NASA I Aeronautical Engineering Aer Ering Aeronautical Engineerin

Aeronautical NASA SP-7037 Engineering May 1978 • %Jf \^^H % NASA ; :ography with lnd<

National Aeronautics and Space Administration

I Aeronautical Engineering Aer [Q 01^ cpm ering Aeronautical Engineerin igineerjng Aeronautical Engin Dal Engineering Aeronautical E nautical Engineering Aeronau Aeronautical Engineering Aer 3ring Aeronautical Engineering gineering Aeronautical Engine al Engineering Aeronautical E lautical Engineering Aeronaut Aeronautical Engineering Aerc ring Aeronautical Engineering ACCESSION NUMBER RANGES

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

STAR(N-10000 Series) N78--15986 —N78-17988

IAA (A-10000 Series) A78-206I5 -A78-24823

bibliography was prepared by the NASA Scientific and Technical Information Facility operated for the National Aeronautics and Space Administration by Informatics Information NASA SP-7037(96)

AERONAUTICAL ENGINEERING

A Continuing Bibliography

Supplement 96

A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in April 1978 in • Scientific and Technical Aerospace Reports (STAR) • International Aerospace Abstracts (IAA)

Scientific and Technical Information Office 1978 National Aeronautics and Space Administration Washington, DC This Supplement is available from the National Technical Information Service (NTIS), Springfield, Virginia 22161. at the price code E02 ($4.75 domestic. $9 50 foreign) INTRODUCTION

Under the terms of an mteragency agreement with the Federal Aviation Administration this publication has been prepared by the National Aeronautics and Space Administration for the joint use of both agencies and the scientific and technical community concerned with the field of aeronautical engineering. The first issue of this bibliography was published in September 1970 and the first supplement in January 1971. Since that time, monthly supplements have been issued This supplement to Aeronautical Engineering - A Continuing Bibliography (NASA SP-7037) lists 448 reports, journal articles, and other documents originally announced in April 1978 in Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (IA A) The coverage includes documents on the engineering and theoretical aspects of design, construction, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and associated components, equipment, and systems It also includes research and development in aerodynamics, aeronautics, and ground support equipment for aeronautical vehicles. Each entry in the bibliography consists of a standard bibliographic citation accompanied in most cases by an abstract. The listing of the entries is arranged in two major sections, IAA Entries and STAR Entries, in that order. The citations, and abstracts when available, are reproduced exactly as they appeared originally in IAA and STAR, including the original accession numbers from the respective announcement journals. This procedure, which saves time and money, accounts for the slight variation in citation appearances. Three indexes — subject, personal author, and contract number -- are included. An annual cumulative index will be published.

in AVAILABILITY OF CITED PUBLICATIONS

IAA ENTRIES (A78-1OOOO 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 $6 00 per document up to a maximum of 20 pages, the charge for each additional page is $025 Microfiche'" of documents announced in IAA are available at the rate of $250 per microfiche on demand, and at the rate of $1 10 per microfiche for standing orders for all IAA microfiche The price for the IAA microfiche by category is available at the rate of $1 25 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 35 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 (N78-10000 Series)

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

Avail NTIS Sold by the National Technical Information Service Prices for hard copy (HC) and microfiche (MF) are indicated by a price code followed by the letters HC or MF in the STAR citation Price codes are given in the tables on page vn of the current issue of STAR

Microfiche is available regardless of age for those accessions followed by a § symbol

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

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

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 $300 price, for those documents identified by a # symbol)

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

IV Avail NASA Public Document Rooms Documents so indicated may be examined at or purchased from the National Aeronautics and Space Administration. Public Documents Room (Room 126), 600 Independence Ave . SW. Washington. DC 20546. or public document rooms located at each of the NASA research centers, the NASA Space Technology Laboratories, and the NASA Pasadena Office at the Jet Propulsion Laboratory

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

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

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

SUBSCRIPTION AVAILABILITY

This publication is available on subscription from the National Technical Information Service (NTIS) The annual subscription rate for the monthly supplements is $45 00 domestic. $75 00 foreign All questions relating to the subscriptions should be referred to NTIS. Ann 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 750 Third Ave New York. NY 10017 Superintendent of Documents U S Government Printing Office British Library Lending Division. Washington. D C 20402 Boston Spa. Wetherby, Yorkshire. England University Microfilms Commissioner of Patents A Xerox Company U S Patent Office 300 North Zeeb Road Washington. D C 20231 Ann Arbor. Michigan 48106

Energy Research and Development University Microfilms. Ltd Administration Tylers Green Technical Information Center London, England PO Box 62 Oak Ridge. Tennessee 37830 U S Geological Survey ESA-Space Documentation Service 1033 General Services Administration ESRIN Building Via Galileo Galilei Washington, D C 20242 00044 Frascati (Rome) Italy

U S Geological Survey Her Majesty's Stationery Office 601 E Cedar Avenue P 0 Box 569. S E 1 Flagstaff. Arizona 86002 London. England

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

U S Geological Survey National Aeronautics and Space Bldg 25, Denver Federal Center Administration Denver, Colorado 80225 Scientific and Technical Information Office (NST-41) Washington. D C 20546 Zentralstelle fur Luftfahrtdoku- mentation und -Information National Technical Information Service 8 Munchen 86 5285 Port Royal Road Postfach 880 Springfield. Virginia 22161 Federal Republic of Germany TABLE OF CONTENTS IAA Entries 157 STAR Entries 193

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

TYPICAL CITATION AND ABSTRACT FROM STAR

NASA SPONSORED DOCUMENT .AVAILABLE ON MICROFICHE -»-N78-10020*jfl Boeing Vertol Co Philadelphia Pa—- WIND TUNNEL INVESTIGATION OF ROTOR LIFT AND NASA ACCESSION PROPULSIVE FORCE AT HIGH SPEED DATA ANALYSIS -CORPORATE NUMBER —»•Frank McHugh Ross Clark and Mary Soloman Oct 1977 •• SOURCE 211 p 3 Vol ^(Contract NAS1-14317) TITLE . r*-

TYPICAL CITATION AND ABSTRACT FROM IAA

NASA SPONSORED. AVAILABLE ON H MICROFICHE r—»- A78-13071 * ft ^^. Toward a new V/STOL generation L Roberts- AIAA ACCESSION NUMBER | and S B Anderson (NASA, Ames Research Center, Moffett Field, - Calif) Astronautics and Aeronautics, vol 15, Nov 1977rT> 22-27 AUTHORS While many V/STOL problems are now better understood and TITLE . technology has progressed to the point where higher thrust/weight ratios and greater stability augmentation are achievable, a number of AUTHOR'S TITLE OF still existing insufficiencies provide a sobering reminder that learning AFFILIATION PERIODICAL- in ground testing and simulation, and careful methodical planning, are a prerequisite for any research and development program The -PUBLICATION present paper is centered on the maior technical problems for the DATE Navy Type multimission V/STOL aircraft The aircraft's configurations with and without forward lift fan are discussed, along with the propulsion systems, testing techniques, controls, displays, flight dynamics, and ground/flow field interactions V P

VIII AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 96)

MAY 1978

that the lower surface is not directly predictable by strip theory and IAA ENTRIES that unexpected flow distortions occur near the centerlme, that the fuselage sides and strake regions require careful attention to specification of streamline origin and careful analyses of the data to assure turbulent flow in the experiment, that unpredictable hot streaks emanate from the strake-body juncture at low angles of attack, and that the upper surface is a highly unpredictable region of separated, high energy, vortical flow (Author) A78-20627 fj Detection of sensor failure and output reconstruction for aircraft engine controls W R Wells (Wright State A78-20648 * ft Study of heat sink thermal protection systems University, Dayton, Ohio) American Institute of Aeronautics and for hypersonic research aircraft. W A Vahl and C L W Edwards Astronautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala, (NASA, Langley Research Center, High-Speed Aerodynamics Div , Jan 16-18, 1978, Paper 78-4 7p 11 refs Hampton, Va ) American Institute of Aeronautics and Astronautics, In this work, the problem of the detection of output sensor Aerospace Sciences Meeting, 16th, Huntsville, Ala, Jan 16-18, 1978, failure and corresponding output reconstruction for application to Paper 78-38 12 p 7 refs aircraft engine control is discussed The requirements of modern The feasibility of using a single metallic heat sink thermal engine control to regulate engine variables to achieve satisfactory protection system (TPS) over a projected flight test program for a transient and steady-state engine performance are better achieved by hypersonic research vehicle was studied using transient thermal this reconstruction The detection strategy discussed is that accom- analyses and mission performance calculations Four materials, plished through the application of Bayesian hypothesis testing to the aluminum, titanium, Lockalloy, and beryllium, as well as several sensor output records This technique requires statistical information combinations, were evaluated Influence of trajectory parameters which is generated by a bank of Kalman filters the by-product of were considered on TPS and mission performance for both the clean which is a reconstruction of the failed sensor states Simulated vehicle configuration as well as with an experimental scramjet numerical examples are used to demonstrate the detection and mounted From this study it was concluded that a metallic heat sink reconstruction capabil ity of the algorithm (Author) TPS can be effectively employed for a hypersonic research airplane flight envelope which includes dash missions in excess of Mach 8 and A78 20632 * ,7 Calculation of unsteady transonic flows using 60 seconds of cruise at Mach numbers greater than 6 For best heat the integral equation method D Nixon (NASA, Ames Research sink TPS match over the flight envelope, Lockalloy and titanium Center, Moffett Field, Calif ) American Institute of Aeronautics and appear to be the most promising candidates (Author) Astronautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala , Jan 16-18, 1978, Paper 78-13 12 p 13 refs The basic integral equations for a harmonically oscillating airfoil A78-20651 * # A review of NASA's propulsion programs for in a transonic flow with shock waves are derived, the reduced civil aviation W L Stewart (NASA, Lewis Research Center, frequency is assumed to be small The problems associated with Cleveland, Ohio), H W Johnson (NASA, Aeronautical Propulsion shock wave motion are treated using a strained coordinate system Dw, Washington, DC), and R J Weber (NASA, Lewis Research The integral equation is linear and consists of both line integrals and Center, Mission Analysis Branch, Cleveland, Ohio) American surface integrals over the flow field which are evaluated by Institute of Aeronautics and Astronautics, Aerospace Sciences quadrature This leads to a set of linear algebraic equations that can Meeting, 16th, Huntsville, Ala , Jan 16-18, 1978, Paper 78-43 14 p be solved directly The shock motion is obtained explicitly by 19 refs enforcing the condition that the flow is continuous except at a shock Five NASA engine-oriented propulsion programs of major wave Results obtained for both lifting and nonhftmg oscillatory importance to civil aviation are presented and discussed Included are flows agree satisfactorily with other accurate results (Author) programs directed at exploring propulsion-system concepts for (1) energy-conservative subsonic aircraft (improved current turbofans, A78-20647 ff Aerodynamic heating to the hypersonic re- advanced turbofans, and advanced turboprops), (2) supersonic cruise search aircraft, X-24C R D Neumann, J L Patterson, and N J aircraft (variable-cycle engines). (3) general aviation aircraft (im- Shski (USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, proved reciprocating engines and small gas turbines), (4) powered-lift Ohio) American Institute of Aeronautics and Astronautics, Aero- aircraft (advanced turbofans), and (5) advanced rotorcraft These space Sciences Meeting, 16th, Huntsville, Ala, Jan 16-18, 1978, programs reflect the opportunities still existing for significant Paper 78-37 11 p improvements in civil aviation through the application of advanced The paper discusses the aerodynamic heating environment propulsion concepts (Author) sustained by the X 24C aircraft evaluated from ground test data and from engineering design techniques including computer solutions appropriate for the preliminary design process The paper shows that A78-20652 ff Trends and research opportunities in air- through proper evaluation of the recovery factor, data from breathing propulsion B Qumn (USAF, Office of Scientific Research, hypersonic tunnels can be brought into agreement The data show Washington, D C ) American Institute of Aeronautics and Astro-

