1769' PLANFOEM S Determination of the spin and recovery Effect of tip planform on blade loading characteristics of a typical low-wing general characteristics for a two-hiaded rotor in hover aviation design [1IASA-TN-78615] N80-140119 [8188 PAPER 80-0169] 880-18351 PLASNA CONTROL Nultiple tactical aircraft combat performance Low-aspect-ratio limit of the toroidal reactor - evaluation system The spheromak [8188 PAPER 80-0189] 880-18358 A80-17876 Problems associated with cargo airplanes having PNEUMATIC EQIJIPRENT aft mounted engines Experimental investigation of the characteristics rSAWE PAPER 1318] 880-20688 of pneumatic transfer lines Infrared sensor system performance simulations 880- 19 052 880-20900 PNEUMATICS Summary of advanced methods for predicting high On the dynamics of compressor surge speed propeller performance 880-17900 [8188 PAPER 80-0225] 880-20966 PODS (EXTERNAL STORES) Summary of advanced methods for predicting high A light aircraft camera Pod - The Enviro-Pod speed propeller performance A80-20251 [8808-18-818091 880-15051 POLLUTION CONTROL PERFOENANCE TESTS Quiet Clean Short-haul Experimental Engine (OCS?E) Effect of the relative area of the flow core on [NASA-CR-159473] 880-15120 the performance of a hypersonic wind tunnel POLYIMIDE RESINS 880-17673 Quiet Clean Short-Haul Experimental Pngine (QCSEE) An experimental mc e1 investigation of turbofan Under-The-Wing (UTW) graphite/PHR cowl development engine internal exhaust gas mixer configurations [NASA-CR-135279] 1180-14119 [AIAA PA P ER 80-0228] 880-19302 POLYNER MATRIX CONPOSITE NATERIALS Verification of digital autopilot microprocessor Advanced materials and the Canadair Challenger hardware and software via hardware-in-the-loop rSAWE PAPER 1284] 880-20632 simulation POROUS WALLS 880-2 0901 Two dimensional aerodynamic interference effects Performance evaluation methods of a secondary on oscillating airfoils with flaps in ventilated radar network subsonic wind tunnels --- computational fluid 880-14 068 dynamics Quiet Clean Short-Haul Experimental Engine (QCSEE) [NASA-CR-3210] 880-114047 Over-The-Wing (01W) propulsion s y stem test POSITION (LOCATION) report. Volume 2: Aerodynamics and performance Guidance system position update by multiple engine performance tests to define subarea correlation propulsion system performance on turbofan engines 880-17 518 fRASA-CR-135324] 880-14120 Laser-optical blade tip clearance measurement system The CF6 let engine performance improvement: New [8858-18-81375] 880-14128 front mount POSITION ERRORS rNAsA-cR-1596391 880-14127 Determination of the repeatability of PEC JA-6A circulation coutrcl wing contractor flight flight tests for position error calibrating demonstration [AETE-PR-79/36] 880-114109 [80-8074888] 880-15080 POSITION INDICATORS PERTURBATION A high accuracy flight profile determining system Trajectory behaviour of a control configurated systems analysis of inertial navigation aircraft subjected to random disturbances system for aircraft position determination 0180-15 171 880-1440442 PHASED ARRAYS POTENTIAL FLOW Target tracking using Doppler-information in General potential theory of arbitrar y wing sections sensor oriented coordinates with a three [NACA-4521 880-15046 dimensional array radar POTENTIAL THEORY [REPT-270] 880-14325 General potential theory of arbitrary wing sections PHOTOGRAPHIC RECORDING [NACA- 4452] 880-150146 US Army Test and Evaluation Command test POWER SUPPLY CIRCUITS operations procedures: Photographic and video An overvoltage safety system for direct current image support aviation materiel aircraft generators [AD-A07 11883] 890-14377 880-19051 PHYSIOLOGICAL RESPONSES POWERED LIFT AIRCRAFT Visual accommodation responses in a virtual image Quiet Clean Short-haul Experimental Engine (QCSEE) environment [!4ASA-CR-159473] 880-15120 [AD-A074415] 880-15082 OOiet powered-lift propulsion PILOT PERFORMANCE [RASA-CP-2077] 880-15127 A statistical method applied to pilot behavior The IC-lA upper surface blown flap: A unigue analysis in multilcop systems control surface A80- 18537 880-15157 The effects of motion and g-seat cues on pilot simulator performance of three piloting tasks [NASA-TP-1601] 880-15069

8-27

PREDICTION ANALYSIS T!CBNICUES SUBJECT INDEX

PREDICTION ANALYSTS TECHNIQUES Quiet Clean Short-haul Experimental Engine (QCSEF) A pre-design code for predicting engine Over-The-Wing (OTW) boilerplate nacelle design acquisitics costs report (AIAA PAPER 80-0055] #80-19269 rNASA-CR-135168] 880-15099 An adaptation and validation of a primitive Quiet Clean Short-haul m xperinental Engine variable mathematical model for predicting the (QCSEE): The aerodynamic and mechanical design flows in turbojet test cells and solid fuel of the QCSEE under-the-wing fan

ra En jets [NASA-CR-135009] 880-15109 (AD-A0714187] 880-14133 Quiet Clean Short-haul Experimental Engine (QCSE?) PRESSURE NASA-CR-159473] 880-15120 Surface conforming thermal/pressure seal --- for Quiet Clean Short-Haul Experimental Engine control devices in space vehicles (QSCEE) . Preliminary analyses and design [WASA-CASE-MSC- 18422-1] 9180-14400 report, volume 1 PRESSURE DISTRIBUTION [NASA-CP.-134838] 880-15123 Pressure distribution cm Joukowski wings Ouiet Clean Short-Haul Experimental Engine [NACA-TN-336] 880-15036 (QCSEE). Preliminary analyses and design The aerodynamic forces on airship hulls report, volume 2 [NACA-184] N80-1c039 [NASA-CR-1348391 880-15128 A users guide for A3'44: A program using a finite PROPULSION SYSTEM PERFORMANCE difference method to analyze transonic flow over Preparing aircraft propulsion for a new era in oscillating airfoils energy and the environment rNASA-CR-159141 1 880-15052 #80-17 737 Exploratory studies of the cruise performance of Multi-variable cycle optimization by gradient upper surface blown configurations: methods --- for variable-cycle engines Experimental program, high-speed pressure tests [ATAA PAPER 80-0052] 880-18254 rNASA-c91-159135) 1180-15071 Quiet Clean Short-Haul Experimental Engine (QCSEF) PRESSURE MEASUBB!BNTS Over-The-Wing (CTW) propulsion system test Aeroacoustic measuring techniques in or outside report Volume 2: Aerodynamics and performance turbulent flows engine performance tests to define 880-14876 propulsion system performance on turbofan engines PRESSUBE RECOVERY rNASA-CR-135324 880-14120 Effect of the relative area of the flow core on Dynamic response of a Mach 2.5 axisymmetric inlet the performance of a hypersonic wind tunnel and turbojet engine with a poppet-value A80- 17673 controlled inlet stability bypass system when PROBLEM SOLVING subjected to internal and external airflow A computerized method for calculating flutter transients characteristics of a system characterized by two rNASA-TP-1531] 880-14123 degrees of freedom Quiet Clean Short-haul Experimental Engine (QCSEE) tNASA-TN-801531 1180-14055 preliminary under the wing flight propulsion PEOPILONETERS system analysis report Discontinuous registration of industrial [NASA-CN-134868] 880-15088 radiographs using profile analysis and piecewise Quiet Clean Short-haul Experimental Engine (QCSEE) correlation techniques Under-The-Wing (IITW) engine composite nacelle #80-17521 test report. Volume 1: Summary, aerodynamic PROGRAM VERIFICATION (COMPUTERS) and mechanical performance An assessment of and approach to the validation of R#SA-CR-159471 ] 880-15099 digital flight control systems Ouiet Clean Short-haul Experimental Engine 880-14036 (QCSEE) . Under-She-Wing (TITW) engine boilerplate PROJECT PLANNING nacelle test report, volume 1 NASA/Army IV-15 tilt rotor research aircraft INASA-CR-135249] 880-15096 wind-tunnel test program plan --- Ames 40-ft by Quiet Clean Short-haul Experimental 'ngine 80-ft wind tunnel tests (QCSEE) . Under-The-Wing (05W) engine boilerplate [NASA-TM-78562] 880-15067 nacelle test report. Volume 3: Mechanical PROPELLER BLADES performance Summary of advanced methods for predicting high RASA-CR-135251] 880-15097 speed propeller performance Quiet Clean Short-haul Experimental Engine (QCSEE) [AIAA PAPER 80-0225] 880-20966 main reduction gears bearing development program PROPELLER EFFICIENCY [NASA-CR-134890] 880-15105 Summary of advanced methods for predicting high fluiet Clean Short-haul Experimental Engine (QCSEE) speed propeller performance main reduction gears detailed design report [AIAA PAPER 80-0225] 880-20966 [NASA-CR-134872] 880-15106 Summary of advanced methods for predicting high Quiet Clean Short-Haul Experimental Engine (QCSFE) speed propeller performance Over-The-Wing (OTW) propulsion system test fNASA-TN-81409] 880-15051 report. Volume 1: Summary report PROPULSION SYSTEM CONFIGURATIONS tNASA-CR-135323] 880-15125 Propulsion/airframe integration considerations for Quiet Clean Short-Haul Experimental Engine (QCSEF) high altitude hypersonic cruise vehicles Over-The Wing (OTW) propulsion system test IAIAA PAPER 80-01111 A80-18272 report. Volume 3: Mechanical performance Advanced technology effects on V/STOL propulsive RASA-CR-135325] 880- 15126 system weight PROPULSIVE EFFICIENCY [SAVE PAPER 1300] #80-20640 Engine component improvement program - Performance Oblique detonation wave ran jet improvement [NASA-CR-159192] 880-14131 (AIAA PAPER 80-0223] #80-19300 Propulsion options for the HI SPOT long endurance Quiet Clean Short-Haul Experimental Engine drone airship (QCSEE). Under-the-wing (T!TW) engine (AD-A074595] 880-14132 boilerplate Nacelle test report. Volume 2: Hypersonic cruise aircraft propulsion integration Aerodynamics and performance study, volume 1 [NASA-CR-135250) N80-14116 [NASA-CR-158926-VOL-1 ] 880-15074 PROTECTIVE COATINGS Hypersonic cruise aircraft propulsion integration Protective coatings for aircraft composites in study, volume 2 nuclear environments (NASA-CR- 158926-VOL-2] 880-15075 #D-A07 4889] 880-14 199 Quiet Clean Short-haul Experimental Engine (QCSEE) PYLON MOUNTING Over The Wing (OTW) design report Preliminary weight estimation of engine section [EASA-CN-134848] 880-15086 structure Quiet Clean Short-haul Experimental Engine ((JCSEE) [SAVE PAPER 1311] A80-20645 preliminary over-the-wing flight propulsion system analysis report rNASA-CrE-135296] 880-15095

A-2 8

SUBJECT INDEX QUIE1 ENGINE PROGRAM

P YLO N S Quiet Clean Short-haul Experimental Engine Direct side force and drag control with the aid of (QCSEE) . Under-The-wing (UTW) engine boilerplate pylon split flaps nacelle test report. Volume 3: Mechanical 980-15163 performance [NASA-CR-135251] 880-15097 Quiet Clean Short-haul Experimental Engine (QCSEB) . ' Composite fan frame subsystem test QUARTZ CRYSTALS report Investigations of the optimal configuration of !4ASA-CR-135010) 980-15098 high-stability quartz oscillators for aircraft Quiet Clean Short-haul Experimental Engine (QCSEE) and missiles Over-The-Wing (01W) boilerplate nacelle design 880-19 990 report QUIET ENGINE PROGRAM ENASA-CR-135168] 980-15099 Quiet Clean Short-Haul Experimental Engine (QCSEE) Quiet Clean Short-haul Experimental Engine (QCSEE) acoustic and aerodynamic tests on a scale model Under-The-Wing (131W) composite nacelle subsystem over-the-wing thrust reverser and forward thrust test report --- to verify strength of selected nozzle composite materials NASA-CR-135254) 980-14115 tNASA-CR-135075] 880-15100 Quiet Clean Short-Haul Experimental Engine Quiet Clean Short-haul Experimental Engine (QCSE!) . Under-the-wing (019) engine (QCSEE). Hall spline pitch change mechanism boilerplate Nacelle test report. Volume 2: design report Aerodynamics and performance [9IASA-CR-134873] N80-15101 [NASA-CR-135250) 980-14116 Acoustic analysis of aft noise reduction Quiet, Clean, Short-Haul, Experimental Engine techniques' measured on a subsonic tip speed 50.8 (QCSEE) Under-The-Wing (l11'W) engine acoustic cm (twenty inch) diameter fan --- quiet engine design program fNASA-CR-1352671 990-19117 [I4ASA-C8-134891] 880-15102 Quiet, Clean, Short-Haul Experimental Engine Quiet Clean Short-haul Experimental Engine (QCSEE) (QCSEE) Over-The-wing (OTW) engine acoustic design main reduction gears test program [NASA-CF-135268') 980-14118 NASA-CR-134669) 880-15103 Static test-stand performance of the YF-102 Quiet Clean Short-haul Experimental Engine (OCSEB) turbofan engine with several exhaust clean comhustor test report configurations for the Quiet Short-Haul Research INASA-CR-134916] Aircraft (QSRA) 4480-15104 Quiet Clean Short-haul Experimental Engine (QCSEE) rNASA-TP-1556, 980-114121 main reduction gears bearing development program Demonstration of short-haul aircraft aft noise (NASA-CR-1314890] 880-15105 reduction techniques on a twenty inch (50.8 cm) Quiet Clean Short-haul Experimental Engine (QCSEE) diameter tan, volume 1 main reduction gears detailed design report rNASA-CN-1348419] 980-15083 [NASA-C14-134872] 880-15106 Demonstration of short haul aircraft aft noise Quiet Clean Short-haul Experimental Engine reduction techniques cn a twenty inch (50.8 cm) (QCSEE) : Hamilton Standard cam/harmonic drive diameter fan, volume 3 variable pitch fan actuation system detail NASA-CR-134851 ] 880-15085 design report Quiet Clean Short-haul Experimental Engine (QCSEE) [8ASA-CR-134852] 880-15107 Over The Wing (01W) design report Quiet Clean Short-haul Experimental Engine (QCSEE) NASA-CR-134848] 980- 15086 under-the-wing engine composite fan blade design Quiet Cleen Short-haul Experimental Engine report (QCSEE) . Aerodynamic and aeromechanical (NASA-Cfi-135046) 880-15108 performance of a 50.8 cm (20 inch) diameter 1.34' Quiet Clean Short-haul Exuerimental Engine PS variable pitch fan with core flow (QCSEE) : The aerodynamic and mechanical design [NASA-C14-135017J 980-15087 of the QCSEE under-the-wing fan Quiet Clean Short-haul Experimental Engine (QCSEE) !4ASN-CR-135009] 880-15109 preliminary under the wing flight propulsion Quiet Clean Short-haul Experimental Engine (QCSEE) system analysis report composite fan frame design report rNASA-CR-134868] 980-15088 fNASA-CB-1352781 880-15110 Quiet Clean Short-haul Experimental Engine Quiet Clean Short-haul Experimental Engine (QCSEE) (QCSEF) . The aerodynamic and mechanical design 01W fan preliminary design of the QCSEE over-the-wing fan (NASA-CR-139842) ' 880-15111 [NASA-CR-134915) 4480-15089 Quiet Clean Short-haul Experimental Engine Quiet Clean short-haul Experimental Engine (QCSEE) (QCSEE) : The aerodynamic and preliminary under-the-wing engine digital control system mechanical design of the QCSEE OTW fan design report rNASA-CR-134841] rNASa-CR-134920] 980-15112 980-15090 Quiet Clean Short-haul Experimental Engine (QCSEE) Quiet Clean Short-haul Experimental Engine (QCSEE) under-the-wing engine composite fan blade design under-the-wing engine simulation report tNASA-CR-134840) [NASA-CR-134914) 880-15113 980-15091 Quiet Clean Short-haul Experimental Engine (QCSEE) Quiet Clean Short-haul Experimental Engine (OCSEE) over-the-wing engine and control simulation over-the-wing control system design report results [NASA-CB-135337) 980-15092 (NASA-CR-135049J Quiet Clean Short-haul Experimental Engine 980-15114 Quiet Clean Short-Haul Experimental Engine (QCSEE) (QCSEE) . Core engine noise measurements ball spline pitch-change mechanism whirligig fNASA-CF-135160] 880-15093 test report Quiet Clean Short-haul Experimental Engine (QCSEE) NASA-CR-135354] 880-15115 Under-The-Wing (UTW) engine composite nacelle Quiet Clean Short-haul Experimental Engine (QCSET) test report. Volume 1: Summary, aerodynamic lT nder-The-Wing (1318) boiler plate nacelle and and mechanical performance core exhaust nozzle design report [NASA-CR-159471] 980-15094• [NASA-CR-135008] 980-15116 Quiet Clean Short-haul Experimental Engine (QCSEE) Quiet Clean Short-haul Experimental Engine (QCSEP) preliminary over-the-wing flight propulsion whirl test of cam/harmonic pitch change system analysis report actuation system r NASA -CR - 1 352961 880-15095 [NASA-CR-135140] 980-15117 Quiet Clean Short-haul Experimental Engine Quiet Clean Short-haul Experimental Engine (QCSEE) (QCSEE) . Under-The-Wing (IJTW) engine boilerplate Over-The-Wing (019) propulsion systems test nacelle test report, vclume 1 report. Volume 4: Acoustic performance fNASA-CR-135249] 880-15096 [NASA-CR-135326) 880-15118 Quiet Clean Short-haul Experimental Engine (QCSEE) Under-The-Wing (UTW) composite nacelle [NASA-CR-135352] 880-15119

8-29 RADAR APPROACH CONTROL SUBJECT INDEX

Quiet Clean Short-haul Experimental Engine (QCSEE) Onboard collision avoidance system: Environmental (NASA-CE-159473] S80-15120 influence on the tracking algorithm requirements Quiet Clean Short-haul Experimental Engine 880-14 105 (QCSEE). Double-annular clean combustor Target tracking using Doppler-information in technology development report sensor oriented coordinates with a three INASA-CR-159483] 880-15121 dimensional array radar Quiet Clean Short-Saul Experimental Engine (REPT-270] 880-14325 (QCSEE) : Acoustic treatment development and N AD AR S CO P ES des ign Visual displays for air traffic control data tHASA-CR-135266] N80-15122 880-14077 Quiet Clean Short-Haul Experimental Engine RADIO NAVIGATION (c1SCEE) . Preliminary analyses and design The Omega radio navigation system --- Russian book report, volume 1 A80-19 413 rNASA-CR-1348381 N80-15123 RADIO TRABSNISSION Quiet Clean Short-Saul Experimental Engine The Omega radio navigation system --- Ilussian book (QCSEE) . Preliminary analyses and design 880-19 413 report, volume 2 BADIOGRAPBT rNASA-CR-134839] 880-15124 Discontinuous registration of industrial Quiet Clean Short-Haul Experimental Engine (QCSEE) radiographs using profile analysis and piecewise Over-The-Wing (01W) propulsion system test correlation techniques report. Volume 1: Summary report 880-17521 (NASA-CR-135323] 880-15125 RAIN Quiet Clean Short-Haul Experimental Enqine (OCHEE) A first look at the effect of severe rainfall upon Over-The Wing (OlE) propulsion system test an aircraft report. Volume 3: Mechanical performance (HASA-CR-162569] 880-15058 fNASA-CB-135325] 880-15126 NANJET ENGINES Quiet powered-lift propulsion Propulsion/airframe integration considerations for rNASA-CP-2077] 880-15127 high altitude hypersonic cruise vehicles [PlEA PAPER 80-0111] A80-18272 Oblique detonation wave ramjet R (WASA-C8-159192] 880-14131 RADAR APPROACH CONTROL An adaptation and validation of a primitive What brings us down tomorrow - Landing guidance variable mathenatical model for predicting the systems for the 1980s flows in turbojet test cells and solid fuel 880-18725 ram jets RADAR BEACONS [80-8074187] N80-1L$133 On radar in air traffic control --- conference, RANGE FINDERS Home, Jul. 1979 Hon-contacting electro-optical contouring of [P08-11-1979] 880-14065 helicopter rotor blades RADAR CROSS SECTIONS [80-8070806] 880-14111 Application of ECS guidelines to weight effective RAT TRACING aircraft design --- Radar Cross Section An air traffic channel simulation by means of (SANE PAPER 12701 880-27626 ray-tracing techniques RADAR DATA 880-14088 Radar data utilization in automating the REACTOR DESIGN sequencing of aircrafts in terminal areas Low-aspect-ratio limit of the toroidal reactor - 880-14 071 The spheromak A distributed processing system for radar data 880-17876 present at ion NEAL TINE OPERATION 880-14 075 Wire obstacle warning system /WOWS/ - A real-time Filtering of synthetic radar data airborne sensor for automatic detection and 880-19076 recognition of wirelike objects RADAR FILTERS 880-1740 2 A survey of the stochastic filtering teChniques hutotuation of flight on-line strategic control: for data processing in air-traffic control and The case of speed control on pre-established surveillance systems routes A 80-20867 N80-14 070 RADAR NETWORKS RECTANGULAR PANELS Problems related to the design and construction of Sonic fatigue design data for bonded aluminum a radar network aircraft structures N80-14 066 [P188 PAPER 80-0303] AB0-18304 Nethodology for the evaluation of a radar site RECTANGULAR WINGS 880-14067 The effects of leading edge modifications on the Organization of an integrated global maintenance post-stall characteristics of wings service --- Radar Networks (AIAA PAPER 80-0199] 880-18375 880-14069 ERDUIDAUCT RADAR RECEIVERS Pedundancy management considerations for a Implementation of air traffic control radar control-configured fighter aircraft triplex receivers with fast Fourier transform processors digital fly-by-wire flight control system 880-19086 N80-1402€ Design study of a low cost civil aviation OPS Failure detection, isolation and indication in receiver system highly integrated digital guidance and control [HASA-CR-159176] 880-15062 system RADAR SIGNATURES 880-19 027 Filtering of synthetic radar data REGENERATORS 880-14 076 FOel conservation benefits and critical RADAR TRACEING technologies of recuperative and advanced Problems related to the design and construction of conventional cycle turboshaft engines a radar network [8188 PAPPB 80-0224] 880-19301 880-19066 REGRESSION ANALYSIS Methodology for the evaluation of a radar site Regression techniques applied to paramettic 880-14 067 turbine engine simulations Tactical analysis of conflicts in an air traffic (8188 PAPER 80-0053] 880-18255 control system: Design and implementation of a REINFORCING FIBERS provisional model PRS composites for advanced gas torbine engine 880-19072 components Tracking algorithms for mono and multiradar AD-A074287] 880-15137 880-14079