157 A78-20663

nautics. Aerospace Sciences Meeting, 16th, Huntsville, Ala, Jan Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, 16-18. 1978, Paper 78-44 10 p 9 refs Huntsville, Ala, Jan 16-18, 1978, Paper 78-98 9p 8 refs The dramatic improvement in jet engine performance is illus- The method of latin squares was applied to a three-dimensional trated with the aid of a graph which shows that the thrust to-weight mission space for a typical ground attack mission profile and ratio has doubled, approximately, every fifteen years Structural independently to a three-dimensional design space to select input improvements are partly related to advances in materials sciences conditions for an aircraft sizing program For each mission, the Engines during the early forties were made almost entirely from' output take-off-gross-weights (TOGW) and corresponding design conventional steels, stainless steel and aluminum were first used points determined a quadratic polynomial for TOGW in the three during the late forties, alummum began to be displaced by titanium design variables by least squares regression analysis The minimum in the mid-fifties, and in the mid-sixties the superalloys began to play TOGWs corresponding to each of the thirteen selected mission points a dominant role and large by-pass ratio fans increased the relative were then determined and these were fit by a quadratic polynomial importance of titanium Recent trends are related to the introduc- in the three mission variables The result is a simple algebraic tion of composites Attention is also given to trends concerning relationship between mission requirements and TOGW for geometri- turbine inlet temperatures, higher through flows, lower specific fuel cally optimized fighter aircraft In a second application of these consumption, and the increasing cost of advanced technology methods, two engine variables were included in the design space Research opportunities considered are related to fluid mechanics, (Author) structural and material mechanics, combustion chemistry, thedevel opment of resin matrix composite materials, and mathematics G R A78-20685 # Computational transonic airfoil design in free air and a wind tunnel V Shankar, N D Malmuth (Rockwell International Science Center, Thousand Oaks, Calif), and J D Cole A78-20663 # The analysis of wing-body combinations at (California, University, Los Angeles, Calif) American Institute of moderate angles of attack N Uchiyama, R P Mikkilmem, and J M Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, Wu (Tennessee, University, Tullahoma, Tenn ) American Instituteof Huntsville, Ala, Jan 16-18, 1978, Paper 78-103 9 p 11 refs Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, Contract No F44620-6 C-0044 Huntsville, Ala, Jan 16-18, 1978, Paper 78-62 7 p 10 refs Grant A computational inverse procedure for transonic airfoils in No DAAG2977-G0108 which shapes are determined supporting prescribed pressure distribu- A computational scheme is developed to predict the flow over tions, is presented The method uses the small disturbance equation, wing-body combinations at moderate angles of attack and the results and a consistent analysis-design differencing procedure at the airfoil of computation are presented for two different wing body combina- surface This avoids the intermediate analysis design-analysis itera- tions The wing is represented by a system of discrete nonmtersectmg tions The effect of any openness at the trailing edge is taken into vortex lines Each vortex line in the wake is composed of a series of account by adding an effective source term into the far field A straight finite segments and a semi-infinite segment The body is systematic expansion procedure which models the far field for solid represented by a system of source/sink elements distributed on the tunnel walls is presented along with some design results for the surface of the body The effect of lifting nose is taken into account associated boundary conditions and those for a free field (Author) by a horseshoe vortex system, the strength and the location of which are based on the empirical relations The basic unknowns in the A78-20686 * # Transonic wing analysis using advanced com- problem are the strengths of the vortex elements and the source/sink putational methods P A Henne (Douglas Aircraft Co , Long Beach, elements, and the direction of the vortex elements in the wake The Calif ) and R M Hicks (NASA, Ames Research Center, Moffett problem is solved using an iterative approach Numerical results are Field, Calif) American Institute of Aeronautics and Astronautics, presented for two wing body combinations The shape of the trailing Aerospace Sciences Meeting, 16th, Huntsville, Ala , Jan 16 18, 1978, vortex sheet is shown at different stations along the body (Author) Paper 78-105 10 p 9 refs This paper discusses the application of three-dimensional com- A78-20664 # Normal-force and pitchmg-moment coeffi- putational transonic flow methods to several different types of cients of wing-body combinations at very high angles of attack D transport wing designs The purpose of these applications is to Nikohtsch (Messerschmitt-Bolkow-Blohm GmbH, Munich, West Ger- evaluate the basic accuracy and limitations associated with such many) American Institute of Aeronautics and Astronautics, Aero- numerical methods The use of such computational methods for space Sciences Meeting, 16th, Huntsville, Ala, Jan. 16-18, 1978, practical engineering problems can only be justified after favorable Paper 78-63 10 p 19 refs evaluations are completed The paper summarizes a study of both the A method has been developed to calculate normal force and small-disturbance and the full potential technique for computing pitching moment of wing-body combinations at angle of attack up to three dimensional transonic flows Computed three dimensional re 40 deg in the subsonic Mach-number range The body is treated suits are compared to both experimental measurements and theoreti according to Wardlaw's multi-vortex model, which has been im- cal results Comparisons are made not only of pressure distributions proved by using a more realistic representation of free vortices The but also of lift and drag forces Transonic drag rise characteristics are exposed wing is calculated with the aid of the Gersten's nonlinear compared Three-dimensional pressure distributions and aerodynamic lifting surface theory The mutual interference is considered partially forces, computed from the full potential solution, compare reason by the slender-body theory and partially by taking into account the ably well with experimental results for a wide range of configurations induced velocities Comparisons between theory and tests show good and flow conditions (Author) agreement (Author) A78-20687 * tf Laser-velocimeter surveys of merging vortices A78-20683 * ;'/ Temperature distributions and thermal stresses in a wind tunnel V R Corsiglia, K L Orloff (NASA, Ames in a graded zircoma/metal gas path seal system for aircraft gas Research Center, Moffett Field, Calif), and J D Iversen (NASA, turbine engines C M Taylor (NASA, Lewis Research Center, Ames Research Center, Moffett Field, Calif , Iowa State University Cleveland, Ohio, Leeds University, Leeds, England) and R C Bill of Science and Technology, Ames, Iowa) American Institute of (NASA, Lewis Research Center, U S Army, Propulsion Laboratory, Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, Cleveland, Ohio) American Institute of Aeronautics and Astro- Huntsville, Ala, Jan 16-18, 1978, Paper 78-107 10 p 28 refs nautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala, Jan The merger of two vortices was studied with a laser velocimeter 16-18, 1978, Paper 78-93 11 p 5 refs designed to measure the two cross-stream components of velocity Measurements were made at several downstream distances in the A78-20684 # Relating take off gross weight and mission vortex wake shed by two semispan wings mounted on the wind requirements for geometrically optimized aircraft. M K Greenway tunnel walls The velocity data provided well defined contours of (USAF, Washington, D C) and S J Koob (USAF, Institute of cross flow velocity, stream function and vorticity Downstream of Technology, Wright-Patterson AFB, Ohio) American^ Institute of the merger point the vorticity ^as shown to be independent of the