8-30

SUBJECT INDEX SEALS (STOPPERS)

RELIABILITY ANALYSIS Investigation of the oscillatory and flight Study of turboprop systems reliability and behavior of rotor systems in relation with maintenance Costs atmospheric turbulence [NASA-CR-135192] N80-14129 [BNVG-FBWT-79-5] 880-14142 RELIABILITY ENGINEERIRG Unsteady flow and dynamic response analyses for US Army Test and Evaluation Command test helicopter rotor blades operations procedures: Photographic arid video [NASA-CR-159190) 880-14355 image support aviation materiel CH-46 composite rotor blade flight stress survey [80-80714883] 8130-18377 data. Volume 3: p lotted forward rotor blade REMOTE SENSORS chord, torsion and absolute loads Wire obstacle warning system /WOWS/ - A real-time [ AD-A075612] 880-15071 airborne sensor for automatic detection and Analysis of low-speed helicopter flight test data recognition of wirelike objects [80-8074141] R80-15079 #80- 17402 Model 540 rotor blade crack propagation Infrared sensor system performance simulations in vest igat ion 880-20900 [80-8074734) 880-15081 REMOTELY PILOTED VEHICLES Fffects of primary rotor parameters on flapping Experience in producing software for the ground dynamics station of a remotely piloted helicopter system [RASA-TP-1431] 880-15138 880-1 4038 ROTATING BODIES RESEARCH On the use of vibration self-damping materials in Current research on aviation weather the manufacture of parts for rotating machinery (bibliography) , 1979 N80-1 t4 135 [NASA-CR-321 I1] 880-14651 ROTATING SHAFTS RESEARCH AIRCRAFT Uirect integration of transient rotor dynamics Quiet short-haul research aircraft familiarization [NASA-TP-1597) N80-15128 document --- STOL ROTATING STALLS [NASA-TM-81149) 880-14108 A phenomenological model of the dynamic stall or a The T-28 thunder/hailstorm penetration aircraft helicopter blade profile 880-14 640 [ON?RA, TP 80. 1979-149] 880-20086 NASA/Army XV-15 tilt rotor research aircraft ROTOR AERODYNAMICS wind-tunnel test program plan --- Ames 40-ft by Evaluation of the intensity of beat-induced 80-ft wind tunnel tests - vibrations [NASA-TR-78562] 880-15067 #80-17965 RESEARCH FACILITIES Flow in transonic compressors Aeronautical Research Laboratories [AIAA PAPER 80-0124] A80-18357 [RN 7 8/301071 N80-15026 A phenomenological model of the dynamic stall of a RESEARCH MANAGEMENT helicopter blade profile NASA broad-specification fuels combustion [ONEPA, TP NO. 1979-149] 880-20086 technology program: Status and description ffect of tip planform on blade loading [NASA-Tfl-79315] 880-14126 characteristics for a two-bladed rotor in hover Unsteady flow and dynamic response analyses for [NASA-TN-78615] 3380-140149 helicopter rotor blades Acoustically swept rotor --- helicopter noise [ASA-CR-159190] 3480-14355 reduction RESEARCH PROJECTS [NASA-CASE-ARC-il 106-1) 880-14107 Navy V/STOL - A continuing initiative Effects of primary rotor parameters on flapping [SAW? PAPBE 1325) 880-20655 dynamics RESIDENTIAL AREAS [NASA-TP-1431) 880-15138 Airport noise, location rent, and the market for ROTORS residential amenities Direct integration of transient rotor dynamics A80-17'20 [NASFi-TP-1597) 880-15128 REYNOLDS NUMBER RUNWAYS Reynolds number and compressibility effects on Reflection cracking of bituminous overlays for dynamic stall of a NACA 0012 airfoil airport pavements: A state of the art [AIAA PAPER 80-0010] 880-18238 (AD-A073484] 880-14144 RIGID ROTORS Effect of weather conditions on airport operations Effects of primary rotor parameters on tlapping 880-14638 dynamics [NASA-TP-11131] 1480-15138 ROLLER BEARINGS S Quiet Clean Short-haul Experimental Engine (QCSEE) SAFETY DEVICES main reduction gears bearing development program An overvoltage safety system for direct current fNASA-CR-13 l4890) N80-15l5 aircraft generators ROLLING MOMENTS 880-1905 1 Effect of spanwise gust variations SATELLITE NAVIGATION SYSTEMS N80- 14639 Navigation error using rate of change of signal ROTARY STABILITY tine of arrival from space vehicles Experimental determination of pure rotary 880- 20 904 stability derivatives using curved and rolling The Russian satellite navigation system flow wind tunnel 880-20982 rAIAA PAPER 80-0309] 880-18308 The Ulobal Positioning Systen ROTARY WINGS 880-20992 Analysis of rotor-fuselage coupling and its effect SCALE MODELS on rotorcraft stability and response Large scale model tests of a new technology V/STOL 880-17716 concept Rotational noise of helicopter rotors [AIAA PAPER 80-0233) 880-19303 #80-17718 Scale model performance test investigation of Effect of tip planform on blade loading exhaust system mixers for an Energy Efficient characteristics for a two-bladed rotor in hover Engine /E3/ propulsion system (NASA-TN-786151 880-14049 [AIAA PAPER 80-0229] 880-20968 Acoustically swept rotor --- helicopter noise SCHEDULING reduction Aircraft delays at major 1)5 airports can be reduced NASA-CASE-ARC-li 106-1) 3380-14107 [P8-299442/4] 880-15061 Non-contacting electro-optical contouring of SEALS (STOPPERS) helicopter rotor blades Feasibility of SIC composite structures for 16814 K [AD-A070806) 33330-14111 (2500 F) gas turbine seal application [N#SA-CR-159597] 3480-14122

8-31

SECONDARY RADAR SUBJECT INDEX

Surface conforming thermal/pressure seal for Sonic-boom wave-front shapes and curvatures control devices in space vehicles associated with maneuvering flight [NASA-CASE-NSC-18822-1] 980-111800 ENASA-TP-1611] 880-14045 SECONDARY RADAR SHORT HAUL AIRCRAFT Covariance simulation of ECAS - An aircraft Ouiet short-haul research aircraft familiarization collision avoidance system document --- 5101 #80-20915 [HASA-T!-811 1l9] 880-14108 On radar in air traffic control --- conference, Quiet Clean Short-Haul Experimental Engine (QCSEE) Rome, Jul. 1979 acoustic and aerodynamic tests on a scale model (PUB-11-1979] 880-14065 over-the-wing thrust reverser and forward thrust Performance evaluation methods of a seccndary nozzle radar network rNASA-CR_135254] 380-14115 880-ill 068 Quiet Clean Short-Haul Experimental Engine An air traffic channel sinulation by means of (QCSEE) . Under-the-wing (018) engine ray-tracing technigues boilerplate Nacelle test report. Volume 2: 880-14 088 Aerodynamics and performance L-band measurements in the air traffic channel to [HASA-CR-135250] 880-14116 characterize secowIary radar systems Quiet, Clean, Short-Haul, Experimental Engine 880-18092 (QCSEH) Under-The-Wing (0TH) engine acoustic Antireflection techniques for detecting false design tracks in air traffic surveillance with (NASA-CR-135267] 880-14117 secondary radar Quiet, Clean, Short-Haul Experimental Engine 980-18100 (QCSEE) Over-The-Wing (0TH) engine acoustic design Automatic systems for airport surface mobile media [NASA-CR-135268] 880-14118 surveillance based on the use of secondary media Ouiet Clean Short-Haul Experimental Engine (QCSEE) 880-18108 Under-The-Wing (0TH) graphite/PMR cowl development SELECTION [NASA-CR-135279] 880-14119 Methodology for the evaluation of a radar site Static test-stand performance of the YF-102 980-18 067 turbofan engine with several exhaust SELF OSCILLATION configurations for the Quiet Short-Haul Research On the dynamics of compressor surge Aircraft (QSRA) 880-17900 [NASA-IP-1556) 880-14121 SENICONDUCTOB DEVICES Demonstration of short-haul aircraft aft noise Integrated circuit characteristics at 260 C for reduction techniques on a twenty inch (50.8 cm) aircraft engine-control applications diameter fan, volume 1 A80-20 112 NASA-CR-134849] 880-15083 SEPARATED PLOW Demonstration of short-haul aircraft aft noise Analytical investigation of aerodynamic reduction techniques on a twenty inch (50.8) characteristics of highly swept wings with diameter fan, volume 2 separated flow ril#SA-CR-134850] 880-15084 880-17697 Demonstration of short haul aircraft aft noise Experimental study of confluence with separation reduction techniques on a twenty inch (50.8 cm) on an afterbody of revolution diameter fan, volume 3 [ONEPA, TP NO. 1979-151] 880-20088 [RASA-CR-138851] 880-15085 The quasi-vortex-lattice method for wings with Quiet Clean Short-haul Experimental Engine (QCSEE) edge vortex separation Over The Wing (018) design report [NP.SA-CB-162530] 880-14052 [NASA-CR-1348148] 880-15086 High angle of attack characteristics of different Quiet Clean Short-haul Experimental Enqine fighter configurations (QCSEE) . Aerodynamic and aeronechanical [MBE-UPE-1883(0) ] 980-14058 performance of a 50.8 cm (20 inch) diameter 1.38 An analytical and experimental study of a short PR variable pitch fan with core flow s-shaped subsonic diffnser of a supersonic inlet r N ASA-CR-1350171 980-15087 [NASA-TM-81406] 880-15138 Quiet Clean Short-haul Experimental Engine (QCSEE) Control of forebody three-dimensional flow preliminary under the wing flight propulsion separat ions system analysis report 890-15164 (NASA-CR-134868 R80-15088 SEQUENCING Quiet Clean Short-haul Experimental Engine Radar data utilization in automating the (QCSEE) . The aerodynamic and mechanical design sequencing of aircrafts in terminal areas of the QCSEE over-the-wing fan 880-14 071 (NASA-CR-1349151 880-15089 SERVICE LIFE Quiet Clean Short-haul Experimental Engine (QCSEE) Technology of the Rolls-Royce 88211 engine under-the-wing engine digital control system #80-18868 design report SEN VOIOTORS [NASA-CR-134920] 890-15090 Aircraft torque motors --- Russian book Quiet Clean Short-haul Experimental nqine (QCSEE) 880-19 199 over-the-wing control system design report SHALE OIL INASA-CR-135337] 880-15092 Microbial deterioration of hydrocarbon fuels from Quiet Clean Short-haul Experimental 'ngine oil shale, coal, and petroleum. 1: Exploratory (QCSNE). Core engine noise measurements experiments rNASA-CR-135160] N80-15093 (AD-A073761] 880-14259 Quiet Clean Short-haul Experimental Engine (QCSEE) SHARP LEADING EDGES Under-The-wing (0TH) engine composite nacelle Euler solutions for wing and wing-body combination test report. Volume 1: Summary, aerodynamic at supersonic speeds with leading-edge separation and mechanical performance r#i## PAPER P0-0126] 880-18359 NASA-CR-159471] 880-15094 SHIPS Quiet Clean Short-haul Experimental Engine (QCSNE) Small ship-based VTOL aircraft - A design exercise preliminary over-the-wing flight propulsion [SAWN PAPER 1296] #80-20639 system analysis report SHOCK WAVE CONTROL rNASA-CR-135296] 880-15095 Turbojet-exhaust-nozzle secondary-airflow pumping Quiet Clean Short-haul Experimental Engine as an exit control of an inlet-stability bypass (QCSEE) . Under-The-Wing (0TH) engine boilerplate system for a Mach 2.5 axisymmetric nacelle test report, volume 1 mixed-compression inlet --- tevis 10- by 10-ft. [NASA-CR-135249] 880-15096 supersonic wind tunnel test Quiet Clean Short-haul Experimental Engine [RASA-TP-1532] 980-14124 (QCSEE). Under-The-wing (018) engine boilerplate SHOCK WAVE INTERACTION nacelle test report. Volume 3: Mechanical Separation due to shock wave-turbulent boundary performance layer interaction [NASA-CE-135251 ] 880-15097 [ONFRA, TP 80. 1979-146] 880-20083

8-32

SUBJECT INDE! SOUND WAVES

Quiet Clean Short-haul Experimental Engine (QCSEE) Quiet Clean Short-Haul Experimental Engine Under-The-Wing (UTW) composite nacelle subsystem (QCSEE) . Preliminary analyses and design test report --- to verify strength of selected report, volume 2 composite materials r14ASA-cR-134839] 880-1512(4 reAsA-cR-135075] 880-15100 SHORT TAKEOPP AINCRAPT Quiet Clean Short-haul Experimental Engine Assessment at full scale of exhaust nozzle-to-wing (QCSEE) . Ball spline pitch change mechanism size on STOL-01a acoustic characteristics design report A80-20 952 [NASA-cR-13 11873] 880-15101 Quiet short-haul research aircraft familiarization Acoustic analysis of aft noise reduction document --- 5101 techniques measured on a subsonic tip speed 50.8 (NASA-TM-81149] 880-114108 cm (twenty inch) diameter fan --- quiet engine JA-6A circulation control wing contractor flight proqram demonstration [NASA-CR-1314891] 880-15102 AD-A07 14888] 880-15080 Quiet Clean Short-haul Experimental Engine (QCSE?) Evaluation of approximate methods for the main reduction gears test program prediction of noise shielding by airframe [NASA-cP-13 11669] '480-15103 components Quiet Clean Short-haul Experimental Engine (QCSEE) NASA-TP-100'41 880-15129 clean combustor test report l'lie IC-lU upper surface blown flap: A Unique [NASA-CB-13'49161 880-151044 control surface Quiet Clean Short-haul Experimental Enqine (QCS!E) 880-15 157 main reduction gears bearing development program SIDESLIP [NASA-CR-134890] 880-15105 Comment on 'Handling quality criterion for heading Quiet Clean Short-haul Experimental Engine control' (QCSEE) Hamilton Standard cam/harmonic drive 880-11698 variable pitch fan actuation system detail SIGNAL RECEPTION design report Ravigation error using rate of change of signal [NASA-cR-134852] 880-15107 time of arrival from space vehicles Ouiet Clean Short-haul Experimental Sngine (QCSEE) A80-2090L1 under-the-wing engine composite fan blade design SILICON CARBIDES report Feasibility of SiC composite structures for 161414 K fEASA-CE-135046] 880-15108 (2500 E) gas turbine seal application Quiet Clean Short-haul Experimental Engine tHASA-CR-159597) 4480-1(4122 (QCSEE): The aerodynamic and mechanical design SILICON NITRIDES of the QCSEE under-the-wing fan Comparative resistance of Beta-Si384 solid INASA-cR-135009] 880-15109 solutions to molten silicon attack Quiet Clean Short-haul Experimental Engin (QCSFE) A80-18062 composite fan frame design report SIMUL&TORS tNASA-cR-135278] 880-15110 Aircraft fuel system simulator tests with Quiet Clean Short-haul Experimental Engine (QCSEE) antimisting kerosene (jet A fuel with FN-9 DIV fan preliminary design additive) --- flammability tests tNASA-CB-13 11842] 880-15111 AD-8073237] 880-114256 Quiet Clean Short-haul Experimental Engine SITES (QCSEE): The aerodynamic and preliminary Methodology for the evaluation of a radar site mechanical design of the QCSEE OTW fan 4480-114067 rNAsA-CB-134841] . 880-15112 SKIN (STRUCTURAL MEMBER) Quiet Clean Short-haul Experimental Engine (QCSEB) Protective coatings for aircraft composites in under-the-wing engine composite fan blade design nuclear environments [NASA-CR-1348 140J 880-15113 IAD-A074889] 880-114199 Quiet Clean Short-haul Experimental Engine (QCSEE) SKIN FRICTION over-the-wing engine and control simulation An improved sensing element for skin-friction results balance measurements --- supersonic drag fNASA-CR-1350449] 880-151114 measuring instrument Quiet Clean Short-Haul Ex perimental Engine (QCSEE) UAIAA PAPER 80-00(49] A80-18251 ball spline pitch-change mechanism whirligig SOIL MECEANICS test report Soil analyses and evaluations at the impact (NASA-CB-135354] 880-15115 dynamics research facility for two full-scale Quiet Clean Short-haul Experimental Engine (QCSPE) aircraft crash tests Under-The-Wing (01W) boiler plate nacelle arid [EASA-CR-159199] 880-15299 core exhaust nozzle design report SOLID SOLUTIONS tNASA-CR-135008] 880-15116 Comparative resistance of Beta-Si384 solid Quiet Clean Short-haul Experimental Engine (QCSEE) solutions to molten silicon attack whirl test of cam/harmcnic pitch change 880-18 062 actuation system SOLID-SOLID INTERFACES tNASA-cB-135140] 880-15117 Contact stress analysis of ceramic-to-metal Quiet Clean Short-haul Experimental Engine (QCSEE) interfaces --- in gas turbine engines Over-The-Wing (01W) propulsion systems test tAD-807 441491] 880-1(41417 report. Volume II: Acoustic performance SONIC BOOMS [ 14ASA-cR-135326] 880-15118 Sonic-boom wave-front shapes and curvatures Quiet Clean Short-haul Experimental Engine (QCSEE) associated with maneuvering flight under-The-Wing (1318) composite nacelle [NASA-TP-1611) 880-140445 [NASA-CR-135352] 880-15119 SOOT Quiet Clean Short-haul Experimental Engine (QCSEE) Dispersion of sound in a combustion duct by fuel fNASA-CR-159 1473] 880-15120 droplets and soot particles Quiet Clean Short-haul Experimental Engine A80-20953 (QCSEE) . Double-annular clean combustor SOOND PROPAGATION technology development report Dispersion of sound in a combustion duct by fuel rNASA-CB-159483] 880-15121 droplets and soot particles Quiet Clean Short-Haul Experimental Engine A80- 20953 (QCSEE): Acoustic treatment development and The analysis of sound propagation in jet engine design ducts using the finite difference method [34ASA-CR-135266) 880-15122 (AD-A074233] 880-114853 Quiet Clean Short-Haul Emperimental Engine SOUND WAVES (QSCEE) . Preliminary analyses and design Applications of diffraction theory to aeroacoustics report, volume 1 aircraft noise [NASA-CR-134838] 880-15123 880-144870