158 A78-20708

downstream distance for small radii, and at larger radii was aircraft Parametric investigations of wing loading, thrust-to-weight dependent on the distance from the wing rather than from the ratio, payload size and vehicle size are presented Results indicate merger point Upstream of the merger point a multicell vorticity improvements in performance for a wide range of potential payload pattern was shown (Author) sizes, particularly when in-flight refueling of the JP fuel is considered as a means of increasing range and mission flexibility (Author) A78-20701 * ff Development and test of an inlet and duct to provide airflow for a wing boundary layer control system D W A78-20706 * # An aerodynamic analysis of several hypersonic Gunnarson (Boeing Commercial Airplane Co , Seattle, Wash ) and J research airplane concepts from IV) = 0 2 to 6 0 J A. Penland, J L. C McArdle (NASA, Lewis Research Center, Cleveland, Ohio) Dillon, and J L Pittman (NASA, Langley Research Center, American Institute of Aeronautics and Astronautics, Aerospace High-Speed Aerodynamics Div, Hampton, Va ) American Institute Sciences Meeting, 16th, Huntsville, Ala, Jan 16-18, 1978, Paper of Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, 78-141 9p NASA sponsored research Huntsville, Ala, Jan. 16-18, 1978, Paper 78-150 12 p 21 refs The boundary layer control (BLC) system of the quiet short- Several conceptual hypersonic research airplanes, designed haul research airplane (QSRA) requires significant amounts of within the constraints of a B-52 launch aircraft, have been studied pressurized airflow for successful operation An inlet and duct were experimentally and analytically at Mach numbers from 0 2 to 6 0 successfully developed which removed airflow from the engine fan Vehicles built to these criteria for Mach 6 cruise were shown to be duct for the BLC system at or above the required total pressure of feasible, if careful attention was paid to the low speed lift, drag, and 99% of the average fan duct total pressure The design was high angle of attack stability to assure successful landings and constrained by the tight space limitations of the QSRA nacelle transonic pitch angle maneuvers The integrated scramjet engine drag Potential flow with boundary layer analysis techniques were used as was high at subsonic speeds and appears to be constant with an aid to select the inlet and duct geometries Airflow and total Reynolds number The variable geometry airfoil used previously to pressure profile data were obtained during development tests improve directional stability was shown to be equally adaptable to (Author) the improvement of longitudinal stability The vortex lattice theory gave good subsonic predictions of lift, drag due to lift, and pitching A78-20702 * # A combined potential and viscous flow solu- moments Wind tunnel tests must be relied on for the drag at zero tion for V/STOL engine inlets A H Ybarra, W W Rhoades (Vought lift, trim, static margins and lateral-directional stability The Gentry Corp , Dallas, Tex ), and N 0 Stockman (NASA, Lewis Research Hypersonic Arbitrary Body Program gave good predictions of the Center, Cleveland, Ohio) American Institute of Aeronautics and trends of lift, drag, and pitching moments with angle of attack at Astronautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala, Mach numbers above 3, but the level of the values were not Jan 16-18, 1978, Paper 78-142 8p 5 refs consistently predicted No currently available theory or program gave A potential flow routine and a viscous boundary layer routine accurate predictions of directional stability or dihedral effects at have been combined into a single routine for estimating the flow in hypersonic speeds (Author) and around subsonic inlets In this combined routine, the viscous flow solution about the inlet body is obtained by adding the viscous A78-20707 * Viscous thin airfoil theory and the Kutta displacement thickness to the inlet geometry Combination of the condition J E Yates (Aeronautical Research Associates of ^wo flow solutions has resulted in cost savings, both in preparation Princeton, Inc , Princeton, N J ) American Institute of Aeronautics time and in computer time This routine is a useful tool in optimizing and Astronautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala , lip shapes for V/STOL inlets The method of combining the routine, Jan 16-18, 1978, Paper 78-152 8 p 17 refs Contract No ,comparison with NASA test data, and utilization of the routine for N00014-76-C-0576 ' V/STOL inlet design are presented (Author) The linearized thin airfoil problem is formulated for viscous incompressible fluids, and the viscous counterpart of the classical A78-20704 # The prediction of the performance of low integral equation of thin airfoil theory is derived It is shown that for pressure-ratio thrust-augmenter ejectors J A C Kentfield (Calgary, any Reynolds number, however large, the Cauchy singularity in the University, Calgary, Alberta, Canada) American Institute of Aero- mviscid kernel is replaced by a much weaker logarithmic singularity nautics and Astronautics, Aerospace Sciences Meeting, 16th, Hunts- Plausible arguments for the uniqueness of solution of the integral ville, A/a , Jan 16-18, 1978, Paper 78-145 11 p 8 refs equation are given An asymptotic solution of the viscous airfoil A description is given of a simple procedure for predicting the equation is developed for high Reynolds number As Reynolds static performance of low pressure-ratio thrust-augmenter ejectors number tends to infinity, the viscous solution tends to the mviscid equipped with hypermixing primary nozzles Such ejectors have been solution obtained by invoking the Kutta condition The Reynolds- proposed as vertical, and transitional, flight mode thrust augmenters number correction to the Kutta condition or the lift curve slope is for VTOL aircraft The analysis is based on incompressible flow found to be much greater than boundary-layer thickness effects concepts employed in such a way that the thrust augmentation ratio calculated with the mviscid parallel shear-flow boundary-layer model is evaluated with negligible error Results are presented of a For Reynolds number between one and ten million, the reduction in parametric, computer generated, study showing the sensitivity of the lift curve slope is approximately 20 percent and offsets the increase optimized performances of a basic ejector configuration to changes due to the geometric thickness of the airfoil (Author) in loss coefficients, area ratio and operating conditions It was concluded that it is most important to achieve the highest possible A78-20708 * ff Subsonic vortex-flow design study for slender effectiveness of the ejector diffuser and that ejectors with large area wings J E Lamar (NASA, Langley Research Center, Hampton, Va ) ratios are particularly adversely affected by back pressure Compari- American Institute of Aeronautics and Astronautics. Aerospace sons of predictions made using the analytical procedure with Sciences Meeting, 16th, Huntsville, Ala, Jan 16-18, 1978, Paper experimental results generated by ARL show good agreement 78-154 10 p 11 refs (Author) A theoretical study describing the effects of spanwise camber on the lift dependent drag of slender delta wings having leading-edge- A78-20705 * ff The application of dual fuel /JP-LH2/ for vortex-flow is presented The earlier work by Barsby. using conical hypersonic cruise vehicles J P Weidner (NASA, Langley Research flow, indicated that drag levels similar to those in attached flow Center, High-Speed Aerodynamics Div , Hampton, Va ) American could be obtained This is reexammed and then extended to the Institute of Aeronautics and Astronautics, Aerospace Sciences more practical case of noncomcal flow by application of the Meeting. 16th, Huntsville, Ala , Jan 16-18, 1978, Paper 78-149 8p vortex-lattice method coupled with the suction-analogy and the 6 refs recently developed Boeing free-vortex-sheet method Lastly, a design The possibility of utilizing jet fuel (JP) stored primarily in the code is introduced which employs the suction analogy in an attempt wings of hydrogen-fueled hypersonic cruise vehicles has been to define 'optimum' camber surfaces for minimum lift dependent evaluated and compared to the performance of all hydrogen-fueled drag for vortex flow conditions (Author)

159 A78-20709

A78-20709 # The prediction of two dimensional airfoil stall to wall interference A family of curves which can be used to progression L W Gross (McDonnell Aircraft Co , St Louis, Mo ) estimate lift and pitching moment interference at transonic speeds is American Institute of Aeronautics and Astronautics, Aerospace presented, and an empirical dependency of lift interference on AR Sciences Meeting, 16th, Huntsville, Ala, Jan 16-18, 1978, Paper squared is suggested (Author) 78-155 12 p 24refs A generalized boundary condition potential flow calculation A78-20717 # Experimental investigation of support inter- method has been combined with a momentum integral boundary ference on an ogive cylinder at high incidence W E Dietz, Jr and layer method and a base flow theory of separation to predict airfoil M C Altstatt (ARO, Inc , Propulsion Wind Tunnel Facility, Arnold viscous mviscid interference up to and beyond stall The resultant Air Force Station, Tenn ) American Institute of Aeronautics and program considers laminar and turbulent separation and is, therefore, Astronautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala, applicable to thin or thick airfoil stall The calculated flow field Jan 16-78, 1978, Paper 78-165 8p 6 refs includes the airfoil and the separation bubble recombination region A wind tunnel test was conducted to determine the support and behind the airfoil Calculated pressure distributions and integrated tunnel wall interference on an ogive-cylinder model at high angles of values for lift are compared to measurements for several airfoils attack in transonic flow The model was supported by either a demonstrating different types of stall The comparisons show a good base-mounted sting or a strut attached to the leeside of the model prediction of the viscous interference effects (Author) The strut support acted as a splitter plate and generally reduced the normal-force coefficient, whereas the sting support increased the A78-20710 ,--;' An analysis method for the viscous flow over normal-force coefficient slightly The support interference circulation-controlled airfoils F A Dvorak (Analytical Methods, diminished with increasing Mach number A simple algebraic method Inc , Bellevue, Wash ) and R J Kind (Carleton University, Ottawa, of estimating support interference was postulated Two semi Canada) American Institute of Aeronautics and Astronautics, empirical methods for calculation of aerodynamic coefficients were Aerospace Sciences Meeting, 16th, Huntsville, Ala , Jan 16-18, 1978, compared with test results (Author) Paper 78-157 11 p 24 refs Contract No N00600-76-C-1494 A method developed for the analysis of the incompressible A78-20718 * # Reynolds number cnticality in dynamic tests viscous flow over circulation-controlled airfoils is described A L E Ericsson and J P Reding (Lockheed Missiles and Space Co , surface vorticity method is used to solve the mviscid portion of the Inc , Sunnyvale, Calif I American Institute of Aeronautics and flow and a combination of integral and finite-difference methods is Astronautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala, used to calculate the development of the viscous layers An iterative Jan 16-18. 1978, Paper 78-166 14 p 48 refs Contracts No process is used to arrive at final solutions which satisfy an NAS8-5338, No NAS8 11238, No NAS8 20354, No NAS8-28130, appropriate trailmg-edge condition and incorporate the interaction No NAS8-30652 between the viscous and potential regions of the flow Comparisons To extrapolate from subscale wind tunnel tests to full-scale between calculated and experimental results show good agreement flight is a well-recognized problem It becomes especially critical for for surface pressure distributions and lift coefficients over a range of present day high performance missiles and aircraft which operate at blowing momentum coefficient from 0 to 0 12 (Author) high angles of attack where separated flow effects often dominate the vehicle aerodynamics The dynamic effects of flow separation A78-20713 * # Steady and unsteady transonic flow H L can usually not be simulated at subscale Reynolds numbers This is Seegmiller, J G Marvin, and L L Levy, Jr (NASA, Ames Research illustrated by examples of tests with slender vehicles and high Center, Moffett Field, Calif ) American Institute of Aeronautics and performance aircraft It is shown how analytic means can be Astronautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala , developed establishing theoretical relationships between dynamic and Jan 16-18, 1978, Paper 78-160 15 p 20 refs static aerodynamic characteristics and how such means make it An investigation of the transonic flow over a circular arc airfoil possible to extrapolate analytically from subscale tests to full-scale was conducted to obtain basic information for turbulence modeling flight The roll of future high Reynolds number facilities in of shock-induced separated flows and to verify numerical computer establishing such 'analytic extrapolation' tools is discussed (Author) codes which are being developed to simulate such flows The investigation included the employment of a laser velocimeter to A78-20719 ,# Some applications of a test track for aero- obtain data concerning the mean velocity, the shear stress, and the dynamic testing. T A Martin and R A Deep (U S Army, turbulent kinetic energy profiles in the flowfield downstream of the Technology Laboratory, Redstone Arsenal, Ala ) American Institute airfoil midchord where the flow features are more complex of Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, Depending on the free-stream Mach number, the flowfield developed Huntsville, Ala , Jan 16-18, 1978, Paper 78-167 5p was either steady with shock-wave-induced separation extending The inability of wind tunnels to match flight conditions for from the foot of the shock wave to beyond the trailing edge or large test articles and the high cost and exact position determination unsteady with a periodic motion also undergoing shock-induced difficulties associated with flight tests has led to the use of a high separation The experimental data were compared with the results of speed track for aerodynamic testing These tests included (1) numerical simulations in which a computer code was employed that determining the ae roe I as tic response of a production wing under high solved the time dependent Reynolds' averaged compressible IMavier- conditions, (2) the aerodynamic effects due to the presence of a large Stokes equations G R plume, and more recently, (3) the flow field character m the near and far wake of a thrusting rocket The development of these testing techniques as well as test results will be discussed (Author) A78-20716 ff Experimental observations of wall interference at transonic speeds R F Starr (ARO, Inc , Propulsion Wind Tunnel Facility, Arnold Air Force Station, Tenn ) American Institute of A78-20739 * # Noise transmission into a light aircraft R Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, Vaicaitis (Columbia University, New York, N Y ) and W McDonald Huntsville, Ala , Jan 16-18, 1978, Paper 78-164 10 p 6 refs American Institute of Aeronautics and Astronautics, Aerospace Lift and downwash interferences on the high aspect ratio (AR) Sciences Meeting, 16th, Huntsville, Ala , Jan 16-18, 1978, Paper ONERA calibration configuration have been isolated from other 78-197 14 p 19 refs NASA supported research variables such as tunnel flow quality, effective Reynolds number, and An analytical study on noise transmission into a cabin of a twin model distortion under load which are present in comparative wind engine G/A aircraft is presented The solution of the governing tunnel data The lift interference on the ONERA configuration was acoustic-structural equations of motion is developed utilizing modal found to be related to the model to tunnel span ratio and is highly expansions and a Galerkin type procedure The exterior noise nonlinear in normal force at transonic speeds Fighter and lifting pressure inputs are taken from available experimental data A direct body configurations were also studied These lower aspect ratio comparison between theory and experiments on cabin noise levels is configurations (AR less than 4) were found to be much less sensitive given Interior noise reduction by stiffening, mass addition, and

160 A78-20762

damping treatments is investigated It is shown that a combination of with constant interblade phase angle in a uniform incompressible added mass and damping could significantly reduce interior noise flow The results show that the blade thickness and the mean flow levels for this aircraft (Author) incidence have significant effects on both the magnitude and phase of the lift and moment These effects are very sensitive to the A78-20743 * An investigation of strut-wall intersection interblade phase angle and become stronger with increased cascade losses T J Barber (United Technologies Corp , Pratt and Whitney stagger For bending oscillations, the effect of thickness increases the Aircraft Group, East Hartford, Conn ) American Institute of aerodynamic damping, while for torsional oscillations it mainly Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, enhances the m-phase component of the rotational moment At Huntsville, Ala . Jan 16-18, 1978, Paper 78-305 9p 14 refs constant blade loading, no definite trends of variation of the A study of the intersection losses associated with the junction of unsteady aerodynamic forces and moments can be established This a symmetric airfoil and a planar wall is reported An experimental indicates a strong coupling between the mean flow incidence and the program, conducted in a low speed air tunnel, provided detailed blade and cascade geometry (Author) wake total pressure profiles as well as surface flow visualization photographs which define the overall flow field The behavior of the A78-20757 # Reliable lifting surface solutions for unsteady intersection losses were examined for dependence on flow incidence flow P F Jordan American Institute of Aeronautics and Astro- angle and strut contour It was found that the endwall intersection nautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala , Jan 16-18, 1978, Paper 78-228 11 p 12 refs Contract No losses were strongly dependent on.the thickness of the incident F44620-73-C-0041 boundary layer, thick incident boundary layers producing markedly lower losses than very thm incident boundary layers A heuristic Numerical experimentation has shown that accurate solutions model of the flow field, which explains marked differences between obtained for suitable sets of numbers N squared of finite elements the thick and thin boundary layer results, is also presented (Author) can readily be extrapolated to the limit N tending to infinity and thus to the correct solution for a given wing A method for calculating the required accurate solutions even in the case of A78-20746 ff The flow about a slender propeller-driven unsteady flow has been developed As a sample application, the gust body in a temperature stratified fluid T F Swean. Jr (STD, Inc , load admittance function is calculated for a set of rectangular wings Washington, DC) and J A Schetz (Virginia Polytechnic Institute and, by means of further extrapolation, is presented for all reduced and State University, Blacksburg, Va) American Institute of frequencies k and for all aspect ratios in the aspect ratio range Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, between one and infinity Additional sample results presented are Huntsville, Ala, Jan 16-18, 1978, Paper 78209 Up 9 refs flutter coefficients and an admittance value for a chessboard type ARPA-supported research gust field (Author) An experimental study of the turbulent wake produced by a slender, stern-propeller-dnven body in a temperature-stratified fluid is presented The velocity and thermal boundary layers on the body A78-20759 ff Influence of nosetip shape on boundary layer upstream of the propeller are also examined The testing was transition in arc heated jets I Auerbach (Sandia Laboratories, conducted in a 6 x 6 ft subsonic wind tunnel at a Reynolds number Albuquerque, N Mex ) American Institute of Aeronautics and of about 200,000 The temperature stratification was produced by Astronautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala, upstream injection of heated air in a manner such that a uniform Jan 16-18, 1978, Paper 78-235 8 p approach velocity field was retained The temperature variation The effect of model shape on the graphite recession rate and provided a means of tracing flow development in the near-body boundary-layer transition was studied in an arc jet over the pressure region Mean flow velocities, static pressure, flow angularity and and enthalpy ranges of 099-207 MPa (98-204 atm) and mean temperature distributions are reported at specified downstream 3416-15640 J/g (1470-6730 Btu/lb), respectively Hemispheric, stations Turbulence data, including temperature fluctuations, are flat-faced, and conic cylindrical models were used It was found that reported The principal effect of the propeller was to induce a more resistance to transition occurs in the order of flat faced-conic or less rigid rotation immediately downstream of the body No hemispheric shape Evidence of this behavior is provided in terms of significant increase in mixing rate was observed in the region up until the relative ablation rates associated with each shape and the times to 4 0 body diameters downstream Temperature fluctuation is low transition The differences in resistance to transition are appreciable across the wake except in the vicinity of the propeller tips where it and suggest that reentry vehicles would benefit with respect to becomes relatively large The high temperature fluctuation often nosetip shape change by changing from the conventional hemispheric occurred in regions of low mean temperature gradients (Author) shape to a conic or, preferably, a flat-faced configuration (Author) A78-20755 ff High-frequency approximation for a nonliftmg A78 20762 * # Measurements of noise produced by flow past thin airfoil in subsonic flow A Plotkin (Maryland, University, lifting surfaces J M Kendall (California Institute of Technology, Jet College Park, Md ) American Institute of Aeronautics and Astro- Propulsion Laboratory, Physics Section, Pasadena, Calif ) American nautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala, Jan Institute of Aeronautics and Astronautics, Aerospace Sciences 16-18, 1978, Paper 78-226 5 p 10 refs Research supported by the Meeting, 16th, Huntsville, Ala , Jan 16-18 ~ 1978, Paper 78 239 12 University of Maryland p 12 refs Contract No NASM2185 The problem of high frequency subsonic potential flow past a Wind tunnel studies have been conducted to determine the thin nonliftmg airfoil is investigated The unsteadiness in the flow is specific locations of aerodynamic noise production within the flow caused by either harmonic pulsation of the airfoil surface or field about various lifting-surface configurations The models tested interaction with an upstream sinusoidal irrotational disturbance included low aspect ratio shapes intended to represent aircraft flaps, Closed-form solutions are obtained for the velocity potential and a finite aspect ratio NACA 0012 wing, and a multi element wing surface pressure distribution for wavelengths intermediate between section consisting of a main section, a leading edge flap, and dual the airfoil thickness and chord (Author) trailing edge flaps Turbulence was induced on the models by surface roughness Lift and drag were measured for the flap models Hot wire A78-20756 jj Effect of blade loading and thickness on the anemometry was used for study of the flap-model vortex roll up aerodynamics of oscillating cascades H Atassi and T J Akai (Notre Apparent noise source distributions were measured by use of a Dame, University, Notre Dame, Ind ) American Institute of Aero- directional microphone system, located outside the tunnel, which nautics and Astronautics, Aerospace Sciences Meeting, 16th, Hunts- was scanned about the flow region to be analyzed under computer ville, Ala , Jan 16-18, 1978, Paper 78-227 11 p 19 refs Grant No control These distributions exhibited a diversity of pattern, suggest- AF AFOSR-74-2675 ing that several flow processes are important to lifting-surface noise The unsteady aerodynamic forces and moments are calculated production Speculation concerning these processes is offered for highly loaded cascade blades oscillating about their mean position (Author)