8-33

SPACE SHUTTLE ORBITERS SUBJECT INDEX

SPACE SHUTTLE ORBITERS Modular strapdovn guidance unit with embedded Altitude response of several airplanes during microprocessors landing approach --- including space shuttle [8188 PAPER 78-1239) #80-18534 (NASA-Tfl-80186) P80-14139 Development of aiding GPS/strapdown inertial SPACECRAFT COMPONENTS navigation system Surface conforming thermal/pressure seal --- for 880-14031 control devices in space vehicles Hethods for strap-down attitude estimation and [RASA-CAS!-MSC-18422-l] 880-14400 navigation with accelerometers SPATIAL DISTRIBUTION N80-1'4034 Air traffic density and distribution measurements STRESS ANALYSIS r 80-8073229] 880-14068 "atigue life prediction of a bonded splice joint SPEECH RECOGNITION [818k PAPER 80-0305] 880-18306 Vocabulary specification for automatic speech Contact stress analysis of ceramic-to-metal recognition in aircraft cockpits interfaces --- in gas turbine engines 880-14303 (80-8074491] 880-14417 1 #0-8073703] SPEED CONTROL Thermo-mechanical stress analysis of advanced Automation of flight on-line strategic control: turbine blade cooling configuration The case of speed control on pre-established AD-8074098] 880-15136 routes STRESS CONCENTRATION 880-14070 Determination of the stress intensity factor of SPOILERS composite structural members Roll control by digitally controlled segment #80-17 958 spoilers STRESS-STRAIN DIAGRAMS 880-15156 Review of investigations into aeronautics related In-flight measured characteristics of combined fatigue Federal Republic of Germany flap-spciler direct lift controls tLBF-S-142] 880-14422 880-15165 STBUCTURAL ANALYSIS Unsteady aerodynamics of two-dimensional spoilers Application of the SIRS concept to Navy helicopters at low speeds systems analysis of flight data recorders of flight conditons of helicopters for structural SPOT WELDS - analysis Loading tests of a wing structure for a hypersonic 80-8974801] 880-15030 aircraft Computer simulation of engine systems [NASA-TP-1596] 880-15068 [NASA-TN-79290] 880-15 132 STABILITY DERIVATIVES STRUCTURAL DESIGN Estimation of the accuracy of dynamic Sonic fatigue design data for bonded aluminum flight-determined coefficients aircraft structures IAIAA PAPER 80-0171) 880-17700 8188 PAPER 80-0303] #80-18304 Experimental determination of pure rotary Assessment of analytic methods for the prediction stability derivatives using curved and rolling of aerodynamic characteristics of arbitrary flow wind tunnel bodies at supersonic speeds (8188 PAPER 80-0309) 880-18308 (AIAA PAPER 80-0071] 880-19308 Altitude response of several airplanes during Quiet Clean Short-haul Experimental Engine landing approach --- including space shuttle (QCSEH). The aerodynamic and mechanical design (NASA-Tfl-80186] 880-14139 of the QCSEE over-the-wing fan STATIC AEPODYNAMIC CHARACTERISTICS (RASA-CR-134915] 880-15089 Evaluation of the aerodynamic characteristics of a Quiet Clean Short-haul Experimental Engine (QCSEE) 1/20-scale 8-10 model at Mach numbers from 0.30 Over-The-Wing (01W) boilerplate nacelle design to 0.75 report tAD-8074867] 880-15Q55 (NASA-CR-135168] 880-15099 STATIC FIRING STRUCTURAL DESIGN CRITERIA Static test-stand performance of the YF-102 Computer simulation of engine systems turbofan engine with several exhaust [NASA-rM-79290] 1180-15132 configurations for the Quiet Short-Haul tesearch Low cost aircraft flutter clearance --- conference Aircraft (QSRA) [ AGARE-CP-278) 1180-15141 tNASA-TP-1556] 880-14121 STRUCTURAL ENGINEERING STATIC PRESSURE Composite structural materials Some practical aspects of the calibration of air [HASA-CR-162578) 880-15076 data systems Quiet Clean Short-haul Experimental Engine (QCSEF) 880-18 865 Under-The-Wing (UTW) composite nacelle STATIC STABILITY tNASA-C11-135352] 880-15119 Simulator study of stall/post-stall STRUCTURAL FAILURE characteristics of a fighter airplane with Sonic fatigue design data For bonded aluminum relaxed longitudinal static stability --- F-16 aircraft structures rNASA-Tp-15381 880-14136 rAIkA PAPER 80-0303] 880-18304 STATISTICAL ANALYSIS STRUCTURAL INFLUENCE COEFFICIENTS A statistical method applied to pilot behavior Structural parameters that influence the noise analysis in tnultiloop systems reduction characteristics of typical general #80-18537 aviation naterials A simple design synthesis method used to estimate (AIAA PAPER 80-0038] 880-18248 aircraft gross weight STRUCTURAL STABILITY [SANE PAPER 1313] #80-20647 Au analytical method of testing pavement strength STOCHASTIC PROCESSES 880- 17 998 A survey of the stochastic filtering techniques An empirical approach for checking flutter for data processing in air-traffic control and stability of gliders and light aircraft surveillance systems 1180-lb 144 #80- 20 867 STRUCTURAL VIBRATION STRAPOOWN INERTIAL GUIDANCE Gas turbine carcase and accessory vibration - Development aspects of a dynamically tuned gyro Problems of measurement and analysis for strapdown - 8885 --- Attitude and Heading AS 0-17730 Reference System Evaluation of the intensity of beat-induced 880- 17 553 vibrations A strapdown inertial reference system for 880-17965 commercial airline use in navigation and flight STRUCTURAL WEIGHT control Application of finite element analysis to - #80-17558 derivation of structural weight An integrated strapdown guidance and control (SAWE PAPER 1271] #80-20627 system for launch veMcle application #80-17559

A-3H

SUBJECT INDEX SWEEP EFFECT

A method of simplifying weight and balance for Turbojet-exhaust-nozzle secondary-airflow pumping small aircraft as an exit control of an inlet-stability bypass [SANE PAPER 1278] 880-20630 system for a Mach 2.5 axisymmetric Application of parametric weight and cost mixed-compression inlet --- Lewis 10- by 10-ft. estimating relationships to future transport supersonic wind tunnel test aircraft [NASA-TP-1532) 880-14128 [sANE PAPER 1292] 880-20637 An analytical and experimental study of a short A simple design synthesis method us€d to estimate s-shaped subsonic diffuser of a supersonic inlet aircraft gross weight [NASA-Tfl-81406] 880-15138 SAWE PAPER 13131 880-20647 SUPERSONIC JET PLOW Weight impact of VIOL Conceptual design and performance estimates for a [SANE PAPER 1326] 880-20656 supersonic aerodynamic window for the ATA vacuum SUBSONIC FLOW system aperture A numerical approach to subsonic viscous-inviscid [UCRL-15051] 880-15183 interaction SUPERSONIC SPEEDS 880-19070 Assessment of analytic methods for the prediction Summary of advanced methods for predicting high of aerodynamic characteristics of arbitrary speed propeller performance bodies at supersonic speeds IAIAA PAPER 80-0225] 880-20966 [8188 PAPER 80-0071] A80-19308 Two dimensional aerodynamic interference effects SUPERSONIC TNANSPORTS on oscillating airfoils with flaps in ventilated The next supersonic transport subsonic wind tunnels --- comutational fluid A80-20214 dynamics Flight and wind tunnel test results of the [NASA-CR-3210] 880-14087 mechanical jet noise suppressor nozzle Summary of advanced methods for predicting high 8188 PAPER 80-0165) 880-2097 1 speed propeller performance SUPPORTS [NASA-TM-81 1409] 880-15051 The CF6 jet engine performance improvement: New Unsteady effects of a control surface in two Front mount dimensional, subsonic and transonic flow rNASA-CR-159639) 880-14127 880-15168 SUEFACE NAVIGATION SUBSONIC SPEED The Omega radio navigation system --- Russian book Optimized aerodynamic design process for subsonic A80-19413 transport wing fitted with winglets --- wind SURGES tunnel model On the dynamics of compressor surge - [NASA-CB-159180] 880-14058 880-17900 Aerodynamic characteristics of moving SURVEILLANCE RADAR trailing-edge controls at subsonic and transonic Weather detection using airport surveillance radar speeds 880-19 129 880-15169 A survey of the stochastic filtering techniques SUPERSONIC AIRCRAFT for data processing in air-traffic control and Application of a higher order panel method to surveillance systems realistic superscnic configurations 880-20867 [AIAA PAPER 79-0274) 880-17696 On radar in air traffic - control --- conference, SUPERSONIC CRUISE AIRCRAFT NESEARCE Rome, Jul. 1979 Plight control and configuration design [P08-11-1979) 880-14065 considerations for highly maneuverable aircraft Problems related to the design and construction of 880-15154 a radar network SUPERSONIC DRAG 880-14066 An improved sensing element for skin-friction Methodology for the evaluation of a radar site balance measurements --- supersonic drag 880-14067 measuring instrument Performance evaluation methods of a secondary [AIAA PAPER 80-0049] A80-18251 radar network SUPERSONIC FLIGBT 880-14068 Investigation of leading-edge devices for drag Organization of an integrated global maintenance reduction of a 60-deg. delta wing at high angles service --- Radar Networks of attack 880-14069 [AIAA PAPER 80-03101 A80-18309 Simulation of a surveillance and control system of SUPERSONIC FLOW surface traffic in an airport An improved sensing element for skin-friction 880-1407 3 balance measurements --- supersonic drag Tracking algorithms for mono and multiradar measuring instrument 880-14074 rAIAA PAPER 80-0049) 880-18251 Filtering of synthetic radar data Suler solutiens for wing and wing-body combination 880-14076 at supersonic speeds with leading-edge separation Implementation of air traffic control radar [8188 PAPER 80-0126] 880-18359 receivers with fast Fourier transform processors Mach 3 hydrogen external/base burning 880-14 086 tAIRA PAPER 80-0280) A80-19311 Development trends of airport surface traffic Numerical simulation of supersonic inlets using a control radar three-dimensional viscous flow analysis 880-14087 tAIAA PAPER 80-0384] A80-20969 An air traffic channel simulation by means of An analytical and experimental study of a short ray-tracing techniques S-shaped subsonic diffuser of a supersonic inlet 88 0-14 088 (8188 PAPER 80-0386] A80-20970 Antireflection techniques for detecting false Summary of advanced methods for predicting high tracks in air traffic surveillance with - speed propeller performance secondary radar rNASA-TM-81409) 880-15051 580- 14 100 SUPERSONIC INLETS Automatic systems for airport surface mobile media Improved numerical simulation of high speed inlets surveillance based on the use of secondary media using the Navier-Stokes equations 880-14104 [AIAA PAPER 80-0383] 880-18340 SURVIVAL EQUIPMENT Dynamic response of a Mach 2.5 axisymmetric inlet Aeronautical systems technology needs: Escape, and turbojet engine with a poppet-value rescue and survival - controlled inlet stability bypass system when I AD-A074906] 880-111061. subjected to internal and external airflow SWEEP EFFECT transients Acoustically swept rotor --- helicopter noise [WASA-TP-1531] 880-14123 reduction [NASA-CASE-ARC-11106-1 880-14107

8-35

SWEPT WINGS SUBJECT INDEX

SWEPT WINGS T-37 AIRCRAFT Analytical investigation of aerodynamic Effects of varying visual display characteristics characteristics of highly swept wings with of the 1-AG, a 1-37 flight simulator separated flow [AD-A071410] 880-15180 880-17 697 TAIL ASSEMBLIES Experimental and computational study of transonic On the effect of wing wake on tail characteristics flow about swept wings 880- 15 174 tAIAA PNPER 80-0005] 880-18235 TARGET ACQUISITION Investigation of leading-edge devices for drag Infrared sensor system performancesimnlatjcns rednction of a 60-deg. delta wing at high angles A80-20900 of attack TARG RECOGNITION - (8188 PAPER 80-0310.] 880-18309 Wire obstacle warning system /WOWS/ - A real-time A computer code to model swept wings in an airborne sensor for automatic detection and adaptive wall transonic wind tunnel recognition of wirelike objects (AIAA PAPER 80-0156] 880-19287 880-17407 Hybrid vortex method for lifting surfaces with TECHNOLOGICAL FORECASTING free-vortex flow What brings us down tomorrow - Landing guidance (AlAN PAPEN 80-0070] 880-19307 systems for the 1980s Wind tunnel measurements and analysis of some A80-18 725 unusual control surfaces on two swept wing The next supersonic transport fighter configurations 080-20214 880-15155 Application of parametric weight and cost SWITCHING THROW! estimating relationships to future transport A!ROPP - Nessage and data switching systems for aircraft aeronautical operations [SAWE PAPER 12921 880-20637 880-19579 Aeronautical systems technology needs: Escape, SYSTEM EFFECTIVENESS rescue and survival Concerning the information efficiency of CAD-A074906] N80-14061 aerodynamic experiments TECHNOLOGY ASSESSMENT 800-17671 Preparing aircraft propulsion for a new era in SYSTEM FAILURES energy and the environment Failure detection, isciation and indication in 080-17737 highly integrated digital guidance and control Technology of the Polls-Boyce RB211 engine system 880-18 864 880-14027 Tilt rotor - An effective V/STOL concept SYSTEMS ANALYSIS [SAWE PAPER 1273] 080-20628 A high accuracy flight profile determining system Small ship-based VTOL aircraft - A design exercise systems analysis of inertial navigation [SANE PAPER 1296] 880-20639 system for aircraft position determination Navy V/STOL - A continuing initiative 880-1'4042 [SAWE PAPER 1325) 080-20655 Integration of flight and fire control --- systems Review of investigations into aeronautics related analysis of digital ccntrolled integrated flight fatigue Federal Republic of Germany and fire control systems LBY-S-142] 880-14422 880-14043 Technical evaluation report on the 28th Guidance A computerized method for calculating flutter and Control Panel Symposium on Advances in characteristics of a system characterized by two Guidance and Control Systems Using Digital degrees of freedom Techniques rNASA-TN-80153] 880-14055 [AGARD-AR-148] 880-15140 Linear systems analysis program, L224(QR) . Volume The IC-lA upper surface blown flap: A unique 1: Engineering and usage control surface INASA-CP-2861) 880-14137 880-15 157 Application of the SINS concept to Navy helicopters TECHNOLOGY UTILIZATION systems analysis of flight data recorders of Technologies conceived for the utilization of flight conditons of helicopters for structural ceramics in turboengines ana lysis [ONERA, TB NO. 1979-132] A80-20076 I A0-A074801] 980-15030 TEMPERATURE EFFECTS Loran digital phase-locked loop and HF front-end On the influence of steady state temperature and system error analysis pressure distortion on the flow characteristics [NASA-CR-162731 ] 880-15065 in an installed multistage jet engine Compressor Design study for ATA vacuum system aperture 880- 17724 [UCRL-15050] 880-15182 Integrated circuit characteristics at 260 C for SYSTEMS ENGINEEBING aircraft engine-control applications A distributed processing system for radar data -. A80-20112 present at ion TERMINAL FACILITIES 880-14 075 Marseilles - Metamorphosis of an airport Development trends of airport surface traffic A80-17 999 control radar Centralized ground power systems conserve energy 880-14 087 880-18000 Onboard collision avoidance system: Environmental Computer simulation of anair cargo small package influence on the tracking algorithm requirements sorting system 880-14 185 080-20 866 Design study of a low cost civil aviation GPS Models for freight access to air terminals receiver system A80-20869 (NASA-CF-159176] 880-15062 TERMINAL GUIDANCE Aircraft anti-icing/de-icing Map-matching techniques for terminal guidance [AD-A074128] 880-15078 using Fourier phase information - Design criteria for optimal flight control systems A80-17517 study of optimal flight control systems TERN AIR AWALYSIS engineering for feedback control Performance evaluation of image correlation (AD-A074092] 880-15139 techniques --- for aircraft inertial navigation systems 880-17534 T TEST CHAMBERS T-28 AIRCRAFT Investigation of noise hazards in the engine test The T-28 thunder/hailstorm penetration aircraft cell, CR8 Baden-Soellingen 880-14 640 (80-8074391] 880-14147

A-3 6

SUBJECT INDEX TRAJECTORY ANALYSIS

Climatic chamber testing aircraft, engines TILT ROTOR AIRCRAFT armament and avionics; Test operations procedure Tilt rotor - An effective V/STOL concept environmental test chambers and facility for (SANE PAPER 1273) 880-20628 testing aircraft construction materials and NASA/Army XV-15 tilt rotor research aircraft engines wind-tunnel test program plan --- Ames 40-ft by [AD-A074049] N80-15181 80-ft wind tunnel tests TEST EQUIPNENT [NAS#-TN-78562] 880-15067 Impact of new instrumentation on advanced turbine Quiet powered-lift propulsion research tNASA-cP-2017] 880-15127 fNASA-TN-79301] 480-15133 TINE DEPENDENCE TEST FACILITIES Application of the multistage axial-flow Flight and wind tunnel test results of the compressor time-dependent mathematical modeling mechanical jet noise suppressor nozzle technique to the TF41-A-1 modified block 76 rAIAA PAP2F 80-0165) 880-20971 compressor Climatic chamber testing aircraft, engines [#0-80711478] 880-14 134 armament and avionics; Test operations procedure TINE NEASURING INSTRUNENTS environmental test chambers and facility for Investigations of the optimal configoration of testing aircraft construction materials and high-stability quartz oscillators for aircraft engines and missiles (80-8074049] 880-15181 A80-19 990 TESTS TINE SERIES ANALYSIS OS Army Test and Evaluation Command test Excitation and analysis technique for flight operations procedures: Photographic and video flutter tests image support aviation materiel [NBB-UF-11146(0) ] 880-14140 AD-A074883) 880-14377 TOKA!A DEVICES TF-41 ENGINE Low-aspect-ratio limit of the toroidal reactor - Application of the, multistage axial-flow The spheronak compressor time-dependent mathematical modeling 880-1787 6 technique to the TP41-8-1 modified block 76 TOLERANCES (NECHANICS) compressor Discontinuous registration of industrial tA0-A07448 880-18134 radiographs using profile analysis and piecewise THEE HI CONTROL COATINGS correlation techniques Thermal barrier coatings for aircraft gas turbines 880-17 521 [AIAA PAPER 80-0302] 880-18303 TOROIDAL PLASNAS THEN HAL RESISTANCE Low-aspect-ratio limit of the toroidal reactor - Surface conforming thermal/pressure seal --- for The spheromak control devices in space vehicles 880-17876 [NASA-CASE-NSc-18822-1] 880-14400 TORQUE NOTORS THEE HOD! HAHIC CYCLES Aircraft torque motors --- Russian book Installation effects on cycle selection for small A80-19 199 turbo-fan engines TORSIONAL STRESS tAIAA PAPER 80-0106) 880-19280 CB-116 composite rotor blade flight stress survey Fuel conservation benefits and critical data. Volume 3: Plotted forward rotor blade technologies of recuperative and advanced chord, torsion and absolute loads conventional cycle turboshaft engines (80-8075612] 880-15077 [8188 PAPER 80-0224] #80-19301 TEACHING (POSITION) TREE NODYNAHIC PROPERTIES Some practical aspects of the calibration of air Thermal state of structural members of aircraft data systems engines --- Russian book 880-18 865 #80-19412 A nonlinear observer/command generator tracker THEPHOHECHANICAL TREATNENT approach to the XM-97 helicopter gun turret Thermo-mechamical stress analysis of advanced control law design turbine blade cooling configuration 880-20 879 [AD-A074098] 880-15136 TEACHING FILTERS THIN AIRFOILS A survey of the stochastic filtering techniques Two dimensional aerodynamic interference effects for data processing in air-traffic control and on oscillating airfoils with flaps in ventilated surveillance systems subsonic wind tunnels --- computational fluid 880-20867 dynamics TRAILING EDGES tNASA-CR-32101 880-14047 Experimental study of confluence with separation THREE DIHENSIONAL BOUNDARY LATER on an afterbody of revolution The minimum induced drag of aerofoils [ONFRA, TP NO. 1979-151) 880-20088 [RACA-121) 880-15038 The quasi-vortex-lattice method for wings with THREE DINEHSIOHL FLOW edge vortex separation Numerical simulation o f supersonic inlets using a [NASA-CR-162530] 880-14052 three-dimensional viscous flow analysis TRAILING-EDGE FLAPS rAIAA PAPER 80-0384] A80-20969 Unsteady effects of a control surface in two Control of forebody three-dimensional flow dimensional, subsonic and transonic flow separations 880-15168 480-15164 Aerodynamic characteristics of moving Computation of three-dimensional flow in turbofan trailing-edge controls at subsonic and transonic mixers and comparison with experimental data speeds [NAS&-TN-81410) 880-15364 880-15169 THRUST TRAINING AIRCRAFT Studies of leading-edge thrust phenomena The rational design of an airfoil for a high [#188 PAPER 80-0325] 880-18315 performance jet trainer THRUST AUGHENTATION [8188 PAPER 80-0328) 880-18317 Recent development of a jet-diffuser ejector Forebody vortex blowing: A novel control concept [#188 PAPER 80-0231] 880-18277 to enhance departure/spin recovery Large scale model tests of a new technology V/STOL characteristics of fighter and trainer aircraft concept 880-15 172 [8188 PAPER 80-0233] 880-1 9303 TRAJECTORY ANALYSIS THRUST REVERSAL Trajectory behaviour of a control configurated Quiet Clean Short-Haul Experimental Engine (QCSEE) aircraft subjected to random disturbances acoustic and aerodynamic tests on a scale model R80-1517/1 over-the-wing thrust reverser anã forward thrust nozzle [NASA-CR-13525 1$) 880-14115

8-37

TRAJECTORT NEASURENENT SUBJECT INDEX

TRAJECTORY NEASURENENT Quiet Clean Short-haul Experimental Engine (QCSEE) A survey of the stochastic filtering techniques under-the-wing engine composite fan blade design for data processing im air-traffic control and report surveillance systems [NASA-CR-135046] 880-15108 980-20 867 Thermo-mechanical stress analysis of advanced TRAJEC?ORT OPTINIZATION turbine blade cooling configuration A comparison of first and second order techniques [ 90-9074098) 880-15136 for computing optimal horizontal gliding TURBINE ENGINES trajectories --- for low level weapons delivery The physical and chemical characterization of ten [AIAA PAPER 80-0061) 980-18260 military turbine engine lubricants Constrained optimum trajectories with specified [90-9074073] 880-15265 range TUB BO CON PEE S SOR S 980-18538 On the influence of steady state temperature and TRANSFER FUNCTIONS pressure distortion on the flow characteristics The transfer of carbon fibers through a commercial in an installed multistage jet engine compressor aircraft water separator and air cleaner 980-17724 Damping capacity of plastic compressor blades f NASA-CR-159183) 880-14359 TRANSONIC CONPRESSOES 980-19868 Flow in transonic compressors Modification of axial compressor streamline [9199 PAPER 80-0124] 980-18357 program for analysis of engine test data TRANSONIC FLOW [NASA-TN-79312] 880-14051 Experimental and computational study of transonic Application of the multistage axial-flow flow about swept wings compressor time-dependent mathematical modeling (9199 PAPER 80-0005] 980-18235 technique to the TF91-A-1 modified block 76 Engine aerodynamic installation by numerical compressor simulat ion (90-9074478] 880-14134 [AIA# PAPER 80-0108) A80-18271 TURBOFAN ENGINES An inverse transonic wing design method Technology of the Rolls-Royce 98211 engine 9199 PAPER 80-0330] 980-18319 980-18864 Analysis of transonic flow about harmonically Installation effects on cycle selection for small oscillating airfoils and wings turbo-fan engines [9199 PAPER 80-0149] 980-18367 19199 PAPER 80-0106] 980-19280 A computer code to model swept wings in an An experimental model investigation of turbofan adaptive wall transonic wind tunnel engine internal exhaust gas mixer configurations 19199 PAPER 80-0156] 980-19287 (9199 PAPER 80-0228) 980-19302 Separation due to shock wave-turbulent boundary Scale model performance test investigation of layer interaction exhaust system mixers for an Energy Efficient (08889, IP 80. 1679-146) 980-20083 Hngine /E3/ propulSion system An investigation of several factors involved in a IAIAA PAPER 80-0229) 980-20968 finite difference procedure for analyzing the Quiet Clean Short-Haul Experimental Engine (QCSEE) transonic flow about harmonically oscillating Over-The-Wing (OTW) propulsion system test airfoils and wings report. Volume 2: Aerodynamics and performance rNASA-cR-159143] 880-14056 engine performance tests to define A users guide for A344: A program using a finite propulsion system performance on turbofan engines difference method to analyze transonic flow over (NASA-CR-135324] 880-14120 oscillating airfoils Static test-stand performance of the !F-102 T:NASA-CR-159141] 880-15052 turbofan engine with several exhaust Unstead y effects of a control sur face in two configurations for the Quiet Short-Haul Research dimensional, subsonic and transonic flow Aircraft (QSRA) 880-15168 [RASA-TP-1556) H80-14121 TRANSONIC SPEED The CF6 jet engine performance improvement: Hew Aerodynamic characteristics of moving front mount trailing-edge controls at subsonic and transonic [NASA-CR-159639] P80-18127 speeds Study of turboprop systems reliability and 880-15169 maintenance costs TRANSONIC WIND TUNNELS [N#S#-CR-135192] 880-14129 A computer code to model swept wings in an Quiet Clean Short-haul Experimental Engine (QCSFE) adaptive wall transonic wind tunnel Over The Wing (01W) design report rAIftA PAPER 80-0156] 880-19287 INASA-CR-139848] 880-15086 TRANSPORT AIRCRAFT Quiet Clean Short-haul Experimental Engine (QCSEE) Application of parametric weight and cost preliminary under the wing flight propulsion estimating relationships to future transport system analysis report aircraft (NASA-CR-13 11868) 880-15088 (SANE PAPER 1292) 980-20637 Computation of three-dimensional flow in turbofan Optimized aerodynamic design process for subsonic mixers and comparison with experimental data transport wing fitted with winglets --- wind (PASA-TN-81410] 880-15364 tunnel model TURBO? AN S [NASA-CR-159180] 880-14054 Demonstration of short-haul aircraft aft noise Accident investigation reduction techniques on a twenty inch (50.8 cm) 880-1463 6 diameter fan, volume 1 TRANSPORTATION NETWORKS (NASA-CR-13 1$8491 880-15083 Shipping by air - Is the value of your time worth it Demonstration of short-haul aircraft aft noise 980-20868 reduction techniques on a twenty inch (50.8) TRENDS diameter fan, volume 2 Development trends of airport surface traffic NASA-CR-134850) 880-15088 control radar Demonstration of short haul aircraft aft noise 880-14087 reduction techniques on a twenty inch (50.8 Cm) TURBINE BLADES diameter fan, volume 3 Discontinuous registration of industrial (HASA-Cfi-134851 ] 880-15085 radiograpbs using prcfile analysis and piecewise Quiet Clean Short-haul Experimental Ingine correlation techniques (QCS!P). The aerodynamic and mechanical design 980-17 521 of the QCSEE over-the-wing fan Optimization of turbime nczzle cooling by (WASA-C8-134915] 880-15089 combining impingement and film injection Quiet Clean Short-haul Experimental Engine [AIAA PAPER 80-0299) 980-19316 (QCSEE) . Composite fan frame subsystem test Digital system for dynamic turbine engine blade report displacement measurements [NASA-cR-135010] 880-15098 [NASA-11-81382) 880-19113

9-38

SUBJECT INDEX VARIABLE GEOMETRY STRUCTURES

Quiet Clean Short-haul Experimental Engine Separation due to shock wave-turbulent boundary (QCSES) : Hamilton Standard cam/harmonic drive layer interaction variable pitch fan actuation system detail [ONENA. TP NO. 1979-146] 880-20083 design report - General potential theory of arbitrary wing sections [N&SA-CR-134852) 880-15107 NACA-452) 880-15046 Quiet Clean Short-haul Experimental ngine (QCSEE) Unsteady effects of a control surface in two composite fan frame design report dimensional, subsonic and transonjc flow (NASA-CR-135278] !80-15110 880-15 168 Quiet Clean Short-haul Experimental Engine (QCSEE) UTW fan preliminary design [NASA-CR-1348t42] N80-15111 U Quiet Clean Short-haul Experimental Engine ULTRAHIGH FREQUENCIES (QCSEE) The aerodynamic and preliminary I-band measurements in the air traffic channel to mechanical design of the QCSEE 01W fan characterize secondary radar systems [RASA-CR-134841] 880-15112 880-14092 Quiet Clean Short-haul Experimental Engine (QCSEE) UNSTEADY PLOW under-the-wing engine composite fan blade design Unsteady flow and dynamic response anal yses for fNASA-CN-134880) 880-15113 helicopter rotor blades Quiet Clean Short-haul Experimental Engine (QCSBE) rNASA_CR_159190] 880-14355 whirl test of cam/harmonic pitch change Unsteady effects of a control surface in two actuation system dimensional, subsonic and transonic flow rNASA-CR-13518o] N80-15117 880-15 168 TURBOJFT ENGINES UJSWEPT WINGS Technologies conceived for the utilization of A flutter-speed formula for wings of high aspect ceramics in turboengines ratio (ONERA, 1? NO. 1979-132) 880-20076 4480-15 187 Dynamic response of a Mach 2.5 axisymmetric inlet UPPER SURFACE BLOWN FLAPS and turbojet engine with a poppet-value Rxploratory studies of the cruise performance of controlled inlet stability bypass system when upper surface blown configuration: Experimental subjected to internal and external airflow program, high-speed force tests tram sie nt 5 [NASA-CR-159134] 880-15070 (NASA-TP-1531] 880-18123 Exploratory studies of the cruise performaflce of Turbojet-exhaust-nozzle secondary-airflow pumping upper surface blown configurations: - as an exit control of an inlet-stability bypass Experimental program, high-speed pressure tests system for a Mach 2.5 axisymmetric (NASA-CR-159135] 880-15071 mixed-compression inlet --- Lewis 10- by 10-ft. Exploratory studies of the cruise performance of supersonic wind tunnel test upper surface blown configurations: Program [WASA-TP-1532] R80-14128 analysis and conclusions An adaptation and validation of a primitive [NASA-CR-159136] 880-15072 variable mathematical model for predicting the URBAN BESPARCB flows in turbojet test cells and solid fuel Airport noise, location rent, and the market for ram jets residential amenities [80-8078187] 880-18133 880-17 720 An extension of engine weight estimation USER REQUIRENERTS techniques to compute engine production cost A pre-design code for predicting engine (AD-A07 11454] N80-15135 acquisition costs TURBONACBINE BLADES (8188 PAPER 80-0055] 880-19269 Impact of new instrumentation on advanced turbine Tilt rotor - An effective V/STOL concept research (SANE PAPER 1273] 880-20628 [NASA-TN-79301 ] N80-15133 TURBOPROP ENGINES Study of turboproç systems reliability and V maintenance costs V/STOL AIRCRAFT rNAsA-CR-135192) 880-14129 The criticality of engine exhaust simulations on TURBO SHAFTS VSTOI. model-measured ground effects Fuel conservation benefits and critical [AIAA PAPER 80-0230] 880-18276 technologies of recuperative and advanced Large scale model tests of a new technology V/STOL conventional cycle turboshaft engines concept (AIAA PAPER 80-0224] 880-19301 [AIAA PAPER 80-0233] 880-19303 TURBULENT BOUNDARY LAYER Tilt rotor - An effective V/STOL concept Separation due to shock wave-turbulent boundary (SANE PAPER 1273] 880-20628 layer interaction Advanced technology effects on V/STOL propulsive rONERA, TP NO. 1979-186) 880-20083 system weight Applications of modern hydrodynamics to (SANE PAPER 1300] A80-206440 aeronautics. Part 1: Fundamental concepts and tm avv V/STOL - A continuing initiative the most important theorems. Part 2: ISAWE PAPER 13251 ABO-20655 Applications VACUUB SYSTEMS [RACA-116] 880-15034 Design study for AlA vacuum system aperture TURBULENT PLOW [UCRL-15050] 880-15182 Aeroacoustic measuring techniques in or outside Conceptual design and performance estimates for a turbulent flows supersonic aerodynamic window for the ATA vacuum 880-14876 system aperture On the effect of wing wake on tail characteristics ruCRL-15051] 880-15183 880-151714 VAPORIZING TURBULENT JETS Effect of degree of fuel vaporization upon Photon correlation laser velocimeter measurements emissions for a premixed partially vaporized in highly turbulent flow fields combustion system --- for gas turbine engines AIAA PAPER 80-0384] 880-18328 NASA-TP-1582) 880-18 125 TURBULENT MIXING VARIABLE CYCLE ENGINES Computation of three-dimensional flow in turbofan Multi-variable cycle optimization by gradient mixers and comparison with experimental data methods --- for variable-cycle engines rBASA-TM-81810] 1490-153614 [8188 PAPER 80-0052) A80-182544 TWO DIMENSIONAL PLOW VARIABLE GEOMETRY STRUCTURES Engine aerodynamic installation by numerical Ringed vehicle equations of motion simulat ion [8188 PAPER 80-0368] 880-18336 [AIAA PAPER 80-0108) 880-18271 Improved numerical simulation of high speed inlets using the Navier-Stokes equations [AIAA PAPER 80-0383] 880-18380

A-3 9 VARIABLE PITCH PROPELLERS SUBJECT INDEX

VARIABLE PITCH PROPELLERS Enhanced departure/spin recovery of fighter Quiet Clean Short-haul Experimental ngine aircraft through control of the forehody vortex (QCSEE). Aerodynamic and aeromechanical orientation performance of a 50.8 cm (20 inch) diameter 1.34 18188 PAPER 80-0173] #80-18352 PR variable pitch fan with core flow Summary of advanced methods for predicting high [148S8-CR-135017] 880-15087 speed propeller performance 880-20966 VELOCITY DISTRIBUTION (AIAA PAPER 80-0225] Effect of tip planform on blade loading The quasi-vortex-lattice method for wings with characteristics for a two-bladed rotor in hover edge vortex separation 880-14052 [NASA-TH-78615) 880-14049 [NASA-CS-162530] VERTICAL TAKEOFF AIRCRAFT Theoretical study of aerodynamic characteristics Small ship-based VIOL aircraft - A design exercise of wings having vortex flow 880-14053 [SANE PAPER 1296] 880-20639 [NASA-CR-159184] Weight impact of VIOL Porebody vortex blowing: A novel control concept [SANE PAPER 1326) 880-20656 to enhance departure/spin recovery VERY HIGH FREQUENCY RADIO EQUIPHENT characteristics of fighter and trainer aircraft The Omega radio navigation system --- Russian book 880-15 172 880-19413 VORTICITY 1et engine combustion noise - Pressure, entropy VIBRATION DANPING Damping capacity of plastic compressor blades and vorticity perturbations produced by unsteady 880-19868 combustion or heat addition On the use of vihration self-damping materials in 880-20 151 the manufacture of parts for rotating machinery 880-14 135 VIBRATION NEASUBENENT Gas turbine carcase and accessory vibration - WAKES Problems of measurement and analysis On the effect of wing wake on tail characteristics 880-1773 0 880-15 174 Digital system for dynamic turbine engine blade WALL FLOW displacement measurements A computer code to model swept wings in an [NASA-TN-81382] 880-14113 adaptive wall transonic wind tunnel 880-19287 VIBRATION TESTS IAIAA PAPER 80-0156] Excitation and analysis technique for flight connt3 generation in a flow near a compliant wall #80-20 153 flutter tests (EBB-1JF-1446(0) ] 880-14140 WARNING SYSTENS Plight testing of the buffeting behavior of combat Wire obstacle warning system /WOWS/ - A real-time aircraft airborne sensor for automatic detection and [ESA-TT-523] 880-14143 recognition of wirelike oblects A simplified ground vibration test FrocEdure for 880-17402 sailplanes and light aircraft Tactical analysis of conflicts in an air traffic 880-15146 control system: Design and implementation of a VIDEO EQUIPHENT provisional model OS Army Test and Evaluation Command test 880-14 072 operations procedures: Photographic and video WAVE DIFFRACTION image support aviation materiel Applications of diffraction theory to aeroacoustics [80-8074883] 880-14377 aircraft noise 880-14870 VISCOUS PLOW A numerical approach to subsonic viscous-inviscid NAVE FRONTS interaction Sonic-boom wave-front shapes and curvatures #80-19070 associated with maneuvering flight Numerical simulation of supersonic inlets using a rNASA-TP-1611) 880-14045 three-dimensional viscous flow analysis NAVE REFLECTION

[AIAR PAPER 80-03841 880-20969 Antireflection techniques for detecting false VISUAL YIELDS tracks in air traffic surveillance with Visual accommodation resçcnses in a virtual image secondary radar 880-14 100 environment 80-8074415] 880-15082 WEAPON SYSTENS VISUAL PERCEPTION The modular life cycle cost model - An overview Visual accommodation responses in a virtual image (SANE PAPER 1290] #80-20636 environment WEAPONS DELIVERY 180-80741415] 880-18082 A comparison of first and second order techniques VOICE CONNUNICATION for computing optimal horizontal gliding Vocabulary specification for automatic speech tralectories --- for low level weapons delivery recognition in aircraft cockpits [#188 PAPER 80-0061] 880-18260 (80-8073703] 880-14303 WEATHER VOLTAGE REGULATORS Accident investigation An overvoltage safety system for direct current 880-14 636 aircraft generators Effect of weather conditions on airport operations #80-1905 1 880-14638 VORTEX GENERATORS WEATHER FORECASTING Streamwise development of the flow over a delta wing Weather detection using airport surveillance radar #80-19 129 [8188 PAPER 80-0200] 880-18376 Some investigations concerning the effects of gaps Current research on aviation weather and vortex generators cm elevator efficiency and (bibliography) • 1979 of landing flap sweep on aerodynamic (NASA-CR-32141 880-14651 characteristics WEATHER RECONNAISSANCE AIRCRAFT 880-15178 The 1-28 thunder/hailstorm penetration aircraft VORTEX STREETS 880-14640 Hybrid vortex method for lifting surfaces with WEIGHT ANALYSIS free-vortex flow Analog aircraft weight and balance computer [AIAA PAPER 80-0070] A80-19307 [SANE PAPER 1283] 880-20631 VORTICES Preliminary weight estimation of engine section Development of a vortex-lift-design method and structure application to a slender maneuver-wing [SANE PAPER 1311] 880-20645 configuration Weight Integrated Sizing Evaluation /NISE/ - A [8188 PAPER 80-0327] 880-18316 tool for preliminary design [SAN! PAPER 1312] 880-206146

8-40

SUBJECT INDEX WINGS

A simple design synthesis method used to estimate WING FLAPS aircraft gross weight Flaperon control: The versatile surface for [SANE PAPER 13131 A80-20647 fighter aircraft Problems associated with cargo airplanes having P80-15 158 aft mounted engines WING FLOW NETBOD TESTS [SANE PAPER 13141 A80-20648 Experimental and computational study of transonic Weight impact of VTOL flow about swept wings [SAWE PAPER 1326] A80-20656 [AIAA PAPER 80-0005] 880-18235 WEIGHT REDUCTION The effects of leading edge modifications on the Application of PCS guidelines to weight effective post-stall characteristics of wings aircraft design --- Radar Cross Sectics !AIAA PAPER 80-0199] 880-18375 [SANE PAPER 1270) A80-2066 Streamwise development of the flow over a delta wing Advanced materials and the Canadair Challenger 8188 PAPER 80-0200] A80-18376 [SANE PAPER 1284] 880-20632 WING LOADING Advanced technology effects on V/STOL propulsive 11pplication of finite element analysis to system weight derivation of structural weight [sAwE PAPER 1300) 880-20640 tSAWE PAPER 1271) A80-20627 WIND TUNNEL NODELS WING NACELLE CONYIGUBATIONS Optimized aerodynamic design process for subsonic Quiet Clean Short-Paul Experimental Engine transport wing fitted with winglets --- wind (QCSEE). Under-the-wing (flTW) engine tunnel model boilerplate Nacelle test report. Volume 2: rnA.sA-CR-159180] P80-14054 Aerodynamics and performance Wind tunnel investigation of controls for OP on a tPASA-CR-135250) P80-14116 fighter-type configuration of higher angles of WING OSCILLATIONS attack Analysis of transonic flow about harmonically oscillating airfoils and wings WIND TUNNEL STABILITY TESTS rAIRA PAPER 80-0149] 880-18367 Experimental determination of pure rotary An investigation of several factors involved in a stability derivatives using curved and rolling finite difference procedure for analyzing the flow wind tunnel transonic flow about harmonically oscillating [AIAA PAPER 80-0309] A80-18308 airfoils and wings WIND TUNNEL TESTS [NASA-CR-159143] P80-14056 Effect of the relative area of the flow core on WING PANELS the performance of a hypersonic wind tunnel Application of finite element analysis to A80- 17673 derivation of structural weight Effects of non-planar strake-wing on the vortex [SANE PAPER 1271] 880-20627 lift characteristics cf a twin-let fighter Elements of the wing section theory and of the configuration wing theory [AIAA PAPER 80-0329) A80-18318 tNACA-191] N80-15040 Correlation of predicted longitudinal aerodynamic Loading tests of a wing structure for a hypersonic characteristics with full-scale wind tunnel data aircraft on the ATLIT airplane [NASA-TP-1596] P80-15068 [AIAA PAPER 80-0186] 880-18356 WING PLANYORNS Large scale model tests of a new techuoloqy V/STOL The effects of leading edge modifications on the concept post-stall characteristics of wings [AIAA PAPER 80-02331 A80-19303 rAlAR PAPER 80-0199) 880-18375 Flight and wind tunnel test results of the WING PROFILES mechanical let noise suppressor nozzle Theoretical study of aerodynamic characteristics [AIAA PAPER 80-0165) A80-20T71 of wings having vortex flow Two dimensional aerodynamic interference eftects [NASA-CR-159184] P80-14053 on oscillating airfoils with flaps in ventilated General potential thecry of arbitrary wing sections subsonic wind tunnels --- computational fluid PACA-4521 P80-15046 dynamics General theory of aerodynamic instability and the [NASA-CR-32101 P80-14047 mechanism of flutter Turbolet-exhaust-nozZle secondary-air f low pumping [MACA- 1196] R80-15047 as an exit control of an inlet-stability bypass WING SLOTS system for a Mach 2.5 axisymmetric Some investigations concerning the effects of gaps mixed-compression inlet --- Lewis 10- by 10-ft. and vortex generators on elevator efficiency and supersonic wind tunnel test of landing flap sweep on aerodynamic fRASA-TP-1532] 980-111124 characteristics NASA/Army XV-15 tilt rotor research aircraft P80-iS 178 wind-tunnel test program plan --- Ames 40-ft by WINGLETS 80-ft wind tunnel tests Optimized aerodynamic design process for subsonic [NASA-TN-78562] P80-15067 transport wing fitted with winglets --- wind Correlation of F-is flight and wind tunnel test tunnel model control effectiveness ( NASA-CR-159180] P80-14054 P80-15152 WINGS Some wind tunnel measurements of the effectiveness An inverse transonic wing design method at low speeds of combimed lift and roll controls [AIAA PAPER 80-0330] 880-18319 P80- 15153 Optimized aerodynamic design process for subsonic Fin design with ACT in the presence of strakes transport wing fitted with winglets --- wind P80-15161 tunnel model An experimental study of the structure and [NASA-CP-1591801 P80-14054 acoustic field of a jet in a cross stream Elements of the wing section theory and of the Ames 7-ft by 10-ft wind tunnel tests wing theory rNASA-CR-162464] N80-15871 [PACA-191] P80-15040 WINDOWS (APENTUBES) A parametric wing design study for a modern Design study for AlA vacuum system aperture laminar flow wing ['1CPL-150501 P80-15182 [PASA-TM-80154) R80-15050 Conceptual design and performance estimates for a JA-6A circulation control wing contractor flight supersonic aerodynamic window for the ATA vacuum demonstration system aperture [ AD-8074888] 1180-15080 [UCRL-15051) N80-15183 Aerodynamic interaction on a Close-coupled canard WING CANNER wing configuration Development of a vortex-lift-design method and P80-15 175 application to a slender maneuver-wing configuration (AIAA PAPER 80-0327] 880-18316