161 A78-20763

A78-20763 * ff EBF noise suppression and aerodynamic penal- oscillations, introduced downstream of the shock wave, cause the ties L J McKmzie, Jr (NASA, Lewis Research Center, Cleveland, shock wave to oscillate, the case considered is that where the shock is Ohio) American Institute of Aeronautics and Astronautics, Aero- forced upstream of the throat, disappears, and then reappears as the space Sciences Meeting, 16th, Huntsville, Ala , Jan 16-18, 1978, downstream pressure first increases and then decreases The subse- Paper 78 240 13 p 15refs quent shock wave motion consists of oscillations either about the Acoustic tests were conducted at model scale to determine the throat or about the original steady flow shock position, depending noise produced in the flyover and sideline planes at reduced upon parametric relationships developed in the analysis These two separation distances between the nozzle exhaust plane and the flaps cases and the dividing case are illustrated with example calculations of an under-the-wmg (UTW) externally blown flap (EBF) configura- (Author) tion in its approach attitude Tests were also made to determine the noise suppression effectiveness of two types of passive devices which were located on the |et impingement surfaces of the configuration In A78-20771 * n Effect of wind turbulence and shear on land- addition, static aerodynamic performance data were obtained to ing performance of jet transports E F Blick, J McCarthy evaluate the penalties produced by these suppression devices (Oklahoma, University, Norman, Okla ), R R Bensch, and N R Broadband low frequency noise reductions were achieved by Sarabudla American Institute of Aeronautics and Astronautics, reducing the separation distance between the nozzle and flaps Aerospace Sciences Meeting, 16th, Huntsvil/e, Ala , Jan. 16-18, 1978, However, mid and high frequency noise was produced which Paper 78-249 10 p Contract No NAS8-31377 exceeded that of the reference configuration Two passive noise Computer simulations of a Boeing 727 class aircraft landing in suppression devices located on the flaps produced moderate to large turbulence were developed by programming the longitudinal aircraft noise reductions at reduced separation distances Consideration of equations of motion into a digital computer with various input values the static aerodynamic performance data obtained for the configure of vertical and horizontal wind speeds Turbulent wind data was fed tions tested suggests that specific broadband noise suppression to the computer in one-second intervals The computer computed in characteristics may be obtained through a trade-off with aero one-second intervals the aircraft speed, altitude, horizontal distance dynamic performance penalties by the careful selection of suppres traveled, rate-of-descent, pitch attitude, glide path angle (from edge sion devices (Author) of runway) and elevator angle All computer runs were made in the 'stick-fixed' mode The RMS values of altitude and velocity perturbations (from equilibrium) were found to be large when A78-20765 ji On some singular acoustic signatures observed horizontal wind gusts had sinusoidal components at or near the in the cockpit of a twin engined jet aircraft S M Ramachandra phugoid (long period) frequency Maximum RMS altitude deviations (Hindustan Aeronautics, Ltd , Bangalore, India) American Institute occurred when the vertical wind had sinusoidal components which of Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, were 1/10 to 1/5 of the phugoid frequency When real wind data Huntsville, Ala , Jan 16-18, 1978, Paper 78-242 7p (obtained from NCAR Queen Air) were used as input winds good An investigation was conducted concerning the origin of a noise correlations were found to exist between RMS velocity perturbations with unusual characteristics which was perceived by test pilots during and both horizontal and vertical wind shears (Author) production flight tests involving a twin-engined jet fighter aircraft The noise was characterized by the pilots as 'grinding' It was found A78-20774 * # Preliminary comparison of model and proto- in the investigation that the noise originated at the tips of compressor blades in cases in which an excessive clearance existed type wakes E Logan, Jr (Arizona State University, Tempe, Ariz ) between the rotor blade tips and the compressor casing Approaches and D W Camp (NASA, Marshall Space Flight Center, Atmospheric for ensuring the uniformity of rotor blade tip clearances are, Sciences Div , Huntsville, Ala ) American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala , therefore, needed to eliminate or alleviate the considered noise Jan 16-18, 1978, Paper 78-254 11 p 9 refs phenomena According to the physical model proposed, the noise is produced by vortices which are shed from the blade tips if an Velocity and turbulence profiles previously measured in the wake of a long building 32m high, located in the field, transverse to excessive clearance exists between the rotor blade tip and the compressor casing G R the wind and in an atmospheric boundary layer several hundred meters thick are compared with wake profiles at corresponding longitudinal stations for a scale model of the building located in a A78-20769 # A study on the mechanism of compressor large meteorological wind tunnel having a boundary layer thickness surge due to inlet pressure disturbances Y Sugiyama (Cincinnati, of 0 61 m to assess the accuracy of full scale wake profile predictions University, Cincinnati, Ohio, Japan Defense Agency, Technical based on model tests Results are presented which show that Research and Development Institute, Tokyo, Japan), A Named, and disparities in nondimensional profiles result from differences in W Tabakoff (Cincinnati, University, Cincinnati, Ohio) American relative^depth of logarithmic layers and in surface conditions Institute of Aeronautics and Astronautics, Aerospace Sciences (Author) Meeting, 16th, Huntsville, Ala , Jan 16-18, 1978, Paper 78-246 12 p 17 refs This paper presents an analysis of the mechanism of compressor A78-20781 # Future aviation turbine fuels A V Churchill, surge in a turbojet engine due to pressure disturbances at the air C L Delaney, and H R Lander (USAF, Aero Propulsion Labora- intake inlet The computational model simulating the whole engine tory, Wright-Patterson AFB, Ohio) American Institute of Aero- from the air intake to the exhaust nozzle, can predict surge hammer, nautics and Astronautics, Aerospace Sciences Meeting, 16th, Hunts- as well as compressor surge cycles The computed results show that a ville, Ala .Jan. 16-18, 1978, Paper 78-268 7p 6 refs significant correlation exists between the compressor surge and the This paper discusses an Air Force program which is being magnitude and duration of the pressure disturbances (Author) conducted to establish the properties of an aviation turbine fuel which will result in adequate fuel availability for the Air Force at an acceptable cost Results of recent processing studies on alternative A78-20770 // Large amplitude shock wave motion in two hydrocarbon sources from coal and shale oil are presented, together dimensional transonic channel flows T C Adamson, Jr, A F with combustor studies directed to determining the effects of Messiter, and M S Liou (Michigan, University, Ann Arbor, Mich ) property variations on combustor performance, durability and level American Institute of Aeronautics and Astronautics, Aerospace of harmful emissions Also, results of a recent survey are given Sciences Meeting, 16th, Huntsville, Ala, Jan 16-18, 1978, Paper showing projected increases in turbine fuel availability resulting from 78-247 9p 5 refs Contract No N0019-76 C0435 turbine fuel property changes A projection of the chemical and Two dimensional unsteady transonic channel flow with a shock physical properties of the future Air Force aviation turbine fuel is wave is considered for the slowing varying time regime Pressure presented (Author)