8-41 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING/A Continuing Bibliography (Suppl. 121) APRIL 1980 Typical___NALA Personal Author Index Listing ABUJA, ANDERSON, B. B. Studies of the acoustic transmission Numerical simulation of supersonic inlets using a characteristics of coaxial nozzles with inverted three-dimensional viscous flow analysis I velocity profiles, volume 1 (5188 PAPER 80-0384] 880-20969 I [NASA-CR-159698] 880-11870 Computation of three-dimensional flow in turbofan mixers and comparison with experimental data [NASA-T8-81410] 880-15364 NASA ANDERSON, J. 0., JR. LREPORI I I The effects of leading edge modifications on the NUMBER ACCESSIONNUMBER post-stall characteristics of wings (AlAS PAPER 80-0199] 580-18375 ANDERSON, .3. L. Application of parametric weight and cost Listings in this index are arranged alphabetically by personal author. The title estimating relationships to future transport of the document provides the user with a brief description of the subject matter. aircraft The report number helps to indicate the type of document cited (e.g., NASA (SAWE PAPER 1292) 880-20637 ANDRIOTANIS, G. report, translation, NASA contractor report). The accession namber is located Covariance simulation of SCAS - An aircraft beneath and to the right of the title. e.g. N80-t 1870. Under any one author's collision avoidance system name the accession numbers are arranged in sequence with the fAA accession #80-20915 numbers appearing first. ANSELL, G. S. Composite structural materials [ttASA-CR-162578] 880-15076 A ATACRE, B. B. AEZUG. B.. J. Optimization of turbine nozzle cooling by Hinged vehicle equations cf motion combining impingement and film injection [#158 PAPER 80-0364] 880-18336 (8188 PAPER 80°299] 580-19316 A?ANASEV, A. 10. AZUMA, A. Aircraft torque motors flotational noise of helicopter rotors 880-19199 880-17718 AGNEW. J. N. Correlation of P-iS flight and wind tunnel test control effectiveness B 880-15152 BADIAGIN, A. A. AHTYE, N. Y. Designing light airplanes Evaluation of approximate methods for the 880-19 414 prediction of noise shielding by airframe BAHR, D. N. components Quiet Clean Short-haul Experimental Engine [NASA-TP-1004] 880-15129 (QCSEE). Double-annular clean combustor AIELLO, B. technology development report CH-46 composite rotor blade flight stress survey [tlAsA-Cit-159483] N80-15121 data. Volume 3: Plotted forward rotor blade BALLARD, .3. 0. chord, torsion and absolute loads Effect of tip planform on blade loading [AD-A075612J 880-15077 characteristics for a two-bladed rotor in hover ALBAWES, N. V. (NASA-TN-78615] . N80-14049 Verification of digital autopilot microprocessor BARALE, G. hardware and software via hardware-in-the-loop A distributed processing system for radar data simulation presentation 880- 20 90 1 88 0-14075 ALEXANDER, C. A. BARGER, B. L. Comparative resistance of Beta-Si3N4 solid Sonic-boom wave-front shapes and curvatures solutions to molten silicon attack associated with maneuvering 'flight 580-18 062 [NASA-TP-1611] ' 880-14045 ALEXANDER, .1. G. BARLOW, J. B. Protective coatings for aircraft composites in Determination of the spin and recovery nuclear environments characteristics of a typical low-wing general [80-8074889] 880-14199 aviation design ALLEN, 0. [5188 PAPER 80-0169] 880-18351 Avionics installation (AVSTALL) cost model for The effects of leading edge modifications on the user equipment of NAVSTAR global positioning post-stall characteristics of wings system [5188 PAPER 80-0199] 580-18375 [AD-. A073681) 880-14106 BARNES, C. S. ALLEN, J. B. Some wind tunnel measurements of the effectiveness An improved sensing element for skin-friction at low speeds of combined lift and roll controls balance measurements 880-15153 [8158 PAPER 80-0049] 880-18251 BARRANGEB, j_ P. ALPERIN, B. Laser-optical blade tip clearance measurement system Recent development of a jet-diffuser ejector (NASA-TN-81376] . 880-14128 [#158 PAPER 80-0231] 880-18277 BASTIANINI, 0. ANDEBLE, B. J. Simulation of a surveillance and control system of The Global Positioning System surface traffic in an airport #80- 20 99 2 880-14 073

B-i BAYLISS, A. PERSONAL AUTHOR INDEX

BAYLISS, A. BORRINI, P. Experimental and numerical results of sound Trajectory behaviour of a control configurated scattering by a body aircraft subjected to random disturbances H80-14 873 1480-15 171 BEACREB, B. P. BOSLET, 3. V. Quiet Clean Short-haul Experimental Engine Verification of digital autopilot microprocessor (QCSEE). Aerodynamic and aeromechanical hardware and software via hardware-in-the-loop performance of a 50.8 cm (20 inch) diameter 1.34 simulation PR variable pitch fan with core flow 680-20901 [NASA-CR-135017] H80-15087 BOUDIGUES, S. BEAUSSIER, .1. Technologies conceived for the utilization of Investigations of the optimal configuration of ceramics in turboengines high-stability quartz oscillators for aircraft [ONERA, TP NO. 1979-132] A80-20076 and missiles BOWDEN, 3. H. A80- 19990 Quiet Clean Short-haul Experimental Engine BEECKEN, G. (QCSEE). Composite fan frame subsystem test An analytical method of testing pavement strength report A80-17 998 [NASA-CR-135010] 1480-15098 BEN, B. BOIWELL, U. A. Stability and control aspects of the CCV-F1OIIG Acoustically swept rotor fNBB-UPP-11447(0) ] N80-1141141 [NASA-CASE-ARC-il 106-1] 1480-14107 BELTRANO, N. N. BOYD, H. V. Application of parametric weight and cost 36-66 circulation control wing contractor flight estimating relationships to future transport demonstration aircraft [AD-m074888] 4480-15080 [SAVE PAPER 1292] A80-20637 BBADBN, 3. A. BENDO, 3. Exploratory studies of the cruise performance of CH-46 composite rotor blade flight stress survey upper surface blown configuration: Experimental data. Volume 3: Plotted forward rotor blade program, high-speed force tests chord, torsion and absolute loads [NASA-CE-159134] 1480-15070 [AD-A075612] N80-15077 Exploratory studies of the cruise performance of BENI, P. upper surface blown configurations: An air traffic channel simulation by means of Experimental program, high-speed pressure tests ray-tracing techniques [14#SA-CE-159135] 1480-15071 N80-14 088 Exploratory studies of the cruise performance of BERGNANN, N. Y. upper surface blown configurations: Program Experimental and computational study of transonic analysis and conclusions flow about swept wings [NASA-CR-159136] 1480-15072 [6166 PAPER 80-0005] A80-18235 BRANSFORD, 3. V. BEBTELBUD, A. LOX/GO! mechanical impact tester assessment Experimental and computational study of transonic tNASA-TN-74106] 1480-15179 flow about swept wings BRATANOW, T. [AIAA PAPER 80-0005] A80-18235 Unsteady flow and dynamic response analyses for BERTINI, F. helicopter rotor blades An air traffic channel simulation by means of [N#SA-CR-159190] 4480-14355 ray-tracing techniques BRAZIER, B. B. 3. N80-1'4 088 The minimum cost approach to flutter clearance BEETOLAZZI, P. 1480-15 148 Tactical analysis of conflicts in an air traffic BREWER, G. 0. control system: Design and implementation of a Hypersonic cruise aircraft propulsion integration provisional model study, volume 1 N80-1'I 072 [NASA-CR-158926-VOL-1] 1480-150711 BETINI, S. Hypersonic cruise aircraft propulsion integration Development trends of airport surface traffic study, volume 2 control radar NASA-CR-i 58926-VOL-2] 1480-15075 N80-1'4 087 BROCAND, T. BEZNENOT, V. IA. Aerodynamic interaction on a close-coupled canard Effect of the relative area of the flow core on wing configuration the performance of a hypersonic wind tunnel 1480-15 175 680-17 673 BROOKS, .3. m. BIANCO, L. Flight and wind tunnel test results of the Automation of flight on-line strategic control: mechanical jet noise suppressor nozzle The case of speed control on pre-established [AIAA PAPER 80-0165] 680-20971 routes BROUSSARD, 3. B. N80-14 070 A nonlinear observer/command generator tracker Radar data utilization in automating the approach to the IN-97 helicopter gun turret sequencing of aircrafts in terminal areas control law design 880-14071 680- 20 879 BLUNENTHAL, A. P. BROWN, H. Nap-matching techniques for terminal guidance Nulti-variable cycle optimization by gradient using Fourier phase information methods 680-17517 [14186 PAPEP 80-0052] 880-18254 BLUMENTHAL, 0. BROWN, P. V. Pressure distribution on Joukowski wings Simulator study of stall/post-stall (NACA-TN-336] 1480-15036 characteristics of a fighter airplane with BOBER, L. A. relaxed longitudinal static stability Summary of advanced methods for predicting high [NASA-TP-1538] 4480-14136 speed propeller performance BRUNSTEIN, A. I. [NASA-TN-81409) 1480-15051 Accident investigation BOBEB, L. 3. 1480-14636 Summary of advanced methods for predicting high BRYAN, C. 3. speed propeller performance LOX/GO! mechanical impact tester assessment [AIAA PAPER 80-0225] 680-20966 [NASA-TN-74106] 1480-15179 BOLDT, T. U. BURCHAM, P. V., JR. Analog aircraft weight and balance computer Landing approach airframe noise measurements and rSAW PAPER 12833 680-20631 analysis [NASA-TP-1602] 1480-15028

B-2 PERSONAL AUTHOR INDEX COWARD, V. B.

BUEDGBS, K. P. dEll, R. V. V. Exploratory studies of the cruise performance of Effects of primary rotor parameters on flapping upper surface blown configuration: Experimental dynamics program, high-speed force tests [NASA-TP-14431) 880-15138 (NASA-CR-159134] 880-15070 CRENG, H. Y. K. Exploratory studies of the cruise performance of Soil analyses and evaluations at the impact upper surface blown configurations: dynamics research facility for two full-scale Experimental program, high-speed pressure tests aircraft crash tests (NASA-CR-159135] 880-15071 (NASA-Cfi-159199] 880-15299 BORHANS, 8. V. CHISU!, C. T. Experimental loop antennas for 60 Eilz to 200 EHz visual accommodation responses in a virtual image [NASA-CR-162729] 880-15063 environment BURROS, D. 1. [#0-80741415) 880-15082 Quiet Clean Short-haul Experimental Engine CEO, 1.-C. (QCSEE). Double-annular clean combustor Hybrid vortex method for lifting surfaces with technology development report free-vortex flow (NASA-CI4-159483] 880-15121 AIAA PAPER 80-0070] 880- 19307 BUSSAC, H. N. CHO, 1.-!. Low-aspect-ratio limit of the toroidal reactor - Adaptive allocation of decisionmaking The spheromak responsibility between human and computer in #80-17 876 multitask situations BUXBAUH, 0. 880-18022 Review of investigations into aeronautics related dIN!, H. fatigue Yederal Republic of Germany Automation of flight on-line strategic control: [LBP-S-142] 880-141422 The case of speed control on pre-established RYAN, T. B. - routes Analyses and tests of the E-1 aircraft structural 880- 14 070 node control system CLARK, 8. B. [NASA-CR-1448871 880-15073 Regression technigues applied to parametric BYKOY, V. I. turbine engine simulations The Omega radio navigation system [#188 PAPER 80-0053] 880-18255 #80-191113 CIBROIS, A. Acoustic analysis of aft noise reduction techniques measured on a subsonic tip speed 50.8 C cm (twenty inch) diameter fan CALLAVAY, A. A. (RA5A-cfi-1314891) 880-15102 Trends in digital data processing and system Quiet Clean Short-Haul Experimental Engine architecture (QCSEE): Acoustic treatment development and 880-18020 design CANELIEB, I. rNASA-CR-135266] 880-15122 An experimental study of the structure and CROSSEN, B. acoustic field of a jet in a cross stream Gesign study of a low cost civil aviation GPS (NASA-CE-16246 l41 880-15871 receiver system CANNON, 0. C. (NASA-cR-159176] 880-15062 Preliminary test results of a flight management COAKLEY, V. 3. algorithm for fuel conservative descents in a Experimental and computational study of transonic time based metered traffic environment flow about swept wings [RASA-TN-80194] 880-14114 [AIAA PAPER 80-0005] #80-18235 CAPPADONA, B. COLLINSON, N. P. 0. L-band measurements in the air traffic channel to Recent advances in fibre optics for high integrity characterize secondary radar systems digital control systems 880-14092 880-14025 CARL!, B. coLoN y , 3. 8. Automatic systems for airport surface mobile media Reteorological input to general aviation pilot surveillance based on the use of secondary media training 880-14104 880-14634 C#RLSON, H. V. COLTRIN, V. B. Studies of leading-edge thrust phenomena An analytical and experimental study of a short [AIH PAPER 80-0325] 880-18315 S-shaped subsonic diffuser of a supersonic inlet CASTEILAN!, V. [8188 PAPER 80-0386] 880-20970 Onboard collision avoidance system: Environmental An analytical and experimental study of a short influence on the tracking algorithm requirements s-shaped subsonic diffuser of a supersonic inlet 880-14105 [NASA-TN-81406] 880-151314 CATALANO, C. U. COOPER, 1. P. Photon correlation laser veloc j meter measurements Effect of degree of fuel vaporization upon in highly turbulent flow fields emissions for a premixed partially vaporized (8188 PAPER 80-0344] #80-18328 combustion system CERROLO, A. (NASA-TP-1582] 880-114125 Photon correlation laser velocimeter measurements COPLIN, .3. P. in. highly turbulent flow fields Technology of the Rolls-Royce P8211 engine AIAA PAPER 80-0344] #80-18328 #80-188644 CHALK, C. B. COEZARI, V. Comment on 'Handling quality criterion for heading Automatic systems for airport surface mobile media con trol• surveillance based on the use of secondary media 880-17698 1480-14 104 CHANBEBLIN, 8. COTTER, L. B. Scale model performance test investigation of A strapdown inertial reference system for exhaust system mixers for an Energy Efficient commercial airline use in navigation and flight Engine /E3/ propulsion system control AIAA PAPER 80-02293 #80-20968 #80-17 558 CHAHBLEB C. N. COWARD, V. N. Application of the multistage axial-flow Quiet, Clean, Short-Haul, Experimental Engine compressor time-dependent mathematical modeling (QCSPE) Under-The-Wing (TJTW) engine acoustic technique to the TPU1-A-1 mo1ified block 76 design compressor tRASA-cR-135267) 880-114117 (#0-80744478] 880-141344 Quiet, Clean, Short-Haul Experimental Engine (QCSEE) Over-The-Wing (0114) engine acoustic design tNASA-CR-135268] 880-114118

B-3

CHITTEEDEN, 3. B. PERSONAL AUTHOR INDEX

Quiet Clean Short-haul Experimental Engine DIGHTOR, B. D. (QCSEE) . Core engine noise measurements Designing to life cycle cost in the Hornet program (NASA-CR-135160J N80-15093 (SANE PAPER 1293] A80-20638 CRITTENDER, .3. B. DONOGHUE, P. 3. Shipping by air - Is the value of your time worth it A strapdown inertial reference svstem.for A80-20868 commercial airline use in navigation and flight CUNPSTY, N. 6. control Jet engine combustion noise - Pressure, entropy A80- 17558 and vorticity perturbations produced by unsteady An integrated strapdovn guidance and control combustion or heat addition system for launch vehicle application 680-20151 680-17559 CYRUS, .3. DREYFUS, B. U. A pre-design code for predicting engine Ron-contacting electro-optical contouring of acquisition costs helicopter rotor blades [AIAA PAPER 80-0055] 680-19269 (AD-A070806] 0480-14111 CYRUS, 3. U. DUTOUQUET, L. Fuel conservation benefits and critical Engine aerodynamic installation by numerical technologies of recuperative and advanced simulation conventional cycle turboshaft engines [AIAA PAPER 80-0108] 680-18271 [6166 PAPER 80-02211] A80-19301 E EASTHAN, B. B. DAHL, H. Air cargo container utilization optimization Investigation of the oscillatory and flight through modeling behavior of rotor systems in relation with 680-20 870 atmospheric turbulence ECHIN, A. I. [B1VG-FEWT-79-5] 880-141112 Unification of oils for aircraft gas-turbine engines DANESI, A. 680-20 690 Trajectory behaviout àf a control configurated EHEKIRCHER, S. aircraft subjected to random disturbances wind tunnel measurements and analysis of some 0480-15 171 unusual control surfaces on two swept wing DANIEL, B. B. fighter configurations Acoustic radiation from axisymmetric ducts - A 0480-15 155 comparison of theory and experiment EBLENS, P. E. [AIAA PAPER 80-0097] #80-18268 Analysis of transonic flow about harmonically DAROLIA, H. oscillating airfoils and wings Feasibility of SiC composite structures for 16144 f [AIAA PAPER 80-0149] 680-18367 (2500 F) gas turbine seal application An investigation of several factors involved in a [NASA-CR-159597] 880-1(4122 finite difference procedure for analyzing the DAT, B. transonic flow about harmonically oscillating A phenomenological model of the dynamic stall of a airfoils and wings helicopter blade profile INASA-CP-159143] 0480-14056 [08886. TP NO. 1979-1 (491 '480-20086 A users guide for A3 144: A program using a finite DAVIES, 0. L. difference method to analyze transonic flow over Discontinuous registration of industrial oscillating airfoils radiographs using profile analysis and piecewise [NASA-C8-1591411 N80-15052 correlation techniques EWDERS, 3. 8. 680-17521 NASA technical advances in aircraft occupant safety DEAL, P. L. tNASA-I'M-808511 0480-15060 Simulator study of stall/post-Stall ENGLIN, B. A. characteristics of a fighter airplane with Pffect of naphthenic aromatic hydrocarbo'cs on the relaxed longitudinal static stability oxidizability of hydrogenated jet fuel fNASA-TP-15381 880-18136 680-17 675 DEFEO, A. ENDOS, 3. I. Ouiet Clean Short-haul Sxperimental Engine (OCNPP) Conce p tual design and performance estimates for a main reduction gears detailed design report supersonic aerodynamic window for the ATA vacuum r s AsA-Cp -13487 2] 880-15106 system aperture DEFINA, C. r'1CNL-1501] 880-15183 Development trends of airport surface traffic ERICKSON, U. E. control radar Fffects of non-planar strake-wing on the vortex 880-16 087 lift characteristics of a twin-jet fiqhter DEL, N. con figuration T!acking algorithms for mono and inultiradar AIAA PAPER 80-0329] 680-18318 880-1 8074 ETOZBENGER, H. DELERY, 3. Constrained optimum trajectories with specified Separation due to shocjc wave-turbulent boundary range layer interaction 680-18538 r OWEFA, "P 80. 1979-186] 680-20083 ESCH, P. DERHAGOPIAN, 3. Direct side force and drag control with the aid of On the use of vibration self-damping naterials in pylon split flaps the manufacture of parts for rotating machinery 880-15 163 880-14135 ESSOCK, D. N. DESOPPER, A. SEN composites for advanced gas turbine engine Onsteady effects of a control surface tn two components dimensional, subsonic and transonic flow [60-6074287] 880-15137 880-15168 OESTUYRDER, 8. Problems of unsteady aerodynamics raised by ti's F use of control surfaces as active controls PALCIASECCA, C. 8O- 15167 Automatic systems for airport surface mobile media DETHORAS, A. P surveillance based on the use of secondary media A flight control, system using the DAI S architecture 880-14 108 880-18019 FAN, A. ?. DETORE, 3. Design criteria for optimal flight control systems Tilt rotor - An effective V/STOL conceut 1 #0-00740921 880-15139 [SAWE PAPER 12731 #80-20628

8-4

PEBSORAL AUTHOR INDEX GILBERT, V. P.

FARINA, A. FREENAN, L. N. A survey of the stochastic filtering techniques Application of a higher order panel method to for data processing in air-traffic control and realistic supersonic configurations surveillance systems rAIRA PAPER 79-0274] 680-17696 A90-20867 PRIEDNANE, P. FASCHING, W. A. y ormulation of coupled rotor/fuselage equations of The C'6 let engine performance improvement: New motion front mount 680-17717 [NASA-CR-159639] 880-14127 PRONNE, 3. PEAR, 3. S. Two dimensional aerodynamic interference effects NASA broad-specification fuels combustion on oscillating airfoils with flaps in ventilated technology program: Status and description subsonic wind tunnels (NASA-TM-79315] 880-14126 [NASA-CR-32101 580-14047 FElLER, C. B. FROST, N. Preparing aircraft propulsion for a new era in Current research on aviation weather energy and the environment (bibliography) , 1979 A80-1 7737 ('IASA-CR-32141 880-14651 PERDANI, P. FRYE, G. N. Automatic systems for airport surface mobile media LOX/GOX mechanical impact tester assessment surveillance based on the use of secondary media NASA-TH-74 106] 880-15179 880-14104 FUCHS, H. V. FEBRI, U. Aeroaconstic measuring techniques in or outside Simulation of a surveillance and control system of turbulent flows surface traffic in an airport 880- 14 87 6 580-14073 FUJI!, K. FIELDS, N. A. A numerical approach to subsonic viscous-inviscid Loading tests of a wing structure for a hypersonic interaction aircraft 680-19070 rNAsA-T p-1596] 18O-15068 FORTH, H. P. FINGER, U. C. Low-aspect-ratio limit of the toroidal reactor - Contact stress analysis of ceramic-to-metal The spheromak interfaces - 680-17876 IAD-60744911 840-14417 FISCHER, j• P. Data reduction software for LORAN-C flight test G evaluation GALEBY, SB. S. rNASA-CR-162730' 880-15064 Aircraft torque motors FISBBACH, L. H. A.0-19 199 Computer simulation of engine systems GARRICK, I. E. (AIAA PAPER 80-0051] 680-18253 General potential theory of arbitrary wing sections PISHRACK, I. H. - [NAcA-4521 880-15046 Computer simulation of engine systems GAULT, 0. E. rNASA-TN-79290] 580-15132 Atmospheric effects on Martian ejecta emplacement PITZSIHHONS, B. 0. A80-20 192 p light and wind tunnel test results of the GELLER, E. V. mechanical jet noise suppressor nozzle A computer code to model swept wings in an fAIAA PAPER 80-0165] A80-20911 adaptive wall transonic wind tunnel FLAIG, 3. N. tAIAA PAPER 80-0156] A80-19287 Small ship-based VTOL aircraft - A design exercise GERNAIN, G. [SANE PAPRE 1296] 680-20639 The integrity of onboard computer programs: A FLETCHER, B. G. solution Development of aiding GPS/strapdown inertial 880-14028 navigation system GEROS, .3. N. 880-14031 Performance evaluation of image correlation FORD, N. 3. techniques Laser-optical blade tip clearance measurement system 680-17534 fNASA-TN-81376] 580-14128 GERSCH, A. FORD, B. L. Weight Integrated Sizing Evaluation /WISE/ - A ATC and the airborne traffic-situation display tool for preliminary design A80-1P 724 [SANE PAPER 1312] 680-20646 FORNANIAK, 3. GERSON, G. Investigation of the wear debris content in oil by Guidance system position update by multiple measurements of the reluctance and eddy current subarea correlation loss in an electric Circuit A80-17518 A80-19 053 GERSTEN, K. FORSBAW, S. E. On the effect of wing wake on tail characteristics Investigation of noise hazards in the engine test 880-15174 cell, CFB Baden-Soellingen GERSTERHAIBR, V. tAD-A074391] 880-14147 Computation of three-dimensional flow in turbofan PRARTZ, B. L. mixers and comparison with experimental data Centralized ground power systems conserve energy [NASA-TM-81410] N80-1536'i 680-18 000 GIPPIP, B. C. PRASCHETTI, G. Quiet Clean Short-haul Experimental Engine Performance evaluation methods of a secondary - (QCSEE) . Aerodynamic and aeromechanical radar network performance of a 50.8 cm (20 inch) diameter 1.34 880-14 068 PR variable pitch fan with core flow Antireflection techniques for detecting false [NASA-CR-135017] 880-15087 tracks in air traffic surveillance with GILBERT, C. secondary radar Design study of a low cost civil aviation GPS 880-14 100 receiver system FRATACCI, G. [NASA-CR-159176] 880-15062 Technologies conceived for the utilization of GILBERT, N. P. ceramics in turboengines Simulator study of stall/post-stall [ONFRA, p 80. 1979-132] 680-20076 characteristics of a fighter airplane with PREENAN, D. S. relaxed longitudinal static stability Quiet Clean Short-haul Experimental Engine (QCSFE) [NASA-TP-15381 880-14136 tinder-The-N ing (UTW) composite nacelle subsystem Control considerations for CCV fighters at high test report angles of attack fNASA-Cit-135075] 580-15100 88 0-15160

B-S GILMORE, J. P. PERSONAL AUTHOR INDEX

GILNORE, .1. P. GRISWOLD, 44. Nodular strapdown guidance unit with embedded Correlation of predicted longitudinal aerodynamic microprocessors characteristics with full-scale wind tunnel data [AIAA PAPER 78-1239] #80-18534 on the ATLIT airplane GIRT!, D. P. (AIAA PAPER 80-0186) A80-18356 Effect of weather conditions on airport operations GROBMAN, 3. S. 980-14638 Preparing aircraft propulsion for a new era in GIULI, D. energy and the environment Antireflection techniques for detecting false A80-17737 tracks in air traffic surveillance with GRODZOVS!II, G. L. secondary radar Concerning the information efficiency of 980- i fI 100 aerodynamic experiments GIUSNGENS, G. S. A80-17671 Aircraft aerodynamics - Dynamics of longitudinal GROESBECK, D. and lateral motion Assessment at full scale of exhaust nozzle-to-wing #80-19379 size on STOL-OTW acoustic characteristics GLISTA, A. S., JR. #80-20 952 Integrated circuit characteristics at 260 C for GROSVELD, P. aircraft engine-control applications Structural parameters that influence the noise #80-20 112 reduction characteristics of typical general GLUECK, D. aviation materials On the effect of wing wake on tail characteristics [AIAA PAPER 80-0038) 980-18248 980-15179 GRUBE, K. GOLBEEG, M. Practical method of fatigue crack growth analysis Two dimensional aerodynamic interference effects for damage tolerance assessment of aluminum on oscillating airfoils with flaps in ventilated structure in fighter type aircraft subsonic wind tunnels (AIAA PAPER 80-0405) A80-18346 [N#SA-CR-32101 980-14047 GULLY, S. N. GOLLOP, P. 3. A nonlinear observer/command generator tracker A high accuracy flight profile determining system approach to the XM-97 helicopter gun turret 980-19042 control law design GOOD, U. E. #80-20879 Model 540 rotor blade crack propagation GUROY, S. V. investigation Thermal state of structural members of aircraft tAD-A074739] 980-15081 engines GOODBL000, G. E. #80- 19412 Comparison of international flutter requirements and flutter freedom substantiation of light . aircraft in the USA P80-151142 HACKETT, 3. H. 000DSON, N. Exploratory studies of the cruise performance of What brings us down tomorrow - Landing guidance upper surface blown configuration: Experimental systems for the 1980s program, high-speed force tests 980-18725 fNASA-CR-159134] 980-15070 GOODWIN, 3. Exploratory studies of the cruise performance of Automation and air traffic control upper surface blown configurations: 980-18722 Experimental program, high-speed pressure tests GOTO, N. (NASA-CR-159135] 980-15071 A statistical method applied to pilot behavior Pxploratory studies of the cruise performance of analysis in inultiloop systems upper surface blown configurations: Program #80- 18537 analysis and conclusions GOVINDARA, K. S. (SAPA-CR-159136) 980-15072 Design criteria for optimal flight control systems HAGEDOORN, A. H. [AD-A074092] 980-15139 Shipping by air - Is the value of your time worth it GRAD!, P. 3. 980-20868 Protective coatings for aircraft composites in HAGUE, D. S. nuclear environments Nultiple tactical aircraft combat performance r#D-A074889) 980-19199 evaluation system GRAPTON, S. B. [AIAA PAPER 80-0189) A80-16358 Control considerations for CCV fighters at high HAIDL, G. angles of attack Excitation and analysis technique for flight 4480-15 160 flutter tests GRAHAM, N. N. [NRR-DP-1446(0) ] 4480-14140 Impact of new instrumentation on advanced turbine HALSEY, N. D. research Conformal mapping analysis of multielement NASA-TN-79301] 980-15133 airfoils with boundary-layer corrections GNARl, A. (AIAA PAPER 80-0069] #80-18261 Organization of an integrated global maintenance HA!ED, A. service Optimization of turbine nozzle cooling by 980-14069 combining impingement and film injection GREEK, D. C. rAIAA PAPER 80-0299] #80-19316 Analyses and tests of the 8-1 aircraft structural HANCOCK, 0. 3. mode control system Unsteady aerodynamics of two-dimensional spoilers (NASA-C8-149887] 980-15073 at low speeds GRERON, B. 980-15 170 Unsteady effects of a control surface in two On the effects of gaps on control surface dimensional, subsonic and transonic flow characteristics 980-15168 980-15 176 GRIPPO, L. HANCOCK, 3. P. Automation of flight on-line strategic control: Exploratory studies of the cruise performance of The case of speed control on pre-established upper surface blown configuration: Experimental routes program, high-speed force tests 980-14 070 (I4ASA-CR-15913 i4] 980-15070 GRISHIN, V. I. Exploratory studies of the cruise performance of Determination of the stress intensity factor of upper surface blown configurations: composite structural members Experimental program, high-speed pressure tests #80- 17958 [NASA-CR-159135] 980-15071

B-6 PERSONAL AUTHOR INDEX JOHNSON, F. T.

Exploratory studies of the cruise performance of HOWARD, D. P. upper surface blown configurations: Program Quiet Clean Short-haul Experimental Engine (QCSEE) analysis and conclusions preliminary under the wing flight propulsion FNASA-CR-159136] N80-15072 system analysis report HANKE, D. (NASA-CR-134868] 1180-15088 In-flight measured characteristics of combined Quiet Clean Short-haul Experimental Engine (QCSEE) flap-spoiler direct lift controls preliminary over-the-wing flight propulsion N80- 15165 system analysis report HARDY, J. N. [NASA-CR-135296] 1180-15095 Engine aerodynamic installation by numerical HOWARD, 6. B., JR. simulation A light aircraft camera Pod - The Enviro-Pod [lIlA PAPER 80-0108] 880-18271 A80-20251 HABGBOVE, A. HOWLETT, J. T. Computer simulation of an air cargo small package A study of partial coherence for identifying sorting system interior noise sources and paths on general 880-20866 aviation aircraft RABBlE, N. H. [NASA-TM-80197] 880-15874 Air traffic density and distribution measurements HUBBARTT, 3. 8. (AD-A073229] 880-14064 Each 3 hydrogen external/base burning HAYES, U. D. (AIRA PAPER 80-0280] 880-19311 Weather detection using airport surveillance radar RUBEN, P. K. 890-19 129 'ntegration of flight and fire control HEIDELBERG, A. 7. P80-140113 Comparison of inlet suppressor data with BURT. 3. approximate theory based on cutoff ratio Wire obstacle warning system /WOWS/ - A real-time [AIAA PAPER 80-0100] 880-209611 airborne sensor for automatic detection and HEIDERGOTT, K. A. recognition of wirelike objects Linear systems analysis program, 1224(QP). Volume 880-171102 1: Engineering and usage HUNTER, H. P. [NASA-CE-2861] 580-14137 Comparison of international flutter requirements HELLER, H. A. and flutter freedom substantiation of light Fatigue life prediction of a bonded splice joint aircraft in the USA 8188 PAPER 80-0305] 880-18306 P80-15 142 BENDRIX, B. A. HUNTER, N. P. A flight control system using the DAIS architecture A computerized method for calculating flutter N 80- 111019 characteristics of a system characterized by two BEEBE, P. 8. degrees of freedom An inverse transonic wing design method rNASA-TN-80153] 580-14055 (AIRA PAPER 80-0330] 180-18319 HUTTON, 3. 6. RIBBS, S. Application of finite element analysis to Design study for ATA vacuum system aperture derivation of structural weight [UCRL-150501 880-15182 [SANE PAPER 1271] 880-20627 HIGHAN, K. N. A simple design synthesis method used to estimate aircraft gross weight [SANE PAPER 1313] 880-206117 IAPOLLA, B. BISLOP. A. iltering of synthetic-madar data The economics of air traffic control 1180-14076 880- 18 72 3 ILIYP, K. V. HOLDEBAN, 7. D. Estimation of the accuracy of dynamic Simultaneous cabin and ambient ozone measurements flight-determined coefficients on two Boeing 747 airplanes, volume 1 (RIAR PAPER 80-0171] 880-17700 [NASA-TN-79166] 880-15059 IRISH, L. A. HOLLAND, N. Application of ECS guidelines to weight effective Code optimization for solving large 3D EMP problems aircraft design 880-197611 [SAWN PAPER 12701 880-20626 HOLNE, A. B. B. Gas turbine carcase and accessory vibration - Problems of measurement and analysis J AQO-17730 JACOBSON, N. 3. HONNEIDA, A. Sonic fatigue design data for bonded aluminum On the use of vibration self-damping materials in aircraft structures the manufacture of parts for rotating machinery rATAA PAPER 80-0303] A80-18304 R80-14 135 JANESOB, A. HONYAK, L. A computer code to sodel swept wings in an Static test-stand performance of the YF-102 adaptive wall transonic wind tunnel turbofan engine with several exhaust [AIAA PAPER 80-01561 A80-19287 configurations for the Quiet Short-Paul Research JANUSTEWSKI, V. Aircraft (QS?A) An overvoltage safety system for direct current [NASA-TP-15561 880-14121 aircraft generators ROOKWAY, N. 0. A80-19051 Propulsion options for the HI SPOT long endurance JOHANNES, B. P. drone airship AFPDL experience in active control technology tAD-A074595] NR0-14132 1180-15 159 lOOPER. N. H. JOHN, H. The state-of-the-art of flutter substantiation High angle of attack characteristics of different procedures among US general aviation manufacturers fighter configurations 880-15143 [ HBB-UPE-1443(o) 1 1180-114058 HOESTHAWN, K. H. JOHNSON, N. S. Roll control by digitally controlled segment Flight and wind tunnel test results of the spoilers mechanical jet noise suppressor nozzle 880-15156 (lIlA PAPER 80-0165] 880-20911 BOUBOLT. J. C. JOHNSON, F. ?. Effect of spanwise gust variations Application of a higher order panel method to N80-111639 realistic supersonic configurations [AIAA PAPER 79-0274] 880-17696

B-7 JOHWSON, H. L. PERSONAL AUTHOR INDEX

JOHNSON, H. I. KIESSLING, P. A computer code to model swept wings in an An empirical approach for checking flutter adaptive wall transonic wind tunnel stability of gliders and light aircraft IAIAA PAPER 80-0156) 880-19287 1180- 15 148 JOHNSON, B. H. KIRALT, I. 3. Development of aiding GPS/strapdown inertial Digital system for dynamic turbine engine blade navigation system displacement measurements 1180-18031 [NASA-TN-81382] 1180-19113 JOHNSON, T. 0., JR. KIRIANOVA, A. A. Investigation of leading-edge devices for drag Effect of naphthenic aromatic hydrocarbons on the reduction of a 60-deg. delta wing at high angles oxidizability of hydrogenated jet fuel of attack #80-17675 [8188 PAPER 80-0310] 880-18309 KIRK, C. N. JOHNSTON, D. 11. An integrated strapdown guidance and control Effects of the aerodynamic cross-coupling and system for launch vehicle application lateral acceleration derivatives on airplane 880-17559 dynamic characteristics KITTIEGEB, D. C. (8188 PAPER 80-0170] 880-17699 Aeronautical systems technology needs: Escape, JOHNSTON, 11. A. rescue and survival Quiet Clean Short-haul Experimental Engine (QCSEE) (80-8078906] 1180-14061 Under-The-Wing (UTW) composite nacelle subsystem KLEBHA!NER, B. test report Wire obstacle warning system /WOWS/ - A real-time [NASA-CR-135075] 1180-15100 airborne sensor for automatic detection and Quiet Clean Short-haul Experimental Engine (QCSEE) recognition of wirelike objects Tinder-The-Wing (UTW) composite nacelle #80-17402 [N8SA-C11-135352] 1180-15119 KLNIDBR, A. JONAS, K. Wire obstacle warning system /WOWS/ - A real-time Roll control by digitally controlled segment airborne sensor for automatic detection and spoilers recognition of wirelike objects 1180-15156 880- 17 402 JONES, 0. KLOPPER, G. H. On the use of vibration self-damping materials in Euler solutions for wing and wing-body combination the manufacture of parts for rotating machinery at supersonic speeds with leading-edge separation 1180-18135 (#188 PAPER 80-0126] 880-18359 JONES, K. KNIGHT, 0. 0. The effects of leading edge modifications on the Improved numerical simulation of high speed inlets post-stall characteristics of wings using the Navier-Stokes equations (8188 PAPER 80-0199] 880-18375 [8188 PAPER 80-0383] 880-18340 JONES, H. B. KNOX, C. 11. Computer program to prepare airfoil characteristic Preliminary test results of a flight management data for use in heliccpter performance algorithm for fuel conservative descents in a calculations time based metered traffic environment NASA-TN-78627] 1180-1503 1 [NASA-TIl-80194] N80-14114 FOEGLER, 3. A., JR. A parametric wing design study for a modern K laminar flow wing KALEHARIS, S. [NASA-T11-8015 14] 1180-15050 Weight impact of VIOL KOENIG, D. G. (SANE PAPER 1326] 880-20656 large scale model tests of a new technology V/STOL KANDIL, 0. A. concept Hybrid vortex method for lifting surfaces with [81811 PAPER 80-0233] 880-19303 free-vortex flow KOENIG, K. [8188 PAPER 80-0070] 880- 19307 The loads at landing impact KARANCHETI, K. 880-17723 An experimental study of the structure and KOERNEB, H. acoustic field of a jet in a cross stream Theoretical aerodynamic methods for active control (1IASA-C8-162864] 1180-15871 devices KARASHINA, K. 1180-15 150 A numerical approach to subsonic viscous-inviscid KOOLE, 11. C. interaction An analytical method of testing pavement strength 880-19070 880-17998 KASCAK, A. P. KOPBLEV, S. K. Direct integration of transient rotor dynamics Thermal state of structural members of aircraft INASA-T p-1597] 1180-15128 engines KEATING, 8. P. 1. 880- 19 1412 Some wind tunnel measurements of the effectiveness FORTE, U. at low speeds of combined lift and roll controls Stability and control aspects of the CCV-F1O4G 1180-15153 [MBE-flFE-1447(o) 1180-1141141 KEHRER, N. T. KUBBAT, N. 3. Flight control and configuration design Failure detection, isolation and indication in considerations for highly maneuverable aircraft highly integrated digital guidance and control 1180-15154 system KENT, 3. S. 1180-14 027 An evaluation of t1e bird/aircraft strike hazard K0CRAN, j• P. at Barksdale Air Force Base, Louisiana (SAC) Scale model performance test investigation of rAD-8074390] 1180-14063 exhaust system mixers for an Energ y Efficient KERKAN, B. F. Engine /E3/ propulsion system Installation effects on cycle selection for small (8188 PAPER 80-0229) 880-20968 turbo-fan engines KUENKLEB, H. 18188 PAPER 80-0106 #80-19280 On the influence of steady state temperature and KERNEBROCK, 3. 1. pressure distortion on the flow characteristics Flow in transonic compressors in an installed multistage jet engine compressor 18188 PA°ER 80-01241 #80-18357 880-1772 4 KIBLEB, K. S. KUGLIE, C. 0. Simulator stndy of stall/post-stall Map-matching techniques for terminal guidance characteristics of a fighter airplane with using Fourier phase information relaxed longitudinal static stability 1180-17 517 (NASA-TP-1538] 1180-18136

B-8

PYNSONAL AUTHOB INDEX NANCY, 8. L.

UHLNAN, 3. N. LIUTENHOZA, 3. F. Optimized aerodynamic design process for subsonic Discontinuous registration of industrial transport wing fitted with vinglets radiographs using profile analysis and piecewise [NASA-CR- 159180] 880-14054 correlation techniques KULINA, N. A80r 17521 Quiet Clean Short-haul Experimental Engine (QCSEE) LO, V. N. main reduction gears detailed design report Guidance system position update by multiple [NASA-CR-1348721 N80-15106 subarea correlation K'lO, A. S. #80-17518 Practical method of fatigue crack growth analysis LOEBENT, G. for damage tolerance assessment of aluminum Stability and control aspects of the CcV-F1O4G structure in fighter type aircraft (NBB-UFE-1447(0) ] 880-14141 [ATAA PAPES 80-01105] #80-183116 LOEWY, B. C. Composite structural materials [NASA-cN-162578) 880-15076 L LONINCZ, 0. 3. LABABBERE, N. Enhanced departure/spin recovery of fighter Automatic recovery after sensor failure onboard aircraft through control of the forebody vortex 880-14 024 orientation LABOYZETTA, B. [AIAA PAPER 80-0173] #80-18352 Methodology for the evaluation of a radar site orebody vortex blowing: A novel control concept 880-14067 to enhance departure/spin recovery - LALANNE, N. characteristics of fighter and trainer aircraft On the use of vibration self-damping materials in 880-15 172 the manufacture of parts for rotating machinery LUCBNTINI, N. 880-14135 Tactical analysis of conflicts in an air traffic LANAB, 3. N. control system: Design and implementation of a Development o f a vortex-lift-design method and provisional model application to a slender maneuver-wing 880-14072 con figuration LUENS, A. B. [AIAA PAPER 80-0327) #80-18316 Effect of tip planform on blade loading LAN, B. characteristics for a two-bladed rotor in hover The quasi-vortex-lattice method for wings with ERASA-TM-78615] 880-140119 edge vortex separation LONNUS, 3. B. [NASA-CR-162530] 480-14052 The criticality of engine exhaust simulations on LANDINGHAN, C. 8. VSTOL model-measured ground effects Aerodynamic data base users guide IAIAA PAPER 80-0230] #80-18276 tAD-AO7I448] 480-15983 LUTEE, P. H. - 1.ANDSON, B. 3. - Experimental determination of pure rotary Assessment of analytic methods for the prediction stability derivatives using curved and rolling of aerodynamic characteristics of arhitrary flow wind tunnel bodies at-supersonic speeds rATAN PAPER 80-0309] A80-18308 IAIAA PAPEB 80-0071] - #80-19308 LYNAN, V. LANSING, D. I. Exploratory studies of the cruise performance of Applications of diffraction theory to aeroacoustics upper surface blown configurations: Program 880-14 870 analysis and conclusions LASAGNA, P. 1. (RASA-cR-159136] 880-15072 Landing approach airframe noise measurements and analysis tNASA-TP-1602] 880-15028 M LAZARICK, B. T. MARE!, 0. G. - Puel conservation benefits and critical Aerodynamic characteristics of moving technologies of recuperative and advanced trailing-edge controls at subsonic and transonic conventional cycle turboshaft engines speeds - - [AIAA PAPER 80-0224] #80-19301 880-15169 LB DI0EET P. NACK, N. 3. Separation due to shock wave-turbulent boundary Studies of leading-edge thrust phenomena layer interaction [AIAA PAPER 80-0325) #80-18315 0NA. TP NO. 1979-1116] A80-20083 MACKALL, N. C. LEE, A. H. Landing approach airframe noise measurements and The YC-14 upper surface blown flap: A unique analysis control surface - NASA-TP-1602-] 880-15028 880-15 157 MACNILLEN, C. 3. LEE, H. Analyses and tests of the B-i aircraft structural Constrained optimum trajectories with specified mode coutrol system range INASA-CR-144887] 1480-15073 #80-18538 NAESTRELLO, L. LEE, N. Experimental and numerical results of sound Vocabulary specification for automatic speech scattering by a body recognition in aircraft cockpits 880-14873 rAD-A073703] 880-1l4303 NAINE, N. B. LEVINE, S. N. Estimation of the accuracy of dynamic Thermal barrier coatings for aircraft gas turbines flight-determined coefficients [AIAA PAP8B 80-0302) #80-18303 tAIAA PAPER 80-0171] #80-17700 LEVY, N. NAISEL, 8. 0. - Practical method o e fatigue crack growth analysis RASA/Army XV-15 tilt rotor research aircraft for damage tolerance assessment of aluminum wind-tunnel test program plan structure in fighter type aircraft [NASA-TN-78562) 880- 15067 [AIAA PAPER 80-0405) #80-18346 HANIA, I. hANG, D. F. Automatic systems for airport surface mobile media Development of aiding GPS/strapdown inertial surveillance based on the use of secondary media navigation system 880-14 104 880-1403 1 NANCY, N. I. LID, C. H. Propulsion options for the RI SPOT long endurance Applications of diffraction theory to aeroacoustics drone airship 880-14 870 [AD-A074595] 880-14132 LID, C. N. Fatigue life prediction of a bonded splice joint AIAA PAPER 80-0305) #80-18306