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A78-20782 ft Air Force research and development activities to 100 micron skin of a material exhibiting a high melting point related to aircraft fire protection B P Botten, G W Gandee. and R Experiments made at 1-g conditions on AI203 coated IN 100 test G Clodfelter (USAF, Aero Propulsion Laboratory, Wright-Patterson specimens showed that a skin giving the requisite conf igurational and AFB, Ohio) American Institute of Aeronautics and Astronautics, chemical stability could be achieved The results of these experi- Aerospace Sciences Meeting, 16th, Huntsvi/le. Ala , Jan 16-18, 1978, ments indicate that this technology is generally feasible (Author) Paper 78-269 9 p 6 refs Selected aspects of the current Air Force research and development program pertaining to aircraft fire protection are reviewed A78-20795 jj Three-dimensional hypersonic gas flow past a These include development of computerized fire and explosion thin wing (O prostranstvennom obtekann tonkogo kryla giperzvu- vulnerability assessment models development of advanced engine kovym potokom gaza) A I Golubmsku and V N Golubkm and a fuel tank fire test simulators for model refinement and (Tsentral'nyi Aerogidrodmamicneskn Institut, Zhukovskn, USSR) advanced protection techniques evaluation, development of advanced Akademna Nauk SSSft, Doklady, vol 234, June 11, 1977, p fire and explosion protection subsystems, and development of 1032 1034 8 refs In Russian non-flammable hydraulic fluid for future aircraft applications Where Formulas are derived for a low-aspect ratio thin wing at angle of appropriate, projected performance comparisons of advanced versus attack in hypersonic flow Its leeward side is in aerodynamic shadow, state-of-the-art protection techniques are included (Author) while the windward side receives the main portion of aerodynamic loading Shock layer theory, with a small parameter epsilon defined A78-20783 § Antimisting fuel kinematics related to aircraft by density ratio for a strong shock, is used to analyze flow past the crash landings A San Miguel (U S Naval Weapons Center, China windward surface Consideration is given to cases of a basic Lake, Calif ) American Institute of Aeronautics and Astronautics, 'Newtonian' flow and of a flow with conical symmetry (the formulas Aerospace Sciences Meeting, 16th, Huntsville, Ala , Jan 16-18, 1978, obtained in this latter case are analogous to those for a delta wing) Paper 78-270 8 p 12 refs U S Department of Transportation BJ Contract No FA76WA1-589 An approximate analysis is presented to quantitize kinematic behavior of antimistmg Jet A fuel in an airstream representative of A78-20802 # Use of the singular perturbation method to survivable aircraft crash landings Antimisting fuel data were gener- investigate automatic control systems (O primenenn metoda smgu- ated from a fuel expulsive airfoil placed in an airstream adjacent to a liarnykh vozmushchenn pri issledovann sistem avtomaticheskogo pulsing propane flame Measurements of burning front velocities and upravlenna) B V Viktorov (Moskovskn Aviatsionnyi Institut, accelerations were obtained from a camera located within the airfoil Moscow, USSR) Akademna Nauk SSSR, Doklady, vol 236, Sept. These data were used in the analysis to predict the diameter, shear 11,1977, p 296-299 14 refs In Russian stress, and shearing strain rate of the average particle of antimistmg The approaches of order reduction and complete splitting are fuel in the airstream under the airfoil A description is given of the applied to special cases of automatic control systems, whose partial airflow-airfoil apparatus in the context of its simulation of crash motions occur with variable intensity Consideration is given to landing conditions The feasibility of using antimisting agents to nonlinear systems, to linear systems in the absence of external suppress a fuel fire during a crash landing is evaluated (Author) excitation, and to linear systems in the presence of external excitation As an example, attention is paid to autopilot-stabilization A78-20791 ff Numerical solution for airfoils near stall in of pitch angle B J optimized boundary fitted curvilinear coordinates J K Hodge (USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, Ohio) and A L Stone (USAF, Acquisition Logistics Div .Wright-Patterson A78-20845 fi Calculation of the flow past a fuselage of AFB, Ohio) American Institute of Aeronautics and Astronautics, arbitrary configuration at low velocities (K raschetu obtekanna Aerospace Sciences Meeting, 16th, Huntsville, Ala , Jan 16-18, 1978, fiuzeliazha proizvol'noi formy pri malykh skorostiakh) L A Maslov Paper 78-284 12 p 22 refs and V P lushm TsAGI, Uchenye Zapiski, vol 7, no 1,1976, p 18 Boundary-fitted curvilinear coordinate systems are optimized In Russian for viscous flows about arbitrary airfoils at angles of attack such that Maslov (1966) has proposed a method for calculating potential boundary-layer-dependent grid systems for high Reynolds numbers flows past three-dimensional bodies of arbitrary configuration, which are generated efficiently The grid systems are utilized in implicit differs from the generally accepted method developed by Hess and finite-difference solutions Solution of a one-dimensional model Smith (1964) in that the basic integral equation is solved by a equation is compared with the theoretical solution The unsteady different method Maslov's modification provides savings in com- Navier-Stokes equations are solved for the incompressible flow puter time without impairing accuracy In the present paper, a around a cylinder and around NACA airfoils approaching stall The further improvement to the method is introduced The cylindrical predicted flows around a NACA 6412 airfoil near stall at Reynolds coordinates, which place certain constraints of the configuration of numbers of 40,000 and 200,000 are compared with the experimental the body, are replaced by a Cartesian system for defining the surface observations obtained in a smoke tunnel (Author) and by a special curvilinear system of coordinates for use in the computations Using this method with a BESM 6 computer, it proved A78-20792 ft Application of skin technology to turbine possible to solve a problem involving 1280 design points at one half blades. J Wortmann, K Schweitzer (Motoren- und Turbmen-Union of a fuselage having a vertical symmetry plane V P Munchen GmbH, Munich, West Germany), H Sprepger, and E Erben (MAN Neue Technologic, Munich, West Germany) American A78-20849 ff Approximate method of calculating the lifting Institute of Aeronautics and Astronautics, Aerospace Sciences force and the longitudinal moment of an airfoil section at low Meeting, 16th, Huntsville, Ala . Jan 16-18, 1978, Paper 78-285 11 velocities with allowance for viscosity (Pnbhzhennyi metod rascheta p 6 refs Deutsche Forschungs- und Versuchsanstalt fur Luft- und pod'emnoi sily i prodol'nogo momenta profilia s uchetom viazkosti Raumfahrt Contract No 01-QV-276-ZK-SNA-SLN pri malykh skorostiakh) M A Brutian and la M Serebniskn The paper presents a technological process which makes it TsAGI, Uchenye Zapiski, vol 7, no 1, 1976, p 3339 5 refs In possible to improve blade materials at zero gravity conditions at a Russian minimum of expenditure of energy and material By this process the properties of blades manufactured conventionally at 1-g conditions with cooling air holes or without are improved by remelting and A78 20850 ff Turbulent boundary layer on a moving surface controlled solidification at zero gravity conditions To preserve the (Turbulentnyi pogramchnyi slot na podvizhnoi poverkhnosti) A S shape of the blades in the gravity process the deformative surface Gmevskn, G N Emal'ianova, and A V Kolesmkov TsAGI, Uchenye tensions arising in the melting operation are contained by a thin, 10 Zapiski, vol 7, no 1, 1976, p 40-50 13 refs In Russian

163 A78-20857

An integral and a numerical method are proposed for calculating also the intervals between replacements are determined A strong the turbulent boundary layer on a moving surface (flap) in the dependence of the effectiveness of the system on the dispersion of presence of a longitudinal pressure gradient under conditions of the operating time of the parts is noted P T H monotonic velocity profiles The integral method is a modification of Fediaevskfi's et al (1973) integral method (for calculating turbulent A78-20880 ff Taking structural and technological constraints boundary layers in an incompressible fluid) to include an airfoil into account in the design of maximum-stiffness load bearing moving faster or slower than the oncoming flow The numerical structures (Ob uchete konstruktivnykh i tekhnologicheskikh ogram- method employs a more complex eddy viscosity model in which chenii pri proektirovann silovykh konstruktsn maksimal'noi zhest- allowance is made for mtermittence at the external side of the kosti) E K Lipm TsAGI, Uchenye Zapiski, vol 7, no 2, 1976, p boundary layer and for the interaction of molar and molecular V 105-113 6 refs In Russian effects at the internal side of the boundary layer "\ \V P The paper gives a formulation and solution of the problem of \ ^ optimizing a complex structure using the condition of minimum A78-20857 ;;' Calculation of the flow of a rarefied gas past c strain energy and satisfying strength and stiffness requirements in the plate of infinite span (Raschet obtekanna plastmy beskonechnogo presence of structural and technological constraints The problem is razmakha potokom razrezhennogo gaza) A I Erofeev and V A formulated as one of classical vanational calculus with conditional Perepukhov TsAGI, Uchenye Zapiski, vol 7, no 1, 1976, p extremum The inequalities expressing the constraints on the 102 106 13 refs In Russian magnitudes of the geometric parameters are replaced by equalities by The Monte Carlo method is applied to the calculation of the the method of Valentine P T H aerodynamic characteristics of a plate of infinite span situated at an angle of attack in a low-density hypersonic flow The influence of A78-20881 it Rational parameters of reinforced panels oper- the plate temperature, the molecular interaction law, and the internal ating under conditions of unsteady heating (O ratsional'nykh molecular degrees of freedom on the aerodynamic characteristics is parametrakh podkreplennykh panelei, rabotaiushchikh v uslovnakh evaluated Calculations are carried out for Mach numbers of 5 and nestatsionarnogo nagreva) S N Ivanov TsAGI, Uchenye Zapiski, 10 It is shown that allowance for internal degrees of freedom leads vol 7, no 2, 1976, p 114120 6 refs In Russian to a better agreement with the experiment V P A formulation and method of solution are given for the problem of selecting rational parameters of reinforced panels operating under conditions of intense aerodynamic heating The panels are subjected A78-20864 ff Solving the problem of numerical construction to time varying transverse loads which do not depend on the of a model of similar rigidity to the initial structure as a problem of coordinates, a longitudinal load, and bending moments at the ends A quadratic programming (Reshenie zadachi o chislennom postroenn panel is also subjected to unsteady aerodynamic heating The modeh, podobnoi po zhestkosti iskhodnoi konstruktsn, kak zadachi temperature field is computed numerically, and the stress field of the kvadratichnogo programmirovantia) V A Tranovich and lu F strut is calculated with the aid of the hypothesis of plane sections laremchuk TsAGI, Uchenye Zapiski, vol 7, no 1,1976, p 147-151 The problem is solved by nonlinear programming methods, in In Russian particular, the method of penalty functions As an example, the parameters of a steel panel of a heat shield reinforced by stringers are computed P T H A78-20866 jj Application of the finite element method to the stability analysis of triangular plates in supersonic flow (Prime nenie metoda konechnykh elementov dha issledovanna ustoichivosti A78-20882 # Taking into account the effect of elasticity of treugol'nykh plastin v sverkhzvukovom potoke) V A Vysloukh, V the structure on the longitudinal short-period motion of an aircraft P Kandidov, and S S Chesnokov TsAGI, Uchenye Zapiski, vol 7, (Ob uchete vlnaniia uprugosti konstruktsn na prodol'noe korotko- no 1,1976, p 160-164 8 refs In Russian penodicheskoe dvizheme samoleta) lu A Kublm and V I Chubarov TsAGI, Uchenye Zapiski, vol 7, no 2, 1976, p 121-130 In Russian A78-20867 // A formulation of the problem of the mini- A method of estimating the effect of elastic strains on the mum-drag wing (Ob odnoi postanovke zadachi o kryle mmimal'nogo longitudinal short period motion of an aircraft is proposed From the soprotivlenna) M N Kogan and V D Permmov TsAGI, Uchenye general equations for the elastic vibrations of an aircraft, a truncated Zapiski, vol 7, no 2, 1976, p 1 7 In Russian system of equations is obtained, describing with sufficient accuracy A vanational problem is formulated and solved for determining for engineering purposes the dynamics of short-period motion the profile of minimum drag in supersonic and hypersonic flow Redistribution of aerodynamic forces due to elasticity of the under the conditions that the distribution of the given lift along the structure is accounted for in the truncated system by corrections to profile is such that for each profile element it is equal to the weight the lift coefficient and the longitudinal moment coefficient Elastic of the profile element For both the supersonic and hypersonic case, strains are determined by the Ritz vanational method PTH this additional condition is shown to lead to a certain increase in drag and a change in the shape of the optimal profile However, it also leads to a reduction in the weight of the wing structure P T H A78-20883 # Approximate method of calculating subsonic compressible flows past a lifting wing profile (Pnbhzhennyi metod rascheta dozvukovykh szhimaemykh techenn okolo nesushchego krylovogo profilia) A A Shagaev TsAGI, Uchenye Zapiski, vol 7, A78-20879 H Optimum schedule for replacement of aircraft no 2, 1976, p 131-135 9 refs In Russian system parts under incomplete information on their reliability (Optimal'noe raspisame zamen elementov sistem samoleta pn nepol- A78-20886 # Interaction of a shock wave with an entropy noi mformatsn ob ikh nadezhnosti) R F Avramchenko TsAGI, layer (Vzaimodeistvie udarnoi volny s entropiinym sloem) A N Uchenye Zapiski, vol 7, no 2, 1976, p 95-104 In Russian Mmailos TsAGI, Uchenye Zapiski, vol 7, no 2, 1976, p 149-153 6 A schedule for part replacement is defined, which ensures a refs In Russian maximum guaranteed mean time of uninterrupted service life of an A straight through finite-difference scheme was used to study aircraft system The reliability of each element is characterized by a the interaction of a shock wave with a flat high-entropy jet both in mean operating time and its dispersion An analytic solution of the the free supersonic flow and in the flow at the body surface Several corresponding minimax problem is constructed by a method based cases are analyzed, and situations characterized by direct reflection on Pontnagm's maximum principle For each act of replacement, the of a wave are examined The advantages and limitations of the optimal time interval in which a replacement should be made and straight-through finite difference scheme are discussed M L