B-9 NAY, N. E. PERSONAL AUTHOR INDEX

NAY, N. N. NEURZEC, 3. 1. icrobial deterioration of hydrocarbon fuels from Dynamic identification of liaht aircraft oil shale, coal, and petroleum. 1: Riploratory structures and their flutter certification experiments 4480-15145 [AD-A0737611 1480-14259 NEYER, V. I. NCARDLE, 3. 0. Acoustic radiation from axisymmetric ducts - A Static test-stand performance of the YP-102 comparison of theory and experiment turbofan engine with several exhaust [NINA PAPER 80-0097] A80-18268 configurations for the Quiet Short-Haul esearch ENTERS, 1. A. Aircraft (QSPA) The transfer of carbon fibers through a commercial [NASA-TP-15561 4440-114121 aircraft water separator and air cleaner NCAULAY, 3. N. [NASA-CR-159183] 4480-14359 Engine component improvement program - Performance METE, C. improvement Vocabulary specification for automatic speech (AIAA PAPER 80-0223) A80-19300 recognition in aircraft cockpits NCCALL, 0. L. AD-A073703] 880-14303 Loran digital phase-locked loop and RP front-end NICHARL, C. system error analysis On the effects of gaps on control surface FRASA-CR-1627313 880-15065 characteristics NCCRACKEN, N. C. 880-15176 Quiet short-haul research aircraft familiarization NICHAS, B. 0. document Determination of the repeatability of PEC [NASA-Tfl-81149] 880-144108 [AFTE-PR-79/36] 880-14109 NCCULLEY, U. MILES, 7. H. Evaluation of approximate methods for the Dispersion of sound in a combustion duct by fuel prediction of noise shielding by airframe droplets and soot particles components A80-20953 (NASA-TP-100 I4] 1480-15129 NILLER, 0. S. NCFAILS, B. N. Assessment of analytic methods for the prediction Demonstration of short-haul aircraft aft noise of aerodynamic characteristics of arbitrary reduction techniques on a twenty inch (50.4 cm) bodies at supersonic Speeds diameter fan, volume 1 [AlAN PAPER 80-0071] A80-19308 fRASA-CR-134889] 880-15083 NILLEB, N. I. Quiet Clean Short-haul Experimental Engine A method of simplifying weight and balance for (QCSEF) . Aerodynamic and aeromechanical small aircraft performance of a 50.8 cm (20 inch) diameter 1.314 [SAWN PAPER 1278) A80-20630 PR variable pitch fan with core flow EuLER, B. A. [NASA-CR-135017) 880-15087 Thermal barrier coatings for aircraft gas turbines NCKIBNON, N. (AIAA PAPER 80-0302] A80-18303 Recent developments in flight simulation techniques NISEL, 0. V. A80-20 907 Quiet Clean Short-haul Experimental Engine (QCSEE) NCNINNON, B. A. main reduction gears test program Flight and wind tunnel test results of the t NASA-CR-1314669] 880-15103 mechanical jet noise suppressor nozzle NITCHELL, D. U. [AlAN PAPER 80-0165] A80-20971 Effects of the aerodynamic cross-coupling and NCIABTY, T. T. lateral acceleration derivatives on airplane Analysis of rotor-fuselage coupling and its effect dynamic characteristics on rotorcraft stability and response [NINA PAPER 80-0170] A80-17699 A80-17716 MITCHELL, C. A. NCI.AUGHhIN, A. L. Summary of advanced methods for predicting high Reflection cracking of bituminous overlays for speed propeller performance airport pavements: A state of the art (NINA PAPER 80-0225) 4.80-20966 [AD-A073484] 880-14144 NITCHELL, S. C. NCOVAT, B. N. Quiet Clean Short-haul Experimental Engine (QCSEE) Aerodynamic characteristics of moving composite fan frame design report trailing-edge controls at snbsonic and transonic rNaSA-CR-135278] 880-15110 speeds NONHBIWG, V. 880-15 169 Sound generation in a flow near a compliant wall NEADOWS, 3. 8. A80-20 153 Verification of digital autopilot microprocessor EOPPETT, B. N. hardware and software via hardware-in-the-loop Exhaust emission reduction for intermittent simulation combustion aircraft engines A80-20901 (RNSA-CR-159757] 880-14130 NEDVEDET, B. N. MOORE. A. S. Determination of the Stress intensity factor of Static test-stand performance of the TF-102 composite structural members turbofan engine with several exhaust 4.80-17958 configurations for the Quiet Short-Haul Research NELLO, 3. F. Aircraft (QSRA) Correlation of F-15 flight and wind tunnel test [RASA-TP-1556] 880-14121 control effectiveness NOORE, 8. A. 880-15152 Enhanced departure/spin recovery of fighter NEBDBUI, U. N. aircraft through control of the forebody vortex A method of evaluation of gas turbine engines orientation A80-20 064 rAIN?. PAPER 80-0173] A80-18352 NERCATANTI, N. Yorebody vortex blowing: A novel control concept Simulation of a surveillance and control system of to enhance departure/spin recovery surface traffic in an airport characteristics of fighter and trainer aircraft 880-14073 880-15 172 NERCEB, 3. N. NORRIS, N. A. A computer code to model swept wings in an Application of parametric weight and cost adaptive wall tramsonic wind tunnel estimating relationships to future transport [NINA PAPEB 80-0156] A80-19287 aircraft NERLO, U. [SAWN PAPER 1292) A80-20637 Performance evaluation methods of a secondary NORRIS, 8. N. radar network Hypersonic cruise aircraft propulsion integration 880-144 068 study, volnwe 1 [NNSA-CR-158926-VOL-1) 880-150744

B-lU PERSONAL AUTHOR INDEX OWEN, P. K.

Hypersonic cruise aircraft propulsion integration control considerations for Ccv fighters at high study, volume 2 angles of attack r NASA-CR-158926-VOL-2) N80-15075 N80-15 160 MORRISON, B. B. NXBLETT, L. T. Oblique detonation wave rainjet A flutter-speed formula for wings of high aspect rNASA-cR-159192] N80-14131 ratio NORWAY, P. B. N80-151117 Visual accommodation responses in a virtual image NIEDBAL, B. environment A simplified ground vibration test procedure for [AD-A078415] - N80-15082 sailplanes and light aircraft MOINES, 3. F. 580-15186 Plaperon control: The versatile surface for EIBDZIALEK, B. fighter aircraft Experimental investigation of the characteristics NB0-15 158 of pneumatic transfer lines NUEHAMEDOV, P. A. A80-19052 Designing light airplanes NIELSEN, 3. N. A80- 19418 Euler solutions for wing and wing-body combination NULCARE, 0. B. at supersonic speeds with leading-edge separation An assessment of and approach to the validation of [AlAN PAPER 80-0126] A80-18359 digital flight control systems Nonlinear aerodynamics of all-movable controls H80-14036 580-15 173 MONK, N. H. NIESZ, D.. B. The minimum induced drag of aerofoils Comparative resistance of Beta-Si3N4 solid (NACA-121] fl80-15038 solutions to molten silicon attack The aerodynamic forces on airship hulls A80- 180 62 [BACA-184] N80-15039 NORED, 0. L. Elements of the wing section theory and of the Preparing aircraft propulsion for a new era in wing theory energy and the environment rNACA-191] N80-15040 A80-17737 MUTBUXEISURAN, N. NORUN, T. D. Estimation of noise source strengths in a gas Applications of diffraction theory to aeroacoustics turbine combustor 580-14 870 [AIAA PAPER 80-0034] A80-182L15 NOVOSARTOY, 9. P. Unification of oils for aircraft gas-turbine engines N A80-20 690 NAKIMIJRA, I. Rotational noise of helicopter rotors 0 A80- 17718 ODONEDI, P. NASYBOM, C. 0. Visual displays for air traffic control data Simultaneous cabin and ambient ozone measurements N80-14 077 on two Boeing 747 airplanes, volume 1 OPPERRIBS, B. P. (RASA-TM-79166J N80-15059 Methods for strap-down attitude estimation and NEALE, D. H. navigation with accelerometers Estimation of noise source strengths in a gas 580-14034 turbine combustor OGBURN, N. B.. tAIAA PAPER 80-0034] A80-18245 Simulator study of stall/post-stall NEAIE, 0. B., SE. characteristics of a fighter airplane with Mach 3 hydrogen external/base burning relaxed longitudinal static stability AIAA PAPER 80-0280] A80-19311 (NASA-TP-1538] 580-14136 NEIBOP, B. A. OGDEN, J. S. Microbial deterioration of hydrocarbon fuels from Comparative resistance of Beta-Si3N4 solid oil shale, coal, and petroleum. 1: Exploratory solutions to molten silicon attack experiments P80-18062 [AD-A073761] N80-14259 OKABATASHI, N. NELSON, 3. P. Low-aspect-ratio limit of the toroidal reactor - Airport noise, location rent, and the market for The spheromak residential amenities A80-17816 mBa- 17720 ONAT, B. NELSON, B. B., JR. A pre-design code for predicting engine Flaperon control: The versatile surface for acquisition costs fighter aircraft [AlmA PAPER 80-0055] P80-19269 NNO-15158 An extension of engine weight estimation NEPPERT, H. techniques to compute engine production cost ome investigations concerning the effects of gaps [ RD-A074454] N80-15135 and vortex generators on elevator efficiency and OBLOPP, K. L. of landing flap sweep on aerodynamic Effect of tip planform on blade loading characteristics characteristics for a two-bladed rotor in hover R80-15178 rNASA-Ts-78615] 580-14049 NESS, N. C. ORYR, P. An assessment of and approach to the validation of Avionics installation (AVSTALL) cost model for digital flight control systems user equipment of NAVSTAP global positioning N80-14036 system - WEOMARN, H. B. I AD-A073681] 580-14106 An analytical and experimental study of a short OSTGAABD, N. A. • S-shaped subsonic diffuser of a supersonic inlet Technical evalnation report on the 28th Guidance [AIAA PAPER 80-0386] A80-20970 and Control Panel Symposium on Advances in An analytical and experimental study of a short Guidance and Control Systems Using Digital s-shaped subsonic diffuser of a supersonic inlet Techniques INASA-TH-81406] 580-15134 tAGARD-RR-148] 580-15140 NEWMAN, F. N. OWEN, P. K. The physical and chemical characterization of ten Control of forebody three-dimensional flow military turbine engine lubricants separations [AD-A078073] 580-15265 580-15 164 NGUYEN, I. T. Simulator study of stall/post-stall characteristics of a fighter airplane with relaxed longitudinal static stability tNASA-TP-1538] 580-14136

B-Il PALKUTI, 1. 3. PERSONAL AUTHOR INDEX

PHILLIPS, V. H. Altitude response of several airplanes during p landing approach 880-14139 PALKUTI, L. .3. (NASA-TB-80186] Integrated circuit characteristics at 260 C for PIATTELLI, B. aircraft engine-control applications Development trends of airport surface traffic A 80-2 0 112 control radar 880-14 087 PlO, 3. 1. The quasi-vortex-lattice nethod for wings with PIAZZOLI, G. edge vortex separation Dynamic identification of light aircraft (NASA-CR-162530] 880-14052 structures and their flutter certification PABDINI, S. 880-15 145 A survey of the stochastic filtering techniques PIRCUER, B. for data processing in air-traffic control and Automatic recovery after sensor failure onboard surveillance systems 880-14024 A80-20 861 PISCOPO, P. P. Tracking algorithms for mono and multiradar Fuel conservation benefits and critical 880-114074 technologies of recuperative and advanced PARDUE, B. B. conventional cycle turboshaft engines Aircraft fuel system simulator tests with tAIAA PAPER 80-0224] A80-19301 antimisting kerosene (jet A fuel with pw-9 POVINELLI, L. A. addit ive) An analytical and experimental study of a short IAD-A073237] 880-14256 S-shaped subsonic diffuser of a supersonic inlet PABBIS, B. L. [AIAA PAPER 80-0386] A80-20970 The effects of motion and g-seat cues on pilot An analytical and experimental study of a short simulator performance of three piloting tasks s-shaped subsonic diffuser of a supersonic inlet [NASA-TP-1601] 880-15069 r14ASA-TN-81 1406] 880-151344 PAYNE, B. B. Computation of three-dimensional flow in turbofan The minimum cost approach to flutter clearance mixers and comparison with experimental data 880-15 1448 INASA-TB-81410) 880-15364 PEAKE, D. .3. POWERS, S. A. Control of forehody three-dimensional flow The rational design of an airfoil for a high separations performance jet trainer 880-151614 [AIAA PAPER 80-0328] A80-18317 PEARSON, 0. S. PRANDTL, L. Gas turbine carcase and accessory vibration - Applications of modern hydrodynamics to problems of measurement and analysis aeronautics. Part 1: Fundamental concepts and A80-17730 the most important theorems. Part 2: PEARSON, 3. 3. Applications Nap-matching techniques for terminal guidance [RACA-116] 880-150314 using Fourier phase information PRINCE, 3. L. A80- 17517 Integrated circuit characteristics at 260 C for PELEGNIN, I. aircraft engine-control applications Automatic recovery after sensor failure onboard 880-20 112 880-14024 PRODAN, 3. PELLEGRINI, P. F. The T-28 thunder/hailstorm penetration aircraft An air traffic channel simulation by means of 880- 14 64 0 ray-tracing techniques PUTBAN, T. B. 880-14088 Landing approach airframe noise measurements and 1-band measurements in the air traffic channel to analysis characterize secondary radar systems [RASA-T?-1602] 880-15028 880-14092 PELLMAN, A. Non-contacting electro-optical contouring of 0 helicopter rotor blades QUINN, 0. V. {P.D-A070806] 880-14111 The analysis of sound propagation in jet engine PENT, B. ducts using the finite difference method Onboard collision avoidance system: Environmental AD-A074233] 880-14853 influence on the tracking algorithm requirements 880-14 105 PEBIN, 3. R The avionics computer program: Practical BABIEGA, N. A. experiences with a methodology Nodels for freight access to air terminals 880-14037 A80-20869 PERKINS, P. 3. RACHOVITZ, B. I. Simultaneous cabin and ambient ozone measurements The modular life cycle cost model - An overview on two Boeing 7447 airplanes, volume 1 rSAWE PAPER 1290] A80-20636 tNASA-TN-79166] 880-15059 RADCBEWKO, B. D. PERKINS, B. C., JR. Fffect of naphthenic aromatic hydrocarbons on the Navy V/STOL - A continuing initiative oxidizability of hydrogenated jet fuel rskwB PAPER 1325] A80-20655 A80-17 675 PERRY, C. B. RAFYOPOULOS, 0. 0. The Russian satellite navigation system Dispersion of sound in a combustion duct by fuel A 80-20982 droplets and soot particles PETERSEN, B. 3. A8 0-20953 Vocabulary specification for automatic speech BARBiE. S. recognition in aircraft cockpits Sound generation in a flow near a compliant wall tAD-A0737031 880-14303 A80-20 153 PETOT, 0. BAILEY, .3. B. A phenomenological nodel of the dynamic stall of a Redundancy management considerations for a helicopter blade profile control-configured fighter aircraft triplex [ONERA, F? 80. 1979-149] A80-20086 digital fly-by-wire flight control system PEYR ASH, 0. A. 880-114026 Preparing aircraft propulsion for a new era in RIO, 0. N. energy and the environment Investigation of leading-edge devices for drag A80-17737 reduction of a 60-deg. delta wing at high angles PEYBIOLI, B. of attack Filtering of synthetic radar data [AIAA PAPER 80-0310] A80-18309 880-14 076

B-i 2

PERSONAL AUTBOR INDEX SATZER, N.

FAPTIs. V. RODS!, B. B. Recent developments in flight simulation techniques Adaptive allocation of decisionmaking - 880-20907 responsibility between human and computer in RAYENHALL, B. multitask situations Quiet Clean Short-haul Experimental Engine (QCSEE) 680-18022 under-the-wing engine composite fan blade design RUBLE, 3. B. report Regression techniques applied to parametric rNASA-CR-135046] 880-15108 turbine engine simulations REARDOB, L. P. [AIAA PAPER 80-0053] A80-18255 Loading tests of a wing structure for a hypersonic BOGGLES, C. I. aircraft Quiet Clean Short-Haul Experimental Engine (QCSEP) (NASA-TP-1596] 880-15068 Under-The-Wing (UTW) graphite/PMR cowl development REDDY, C. S. [8ASA-CR-135279] 880-14119 Analytical investigation of aerodynamic BUISI, F. characteristics of highly swept wings with I-band measurements in the air traffic channel to separated flow characterize secondary radar systems 880-17697 880-14092 Development of a vortex-lift-design method and RYNASKI, F. C. application to a slender maneuver-wing Design criteria for optimal flight control systems configuration [ AD-A074092] 880-15139 IAIAA PAPER 80-0327] 680-18316 Theoretical study of aerodynamic characteristics of wings having vortex flow S tRASA-cR-159184] 880-14053 SABLA, P. E. REDEEBE, G. Quiet Clean Short-haul Experimental Engine Flight testing of the buffeting behavior of combat - (QCSEE) . Double-annular clean combustor aircraft technology development report [ESA-TT-523] 880-14183 [NASA-CR-159483] 880-15121 REGELSON, B. SACCO, V. vocabulary specification for automatic speech Antireflection techniques for detecting false recognition in aircraft cockpits tracks in air traffic surveillance with [AD-80737031 880-14303 secondary radar REID, 0. B. 880-14100 Development of aiding GFS/strapdown inertial SAINI, 3. K. navigation system The effects of leading edge modifications on the 880-18031 post-stall characteristics of wings RICCIARDBI.LI, S. [AIAA PAPER 80-0199] 680-18375 Radar data utilization in automating the SAINT JOHN, F. H. sequencing of aircrafts in terminal areas Code optimization for solving large 3D FM P problems 880-14071 880- 19 7611 RICE, B. 3. SAINT JOHN, F. S. Comparison of inlet suçpressor data with Advanced technology effects on V/STOL propulsive approximate theory based on cutoff ratio system weight [AIAA PAPER 80-0100] 680-2096(1 [SANE PAPER 1300] #80-20640 RICE, F. K. SALENNE, C. F. Plight certification of the Cessna T0206G Quiet clean Short-haul Experimental Engine (QCSEE) amphibious floatplane under-the-wing engine composite fan blade design A80-18 186 report RICHMOND, L. D. tNASA-CR-135046] 880-15108 Application of finite element analysis to SALIBA, N. derivation of structural weight Simulation of a surveillance and control system of [SANE PAPER 1271] 880-20627 surface traffic in an airport RIBALDI, C. 880-14073 Radar data utilization in automating the SANDERS, B. V. sequencing of aircrafts in terminal areas Dynamic response of a Mach 2.5 axis y mmetric inlet 880-14 071 and turbojet engine with a poppet-value RIB, 0. controlled inlet stability bypass system when In-flight measured characteristics of combined subjected to internal and external airtlow flap-spoiler direct lift controls transients 880-15 165 [ BASA-TP-1531] R80-14123 RIEZO, P. 3. Turbojet-exhaust-nozzle secondary-airflow pumping Thermo-mechanical stress analysis of advanced as an exit control of an inlet-stability bypass turbine blade cooling configuration system for a Mach 2.5 axisymmetric [60-6074098] 880-15136 mixed-compression inlet ROGERS, H. (RASA-TP-1532] 880-14124 Photon correlation laser velocineter measurements SAIDEBSOI, B. in highly turbulent flow fields Some investigations Concerning the effects of gaps [AIAA PAPER 80-0344] 680-18328 and vortex generators on elevator efficiency and ROBE, H. 3. of landing flap sweep on aerodynamic Covariance simulation of RCAS - An aircraft characteristics collision avoidance system 880-15178 A80- 20915 SANKAR, N. I. ROSEBBLUTH, N. B. Reynolds number and compressibility effects on low-aspect-ratio limit of the toroidal reactor - dynamic stall of a NACA 0012 airfoil The spheromak [AIAA PAPER 80-0010] 680-18238 A80-17876 SASSANO, A. ROSKAN, 3. Radar data utilization in automating the Structural parameters that influence the noise sequencing of aircrafts in terminal areas reduction characteristics of typical general 880-14071 aviation materials SATTLER, D. P. [AIAA PAPER 80-0038] A80-18248 The rational design of an airfoil for a high Correlation of predicted longitudinal aerodynamic performance jet trainer characteristics with full-scale wind tunnel data [#188 PAPER 80-0328] 680-18317 on the ATLIT airplane SATZBR, B. [AIAA PAPER 80-0186] A80-18356 Vocabulary specification for automatic speech ROSS, A. 3. recognition in aircraft cockpits A survey of experimental data on the aerodynamics [AD-A073703] 880-1(4303 of controls, in the light of future needs 880-15151