164 A78-20917

A78-20889 H Pressure distribution over sharp-nosed cones resistance appears at the interface Adapted to a digital computer, situated at angles of attack from 0 to 10 degrees in supersonic flow the method provides substantial time savings as compared to (Raspredelenie daylenua na ostrykh konusakh pri uglakh ataki alpha programs based on an explicit scheme V P = 0-10 deg v sverkhzvukovom potoke) P G Leutin TsAGI, Uchenye Zapiski, vol 7, no 2, 1976, p 163-166 8 refs In Russian An empirical method is proposed for determining the pressure A78-20905 # Velocity profiles in the Laval nozzle throat for distribution over cones with half-angles ranging from 10 to 30 uniform compressible swirling flow (Profili skorostei v minimarnom degrees, situated at incidence in supersonic flow The method is secherm sopla Lav all a pn odnorodnom vmtovom techenu gaza) N based on the use of a similarity rule for sharp-nosed cones at zero N Slavianov TsAGI, Uchenye Zapiski, vol 7, no 3, 1976, p 91 96 incidence in combination with a pressure coefficient that varies 10 refs In Russian linearly with the angle of attack in the mend lonal plane V P In the present paper, a special case of Laval-nozzle flow - a uniform swirling flow in which the radial velocity component and its A78-20895 ti Calculation of the mean flow characteristics at derivative are negligible along the flow • is analyzed The axial and the inlet to the air intake located under a delta wing (Raschet circumferential velocity profiles in the nozzle throat are calculated, osrednennykh kharaktenstik potoka na vkhode vozdukhozabormka, along with the threshold values of swirl intensity, at which separated ustanovlennogo pod treugol'nym krylom) A P Bazzhin and I M and reciprocating circulation zones do not arise in the flow core The Fihmonov TsAGI, Uchenye Zapiski, vol 7, no 3, 1976, p 10-17 In analysis indicates that swirl induced phenomena are more distinct in Russian gases having large specific heat ratios V P The paper presents calculated values for the mean Mach number, the contraction ratio, the full pressure recovery coefficient, and the A78-20906 8 Inviscid supersonic flow about a thin rectangu- downwash and upwash averaged for flow at the inlet to the air intake lar plate (Neviazkoe sverkhzvukovoe techeme u tonkoi located under an 80 deg delta wing for free stream Mach numbers pnamougol'noi plastiny) A N Mmatlos TsAGI, Uchenye Zapiski, from 3 to 6 and attack angles from 0 to 10 deg Flow around the vol 7, no 3, 1976, p 97-102 6 refs In Russian wing with separation at the leading edge is examined The depen- In the present paper, a modified Lax-Wendroff scheme is applied dence of the parameters on the position of the air intake inlet plane to the calculation of the flow pattern about a rectangular plate is studied M L situated at an angle of attack of 30 degrees in a supersonic flow A solution is obtained, neglecting flow separation from the lateral edges The flow pattern (shock waves and vortices) are plotted A78-20900 /? The basic characteristics of the variation of against the angle of attack at a freestream Mach number of 5 The aerodynamic parameters in the transition region at hypersonic flow pressure distribution over the upper and lower plate (wing) surfaces velocities (Osnovnye zakonomernosti izmenenna aerodmamicheskikh is diagrammed VP kharaktenstik v perekhodnoi oblasti pri giperzvukovykh skorostiakh potoka) V N Gusev, T V Khmova, and V V Riabov TsAGI, Uchenye Zapiski. vol 7, no 3, 1976, p 47 54 13 refs In Russian A78-20913 ft Rearrangement of the flow between a pair of The paper reports an experimental study of aerodynamic bodies, one of which is situated in the other's wake, in supersonic parameters at hypersonic flow velocities The aerodynamic param- flow (Perestroika techeniia mezhdu paroi tel, odno iz kotorykh eters of bodies of simple form in the transition region between the raspolozheno v slede drugogo, pri sverkhzvukovom obtekami) V S region of free molecular flow and the region where the gas flow is Khlebmkov TsAGI, Uchenye Zapiski, vol 7, no 3, 1976, p like a continuum were investigated The basic characteristics of the 133-136 7 refs In Russian variation of these parameters during the change of basic similarity The critical spacing between two bodies situated one behind the criteria are analyzed and discussed M L other is understood to mean the spacing at which the common separation zone of the two bodies breaks down In the present paper, a relationship between the critical spacing and a certain correlation parameter is derived The relationship can be used to determine the A78-20902 # Approximate wind-tunnel simulation of the spacing (between two bodies in supersonic flow) at which a dynamics of a system composed of a body with a trailing cable rearrangement of the flow structure between the bodies will set in (Priblizhennoe modelirovame dinamiki sistemy tros-telo v aero- VP dinamicheskoi trube) V I Valiaev TsAGI, UchenyeZapiski, vol 7, no 3, 1976, p 65-71 In Russian In the present paper, a criterion is derived for simulating, in a A78-20915 ft Simulation of the flight conditions in the subsonic wind tunnel, the dynamic instability of trailing cable with ionosphere (K voprosu o rnodelirovanu uslovn poleta v lonosfere) B an end load in incompressible flow The criterion is obtained from an E Zhestkov, A la Kmvel', and A I Omelik TsAGI, Uchenye analysis of equations of perturbed motion and the corresponding Zapiski, vol 7, no 3, 1976, p 142-147 12 refs In Russian boundary conditions, derived in a simplified two-dimensional formu- The plasma component in a weakly-ionized hypersonic free lation The mathematical model is seen to describe the essential molecule nitrogen stream is analyzed The analysis leads to a probe features of the phenomenon, while the necessary corrections, design that is suitable for analyzing the ion and electron components resulting from the influence of neglected factors, can be determined in the presence of a neutral gas in the plasma, even when the neutral in the course of the experiment V P gas intensity exceeds that of the plasma component by several orders of magnitude A flow with a plasma component is shown to provide satisfactory simulation of the forces acting on a vehicle orbiting in A78-20903 H Economical method for calculating unsteady the ionosphere V P temperature fields in thin-walled aircraft structures (Ekonomichnyi metod rascheta nestatsionarnykh temperaturnykh polei v ton- kostennykh aviatsionnykh konstruktsnakh) G N Zamula and S N A78-20917 H Determination of the stress-strain state in the Ivanov TsAGI, Uchenye Zapiski, vol 7, no 3, 1976. p 72 79 5 refs end region of a stress-raiser rib (Otsenka napnazhennogo sostoianna v In FUiss^an kontsevoi zone prervannogo strmgera) E K Lipm and V M Frolov The numerical engineering method proposed in the present TsAGI, Uchenye Zapiski, vol 7, no 3, 1976, p 152-155 In Russian paper for calculating unsteady temperature fields in plane sections of The problem of the stress-strain state of a stress raiser rib does thin-walled aircraft structures is based on the use of the implicit not possess an exact solution In the present paper, the stress-strain scheme of the balance method in combination with difference state is determined by approximating the representation of the stress factorization The method can be extended to systems containing function in the form of the product of two functions obtained from two layer struts connected laterally in such a way that a thermal the condition of minimum complementary strain energy V P