B-i 3 SCHENENSET, B. T. PERSONAL AUTHOR INDEX

SCHEMENSKY, E. T.. Forebody vortex blowing: A novel control concept Development of a vortex-lift-design method and to enhance departure/spin recovery application to a slender maneuver-wing characteristics of fighter and trainer aircraft con figuration 880-15172 tAIAP. PNPPB 80-0327) #80-18316 SNEIANOV, V. A. SCHNIDT, A. B. Unification of oils for aircraft gas-turbine engines Preliminary weight estimation of engine section 880-20 690 structure SEITH, C. A. rsmwE p APER 1311) 880-20645 Nonlinear aerodynamics of all-movable controls SCHEIT'!, V. RHO-lb 173 Aerodynamic interaction on a close-coupled canard SEITH, H. N. wing configuration ! xperience in producing software for the ground 880-15175 station of a remotely piloted helicopter system SCHBITZ, P. B. 880-14038 Acoustically swept rotor - SNuB, p. I NASA-CASE-ARC-11106-1) 880-14107 Discontinuous registration of industrial SCHULTZ, P. H. radiographs using profile analysis and piecewise Atmospheric effects on Nartian ejects emplacement correlation techniques #80- 20192 880-17521 SCBUTZ, 0. SNOLKA, S. Review of investigations into aeronautics related Trajectory behaviour of a control configurated fatigue Federal Republic of Germany aircraft subjected to random disturbances [LBF-S-1421 880-14422 880-15 171 SCOLATTI, C. A. SNORVO, N. 3. Control integration technclogy impact Streamwise development of the flow over a delta wing 880-15 162 [AIAA PAPER 80-0200] 880-18376 SEBASTIAN, 3. 0. SNITH, 8. K. An investigation of several factors involved in a State of the art for digital avionics and finite difference procedure for analyzing the controls, 1978 transonic flow about harmonically oscillating 88 0-14 0 18 airfoils and wings SOHST, H. [NASA-CR-159143] 880-14056 Development aspects of a dynamically tuned gyro SEKEHCIOGLU, I. for strapdown - AERS Comparative resistance of Beta-Si384 solid A80-17 553 solutions to molten silicon attack SOLIGNAC, 3. L. ARO- 18062 Experimental study of confluence with separation SFORZA, P. N. on an afterbody of revolution Streamwise development of the flow over a delta wing [OREPA, TP NO. 1979-151) A80-20088 [AIAA PNPFR 80-0200] 880-18376 SONILErrNER, V. SHAH, P. C. Wind tunnel investigation of controls for DR on a Linear systems analysis program, L224(QR). Volume fighter-type configuration of higher angles of 1: Engineering and usage attack fNASA-CR-2861) 880-14137 880-15 166 SHIP?!, D. 3. SOWERS, H. D. Thermo-mechanical stress analysis of advanced Quiet, Clean, Short-Haul, Experimental Engine turbine blade cooling configuration (QCSEE) Under-The-Wing (UTW) engine acoustic [80-80740981 880-15136 design SHORT, 3. 3. [NASA-CR-135267] 880-14117 An evaluation of the bird/aircraft strike hazard Quiet, Clean, Short-Haul Experimental Engine at Barksdale Air Force Base, Louisiana (SAC) (QCSEE) Over-The-Wing (OTW) engine acoustic design IAD-A074390) 880-14063 [NASA-CR-135268] 880-14118 SHOVALTER, T. N. Quiet Clean Short-haul Fxperimental Engine The effects of motion and 9-seat cues on pilot (QCSEE). Core engine noise seasurements simulator performance of three piloting tasks (RASA-CR-135160] 880-15093 rNASA-TP-1601) 880-15069 STALIAKER, V. A. SHUNNER!, P. K. A computerized method for calculating flutter An experimental model investigation of turbofan characteristics of a system characterized by two engine internal exhaust gas mixer configurations degrees of freedom tAIAA PAPER 80-0228] A80-19302 (NASA-TN-80153) 880-14055 SIDDALINGAPPA, S. STAVINOHA, L. L. Unsteady aerodynamics of two-dimensional spoilers The physical and chemical characterization of ten at low speeds military turbine engine lubricants 880- 15 170 [AD-A074073] 880-15265 SIDES. 3. STECUNA, S. Unsteady effects of a control surface in two Thermal barrier coatings for aircraft gas turbines dimensional, subsonic and transonic flow [8188 PAPER 80-0302] A80-18303 880-1516 8 STEIVINGER, N. SIDORENKO, N. K. Excitation and analysis technique for flight Evaluation of the intensity of beat-induced flutter tests vibrations [8B8-UF-1446(0) 3 880-14140 A80- 17965 STEPANENKO, N. 0. SIEGEL, V. H. Damping capacity of plastic compressor blades Loading tests of a wing structure for a hypersonic 880- 19 868 aircraft STEPHENS, B. E. [RASA-TP-1596] 880-15068 Problems associated with cargo airplanes having SIENIRADZKI, I. aft mounted engines An overvoltage safety system for direct current [SAVE PAPER 1314] 880-20648 aircraft generators STEENBERGEB, N. A80-19051 The modular life cycle cost model - An overview SINPSON, SANE PAPER 1290) A80-20636 Code optimization for sclving large 3D Eli? problems STEVENS, N. L. 880-19764 Surface conforming thermal/pressure seal SKOW, A. N. [NASA-CASE-NSC-18422-1) 880-14400 Enhanced departure/Spin recovery of fighter STEVENSON, C. A. aircraft through control of the forebody vortex An adaptation and validation of a primitive orientation variable mathematical model for predicting the [AIBA PAPER 80-0173) 880-18352 flows in turbojet test cells and solid fuel ray jets [80-8074187] 880-14133

8-14

PERSONAl. AUTHOR INDEX VAN DAM, C. P. G.

STEWART, N. TANCOBRA, A. Avionics installation (AVSTALL) cost model for Problems related to the design and construction of user equipment of NAVSTAI4 global positioning a radar network system 880-14 066 [AD-A073681 1 880-14106 TASSA, I. STEWART V. I. Reynolds number and compressibility effects on Preparing aircraft propulsion for a new era in dynamic stall of a NACA 0012 airfoil energy and the envirctment [AIAA PAPER 80-0010] A80-18238 #80-17737 TERRIS, D. STIMPERT, D. L. Navigation error using rate of change of signal Quiet Clean Short-Haul Experimental Engine (QCSEE) tine of arrival from space vehicles acoustic and aerodynamic tests on a scale model 880- 20 90 II over-the-wing thrust reverser and forward thrust THEODORSEN, ?. nozzle General potential theory of arbitrary wing sections ISASA-CR-135254] 880-14115 [NACA-452] 880-15046 Demonstration of short-haul aircraft aft noise General theory of aerodynamic instability and the reduction techniques on a twenty inch (50.8 cm) mechanism of flutter diameter fan, volume 1 rNAcA-496] 880-15047 [HASA-CR-134849] 880-15083 THOMAS, H. 8. H. N. Demonstration of short-haul aircraft aft noise A survey of experimental data on the aerodynamics reduction techniques on a twenty inch (50.8) of controls, in the light of future needs diameter fan, volume 2 880-15151 [NASA-C8-134850] 880-15084 TIERWEGO, N. J. L. Demonstration of short haul aircraft aft noise Methods for strap-down attitude estimation and reduction techniques on a twenty inrh (50.8 cm) navigation with accelerometers diameter fan, volume 3 880-14034 (NASA-CR-134851] 880-15085 TINOCO, E. N. Acoustic analysis of aft noise reduction Application of a higher order panel method to techniques measured on a subsonic tip speed 50.8 realistic supersonic configurations cm (twenty inch) diameter fan (AIAA PAPER 79-0274] A80-17696 fNASA-CR-134891] 880-15102 TISCHLER, N. B. Quiet Clean Short-haul Experimental Engine (QCSEE) Determination of the spin and recovery Over-The-Wing (OTW) propulsion systems test characteristics of a typical low-wing general report. Volume 4: Acoustic performance aviation design [NASA-CR-135326] 380-15118 (AIAA PAPER 80-0169] #80-18351 STONIER, S. I. TODD. A. I. N. LOX/GOX mechanical impact tester assessment Low-aspect-ratio limit of the toroidal reactor - [NASA-TN-741061 880-15179 The spheromak STOLOV, I. I. #80-17876 Aircraft torque motors TOLLE, F. F. 880- 19199 An extension of engine weight estimation STOTLEB, C. L., JR. techniques to compute engine production cost Quiet Clean Short-haul Experimental Engine [AD-A074454] 880-15135 (QCSEE). Composite fan frame subsystem test TONDI, A. report On the dynamics of compressor surge [NASA-CP-135010] 880-15098 A80-17 900 Quiet Clean Short-haul Experimental Engine (QCSPE) T0NSKOTIEP, 8. Tinder-The-Wing (OTW) composite nacelle subsystem On the influence of steady state temperature and test report pressure distortion on the flow characteristics (NASA-C8-135075] 880-15100 in an installed multistage jet engine compressor STRACK, S. I. A80-17724 Pleet hardness variation TOWI!, C.. E. (AD-#074849] 880-15029 Numerical simulation of supersonic inlets using a STRABLE, V. C. three-dimensional viscous flow analysis Estimation of noise source strengths in a gas (AI#A PAPER 80-0384) A80-20969 turbine colDbnstor TRAMBUSTI, N. (AIAA PAPER 80-0034) A80-18245 L-band measurements in the air traffic channel to Mach 3 hydrogen external/base burning characterize secondary radar systems IAIAA PAPER 80-0280] 880-19311 1480-14092 STUCKENBERG, N. TRAIl, C. T. An observer system for sensor failure detection A phenomenological model of the dynamic stall of a and isolation in digital flight control systems helicopter blade profile 880-14023 (C14ERA, TP 740. 1979-149] A80-20086 STUDNEY, H. V. TRONPETTE, P. Aircraft aerodynamics - Dynamics of longitudinal On the use of vibration self-damping materials in and lateral motion the manufacture of parts for rotating machinery 880-19374 880-14 135 STURGEON, N. B. TUCKER, N. I. Controllers for aircraft ffiotion simulators Experience in producing software for the ground [AIAA PAPER 80-0050) 880-18252 station of a remotely piloted helicopter system SULKOSKE, H. A. 88 0-14038 Regression techniques applied to parametric TURKEL, B. S. turbine engine simulations Current research on aviation weather [AIAA PAPER 80-0053] #80-18255 (bibliography) 1979 SWEETHAN, B. NASA-CR-3214] 880-14651 The next supersonic transport TURNER, D. P. A80-20 214 Advanced materials and the Canaair Challenger [SAVE PAPER 12814] A80-20632 II TABAKOFF, V. V Optimization of turbine nozzle cooling by VAN DAN, C. P. 0. combining impingement and film injection Correlation of predicted longitudinal aerodynamic (#188 PAPER 80-02991 880-19316 characteristics with full-scale wind tunnel data TANGIER, J. I. on the ATLIT airplane Analysis of low-speed helicopter flight test data (AIAA PAPER 80-0186] 880-18356 rAD-A074141] m80-15079

B-iS VANKEUK, C. PERSONAL AUTHOR INDEX

VANKEUK. G. WEIDNER, 3. P. Target tracking using Doppler-information in Propulsion/airframe integration considerations for sensor oriented coordinates with a three high altitude hypersonic cruise vehicles dimensional array radar [hAl PAPER 80-0111] 1*80-18272 [NEPT-270] 1180-114325 WELSH, B. A. VATALARO, P. Aerodynamic characteristics of moving Automatic systems for airport surface mobile media trailing-edge controls at subsonic and transonic surveillance based on the use of secondary media speeds 1180-14 104 1180-15169 VAUSE, B. VELTE, 0. Acoustically swept rotor Hind tunnel measurements and analysis of some NASA-CASE-ARC-i 1106-1) 1180-14107 unusual control surfaces on two swept wing VENTURI, V. fighter configurations I-band measurements in the air traffic channel to 1180-15 155 characterize secondary radar systems WERNER, K. 1180-114092 High angle of attack characteristics of different VESELIANSKAIA, V. N. fighter configurations Effect of naphthenic aromatic hydrocarbons on the [MBB-UPE-1443 (0)3 1180-11*058 oxidizability of hydrogenated let fuel WEBTH, .3. 1*80-17675 Two dimensional aerodynamic interference effects VILENKIN, A. V. on oscillating airfoils with flaps in ventilated Unification of oils for aircraft gas-turbine engines subsonic wind tunnels AR 0-20 690 [NASA-CR-3210] 1180-11401*7 VINCENT, N. C. WESCOTT, P. A. Application of ACS guidelines to weight effective Experience in producing software for the ground aircraft design station of a remotely piloted helicopter system [SANE PAPER 1270] A80-20626 1180-14038 VISSEB, V. WHITNOTER, B. A. An analytical method of testing pavement strength APPDL experience in active control technology A80- 17998 1180-15159 VON OIlER, U. WHITTLE!, 0. C. Assessment at full scale of exhaust nozzle-to-wing Large scale model tests of a new technology V/STOL size on STOL-OTW acoustic characteristics concept A80-20 952 [AIAA PAPER 80-0233] 180-19303 Acoustic considerations of flight effects on jet VIBERL!, S. B. - noise suppressor nozzles composite structural materials [hAl PAPER 80-0164]- 180-20965 tNASA-CR-162578] 1*80-15076 POUNDER, P. N. VILLIANS, .3. C. A high accuracy flight profile determining system Modification of axial compressor streamline 1180-14 042 program for analysis of engine test data [NASA-TM-79312] N80-14051 WILLIAISOE, N. B., .3R. A comparison of first and second order techniques WALKER, U. .3. for computing optimal horizontal gliding y in design with ACT in the presence of strakes tra jectories 15161 rAIRA PAPER 80-0061] 180-18260 WARNNRODT. V. WILLIS, N. S. Pormulation of coupled rotor/fuselage equations of Quiet Clean Short-haul Experimental Engine (QCSEE) notion [11A5A-cR-1591$73] 880-15120 A80-17717 WILLS, B. B. WATSON. .3. H. Comparative resistance of Beta-Si3N4 solid Redundancy management considerations for a solutions to molten silicon attack control-configured fighter aircraft triplex 180-18062 digital fly-by-wire flight control system VIUKEL!AEN, A. B. 1480-14 026 The effects of leading edge modifications on the WATTS. P. 11. post-stall characteristics of wings Gas turbine carcase and accessory vibration - [8111 PAPER 80-0199] 180-18375 Problems of measurement and analysis WIESNEER, 1. 3. 180-17730 Performance evaluation of image correlation WEATHEBILL, V. H. techniques Analysis of transonic flow about harmonically 180-17531* oscillating airfoils and wings WOOD, C. U. rAIRA PAPER 80-01149] 1*110-18367 The Russian satellite-navigation system An investigation of several factors involved in a 180-20 982 finite difference procedure for analyzing the VOODRUP!, B. B. transonic flow about- Farmonically oscillating Effects of varying visual display characteristics airfoils and wings of the 1-4G. a 1-37 flight simulator [NASA-C11-i59183) t80-14056 [AD-A071410] 1180-15180 A users guide for 1*344: 1* progran using a finite V000WAED, 0. S. difference method to analyze transonic flow over Some wind tunnel measurements of the effectiveness oscillating airfoils at low speeds of combined lift and roll controls rNAsA-CR-lSSlDi] 1180-15052 1480-15153 WEBB!, .3. P. WRIGHT, H. B. Experience in producing software for the ground Photon correlation laser velocimeter measurements station of a remotely piloted helicopter system in highly turbulent flow fields 1480-14038 1*111 PAPER 80-0344] 180-18328 WEGER, U. VU, P. T. Investigation of the oscillatory and flight Infrared sensor system performance simulations behavior of rotor systems in relation with 18 0-2 0 90 0 atmospheric turbulence VU, 3. 3. rBNVG-PBWT-79-5] 1180-14142 Recent development of a jet-diffuser ejector WEHRERD, V. B. • .3P. [hIll PAPER 80-0231] - 1*80-18277 Pilot control through the TAPCOS automatic flight WUENNENBERU, H. control system Roll control by digitally controlled segment rNAs1*-TN-81152] 1180-14138 spoilers VEIBENG, 3. A. 880-15156 NASA/Army EV-15 tilt rotor research aircraft Direct side force and drag control with the aid of wind-tunnel test program plan pylon split flaps rNASA-TM-78562] 1180-15067 1480-15163

B-16 PERSONAL AVBOR INDEX ZTKOV, B. N.

WTKES .1. B. Analyses and tests of the B-i aircraft structural node control system INASA-C!-144887) !l80-15073 V !ATES, B. C., .JR. Hybrid vortex method for lifting surfaces with free-vortex flow (AIAA PAPEB 80-0070] A80-19307 TEARLEY, P. 1. Evaluation of the aerodynamic characteristics of a 1/20-scale A-b model at Bach numbers from 0.30 to 0.75 f AD-A074867) 880-15055 YEN, 3. G. Analysis of rotor-fuselage coupling and its effect on rotorcraft stability and response

Y0R, B. N. Fleet hardness variation [AD-A078889] 880-15029 YORK, P. Weight impact of VTOL SAWS PAPEP 1326] #80-20656 rouss y , w. J. Bedundancy management considerations for a control-configured fighter aircraft triplex digital fly-by-wire flight control system s80-1'4026

z ZAPPA, G. Tracking algorithms for mono ad multiradar 880- i fI 078 ZINN, B. T. Acoustic radiation frcn axisynmetric ducts - A comparison of theory and experiment r#IA# PAPEE 80-0097] 980-18268 ZYKOV, B. N. Aircraft torque motors 980-19199

B-17 CONTRACT NUMBER INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Suppl. 121) APRIL 1980

Typical Contract Number Index Listing 1180-15114 1180-15115 4180-15116 118S2-9344 1180-11097 I I 4480-15119 CONTRACT NASA ACCESSION 880-15120 NUMBER NUMBER 1180-15121 880-15122 1180-15123 880-15124 Listings in this index are arranged alphanumerically by contract number. 1480-15125 Under each contract number, the accession numbers denoting documents 1180-151 26 that have been produced as a result of research done under that contract tlAS3'.197514 1180-14130 are arranged in ascending order with the IAA accession numbers appearing number denotes the number by whch the cltaflon s first. The accession 11853-20629 1180-14127 identified in either the /AAor STARrection, 118S4-2519 1180-15073 NAS7-100 880-18062 AF PROJ. 3298 F33615-78—C-3008 14458-32692 1180-14651 1180-15055 880-18340 NGL-05-020-526 A? PROJ. 1123 F33615-78—C-3422 1480-15871 880-15180 880-20626 NGL-33-018-003 A? PROJ. 2307 F33615-78—C-3604 880-15076 1180-15136 880-17699 1108-36-009-017 A? PROJECT 14710130 F40600-79—C-001 880-15063 880-18304 480-19287 1480-15064 AF — APOSR-2824-79 F49620-77—c-0066 NGR-39-009—O 17 1180-15136 880-18268 880-15065 BCS—G0061 1180-14137 NASV-2691 1480-14018 ttGR-50-007-001 DR PROJ. 1F2-62209— Afl-76 NAS1-13175-16 880-14355 1180-15081 880-18308 NSG— 1357 1180-14054 DR PROJ. 1L1-61102—AR-45 NRS1-13871 1180-15070 NSG-1537 880-14052 880-15031 880-15071 NSG-1560 880-19307 DR PROJ. 1L2-62209—AH-76 1180-15072 NSG-1570 880-18351 1480-15079 NAS1-14193 1180-14053 880-18375 DAABO7-77—C-2167 1480-15299 NSG-1578 880-17717 880-17402 NAs1-14193-48 NSG-2007 1480-15871 DAAJO2-17—C-0022 880-17697 NSG-2119 880-18022 1180-15079 RAS1-15057 1480-15074 NSG-2140 880-114047 DAAK IIO-76 — C-1193 1180-15075 4450-6026 1180-15058 880-17517 NAS1-15128 880-18367 NSR-09-051-001 DAAE5O-78— C-0008 880-14056 880-20192 1180-14111 880-15052 8000 14-74—C-0050 DRAK7O-79 — C-0142 WAS1-15238 4480-14359 1180-15173 1180-15265 NAS1-15343 1180-15062 8000 14-78—C-0155 DFG— SFB-83 880-17724 11851-15344 1180-14131 1180-15139 DGRST-75-7-0968 !AS1-15346 4480-14137 N00014-78—C-0547 1180-14135 NAS3-18021 880-14115 880-141417 DNAOO1-77—C-0098 880-14116 8000 14-78—C-0692 880-14199 880-14117 880-14303 DNAOO1-78—C-0138 880-14118 1100019-75—C-0396 1180-15029 1480-14119 880-15077 DNAOO1-78— C-0345 880-14120 11000 19-77—C-0318 480-19764 1180-15083 1180-15030 DOT—FA-77W8-4077 880-15084 0t62269-77—C-02 17 880-18245 1180-15085 1180-15137 DOT — FA7711 81-817 1180-15086 1162269-78—C-0286 1480-14064 880-15087 880-15135 DOT— FA78WAI-925 1180-15 088 1462269-79—C— 0204 1180-14256 1180-15089 1180-14132 DOT— TS-14698 880-20915 1180-15090 SF54592201 880-15137 E(11-1)-3237 880-17876 1180-15091 W-7405—E14G-148 EY-76 — C-02-3073 1180-15092 1180-15182 880-17876 1180-15093 1180-15183 FAR PROJ. 052-2 111-04 1180-15094 118041010101 1180-15082 1180-14064 880-15095 ZF57571004 1180-14259 F04701-78—C-0124 1180-15096 505— 02-54 880-15068 880-14106 1180-15097 505-03 1180-14125 F08635-76— C-0306 1480-15098 505-04 1480-14124 880-18534 1180-15099 880-15128 F30602-77—C-0049 1480-15100 505-06-31 1180-14047 880-17518 1180-15101 505-06-63-03 1180-14136 F33615-75— C-3016 880-15102 505-09-41 1180-15069 880-18304 1180-15103 505-10-23-03 1480-15031 F33615-75—C-3144 880-151014 505-33-53-03 880-15874 880-183014 1480-15105 505-34-33-02 1480-14139 F33615-76— C-1300 1180-15106 513-52-01-16 880-114114 880-17534 4480-15107 535-03-14 1180-15028 F33615-76— C-3072 1180-15108 7144-01-01 1180-15067 880-17699 1180-15109 769-02 880-14121 F33615-77— C-3036 880-15110 1480-14026 1480-15111 F33615-78— C-3000 1180-15112 880-18358 4480-15113

C—i 1. Report No. 2. Government Accession No. 3. Recipient 's Catalog No. NASA SP-7037 (121) 4. Title and Subtitle 5. Report Date April 1980 AERONAUTICAL ENGINEERING 6. Performing Organization Code A Continuing Bibliography Supplement 121)

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

______10. Work Unit No. 9. Performing Organization Name and Address

National Aeronautics and Space Administration 11. Contract or Grant No. Washington, D. C. 205146

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 1411 reports, articles, and other documents introduced into the NASA scientific and technical information system in March 1980.

17. Key Words (Suggested by Author(s)) 18. Di5trttic41 Statement Aerodynamics Aeronautical Engineering Unclassified — Unlimited Aeronautics Bibl iographies

19. Security Ciassif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price Unclassified Unclassified 1314 $5.00 HC

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NASA CONTINUING BIBLIOGRAPHY SERIES

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