165 A78-20918

A78-20918 ff Upgrading the carrying capacity of stretched The integral relation method is used to obtain a numerical panels with a stress-raiser rib by the technique of strain-compensating solution for the problem of the supersonic flow of an mviscid holes (Povyshenie nesushchei sposobnosti rastianutykh panelei s nonheat conducting gas past the under surface of a delta wing Angle prervannym strmgerom metodom razgruzhaiushchikh otverstn) A of attack varied in the range 30-60 deg and freestream Mach number N Kulikov, V F Kut'mov, S K Kusheverskn, and I N Panchenko varied in the range 4-10 Two new correlation dependencies were TsAGI, Uchenye Zapiski, vol 7, no 3, 1976, p 156 159 In Russian obtained as a result of the numerical solution for the transverse velocity gradient at the symmetry axis of the wing and for shock wave detachment from the wing in the symmetry plane B J A78-20920 ff The effect of blunting the leading edge of a delta wing on its aerodynamic characteristics during supersonic flight (Vliiame skruglenna perednei kromki treugol'nogo kryla na ego A78-20949 H Effect of the thickness of profile and trailing edge on the flow field and the aerodynamic characteristics of a aerodynamicheskie kharaktenstiki pri sverkhzvukovykh skorostiakh low-aspect-ratio delta wing at M = 3 (Vlnanie tolshchmy profilia i poleta) V V Keldysh and R I Shtemberg TsAGI, Uchenye zadnei kromki na pole techenna i aerodmamicheskie kharaktenstiki Zapiski, vol 7, no 4, 1976, p 1-8 5 refs In Russian treugol'nogo kryla malogo udlinenna pri chisle M-3) A N Mmailos Wind tunnel tests were performed to study the effect of TsAGI, Uchenye Zapiski, vol 7, no 5, 1976, p 9 14 In Russian blunting the subsonic leading edge of a delta wing on the aerodynamic characteristics of the wing in transonic and supersonic flow Models of delta wings with blunt and with sharp leading edges were tested and it was determined that a blunt subsonic leading edge A78-20951 ff Flow visualization in the region of intersection for a blunting radius to thickness ratio of not greater than 0 25 does of aerodynamic surfaces (Vizual'noe issledovame kartmy techenna v not necessarily lead to a reduction in the lift-drag ratio of the wing oblasti peresechemia aerodmamicheskikh poverkhnostei) A G For a supersonic blunt leading edge, increasing its sweep angle from Ereza and E Kh Orlovskaia TsAGI, Uchenye Zapiski, vol 7, no 5, 60 to 80 deg is accompanied by a considerable increase in maximum 1976, p 2631 In Russian lift-drag ratio B J The paper presents wind tunnel results on the visualization of boundary layer flow in the region of intersection of aerodynamic surfaces in the transonic range (M = 0 6-0 9) and at high Reynolds A78-20921 si Supersonic flow near a thin trapezoidal wing (Sverkhzvukovoe techeme u tonkogo trapetsievidnogo kryla) A N numbers (about 13 x 10 to the 6th) The following variants of Mmailos TsAGI, Uchenye Zap/ski, vol 7, no 4, 1976, p 9-17 5 connection of the half-profile tested with the wind tunnel wall were refs In Russian considered (1) the connection slit was totally eliminated and the A numerical method developed by Mmailos (1976) is used to interface radius was about 2 mm, (2) the slit was totally eliminated study the steady supersonic conical flow past a thin trapezoidal wing, and the interface radius was 10 mm, (3) the slit was not eliminated, with a lateral-edge sweep angle varying from 45 to 90 deg The and (4) the slit was eliminated beneath the panel for the whole analysis, based on the use of isosurfaces, is applied to the length of the wind tunnel wall, and there was through flow in the investigation of flow profiles for cases of shock waves attached to interface Oil film pictures of the flow lead to the conclusion that the and detached from the lateral edge Results are presented for a boundary layer flow in the presence of a positive pressure gradient is freestream Mach number of 5 and an angle of attack range of 5-25 sensitive to connection interface conditions as well as to through deg BJ flow in the interface B J A78-20953 ff Characteristics of the jet acceleration of a flow to hypersonic speeds (Osobennosti strumogo razgona potoka do A78-20930 ff Use of the polynomial method to calculate the giperzvukovykh skorostei) V N Gusevandlu V Nikol'skn TsAGI, parameters of the stabilized maneuver of an elastic aircraft (Prime- Uchenye Zapiski, vol 7, no 5, 1976, p 44-52 6 refs In Russian nenie metoda mnogochlenov k raschetu parametrov ustanovivshe- The theory of jet acceleration to hypersonic speeds, involving gosia manevra uprugogo samoleta) G A Amir'iants and V G pressure recovery and the generation of a shock wave system Bun'kov TsAGI, Uchenye Zapiski. vol 7, no 4, 1976, p 88-94 In (hanging, reflected and Mach disk) in an mviscid supersonic Russian underexpanded flow in a duct, is reviewed Consideration is given to An algorithm is developed making it possible to extend the the degree of nonumformity of the flow field in the axial region of a polynomial method to the computation of some of the aerodynamic strongly underexpanded jet, along with methods for reducing this characteristics of an elastic aircraft, performing a stabilized maneu- nonumformity The flow of a strongly underexpanded jet in a duct ver The aeroelastic flutter analysis is performed on the basis of with sudden expansion is examined in the framework of employing stiffness, mertial and aerodynamic matrices Universal expressions are jet acceleration in wind tunnel experiments B J obtained for deformations of the aircraft and for rudder performance for cases of lateral and longitudinal maneuver B J A78-20966 ;: Hypersonic gas flow past a flat delta wing (Obtekame ploskogo treugol'nogo kryla giperzvukovym potokom gaza) V N Golubkm TsAGI, Uchenye Zapiski, vol 7, no 6,1976, A78-20932 # Use of a fast Fourier transformation and the p 1-10 11 refs In Russian Monte Carlo method to calculate repeatibility of load and fatigue The attached hypersonic flow at incidence past a flat small damage of aircraft structural elements under vibration excited by aspect-ratio delta wing is analyzed, and a method of solving the external stationary random loads (Primenenie bystrogo preobra- direct problem is proposed The method is based on the assumption zovanna Fur'e i metoda Monte Karlo dlia rascheta povtonaemosti that a portion of the wing m the region of the symmetry plane is a nagruzok i ustalostnogo povrezhdenna elementov aviatsionnykh conical stream surface, and that the stream function varies along this konstruktsn pn kolebannakh ot statsionarnoi sluchamoi vneshnei surface It is shown that using this assumption and two solutions of nagruzki) G V Vronskn TsAGI, Uchenye Zapiski, vol 7, no 4, the equation describing the shape of the shock, it is possible to 1976, p 102110 12 refs In Russian, construct a compression shock that transfers continuously from a rectilinear to a curvilinear shock V P

A78-20933 ff Two new correlation dependencies for param A78-20970 ff Calculation of the Laval-nozzle flow by a eters of flow on a plane delta wing (Dve novye korreliatsionnye modified Lax Wendroff method of second-order accuracy (Raschet zavisimosti dlia parametrov techenua na ploskom treugol'nom kryle) techenna v sople Lavalia metodom ustanovlenua vtorogo ponadka A P Bazzhm TsAGI, Uchenye Zapiski, vol 7, no 4, 1976, p tochnosti) A P Wlazurov TsAGI, Uchenye Zapiski, vol 7, no 6, 111-114 5 refs In Russian 1976, p 35-40 9 refs In Russian

166 A78 21090

The mixed inviscid nonheat conducting gas flow in a two Nov 10-12, 1976) Journal of Geophysical Research, vol 82, Dec dimensional symmetrical Laval nozzle with a low-radius-of-curvature 20, 1977, p 5833-5866 31 refs FAA-supported research throat is analyzed The flow fields and flow coefficients are The effect of aircraft flight altitude on atmospheric ozone has calculated by a modified Lax-Wendroff method, using Mac Cor- been studied by using N0(x) emitted from hypothetical fleets mack's finite-difference scheme Flow coefficients obtained for operating individually in an altitude range between 10 8 and 18 km convergence and divergence angles of 30 and 15 degrees, respectively, The study is based on the use of an empirical two-dimensional (2-D) and for throat radii of curvature of 035, 055, 075, and 1 00 are photochemical model of the troposphere and stratosphere An found to correlate well with computations by the method of important characteristic of this model is the incorporation of the asymptotic expansions, and to compare satisfactorily with experi methane oxidation reactions, which produce ozone in the tropo- mental data V P spherp and lowest stratosphere The 2-D model reproduces several characteristics of the latitudinal and seasonal variations in ozone and other species Other characteristics of the model are (1) the numerical simulation of water vapor data in the natural troposphere and stratosphere and (2) the inclusion of Rayleigh scattering for A78-20971 a Construction of a mathematical model of a jet wavelengths longer than 300 nm in the determination of photo- engine for analyzing transient flows (K postroennu matematicheskoi dissociation rates Results are presented in terms of ozone column modeli silovoi ustanovki VRD dlia issledovanua nestatsionarnykh changes as a function of latitude and season for the assumed (not rezhimov) V T Grin' TsAGI, Uchenye Zapiski, vol 7, no 6,1976, forecast) N0(x) injection rates for each fleet In general, the results P 41-49 11 refs In Russian show (1) a small (less than 1%) enhancement in the ozone column A complete system of equations describing two-dimensional due to the methane oxidation reactions in regions of heavy traffic for transient flows of an ideal gas is used as a basis to construct a injections at 10 8 km, (2) almost no effect on the ozone column for mathematical jet-engine model, including an air intake, a compressor, injections at 14 5 km, and (3) a decrease in the ozone column due to a combustion chamber, a nozzle, and control elements The model the N0(x) catalytic cycle for SST injections at 18 km (Author) describes the transient phase of engine operation, the duration of which is defined by the flow dynamics The model can be used to analyze dynamic processes and to gam insight into air intake/compressor interaction For illustration, it is applied to the analysis of a transient process arising from the interaction between a temperature wave and the steady supersonic flow at air-intake inlet section V P A78-21020 a Lateral stability of a light aircraft during' landing (Statecznosc boczna w czasie dobiegu ladujacego samolotu sportowego) Z Goraj, J Marymak, Z Paturski, and M Zlocka (Warszawa, Pohtechmka, Warsaw, Poland) Mechamka Teoretyczna i Stosowana, vol 15, no 4, 1977, p 501516 20 refs In Polish A78-20973 # Determination of airfoil lift from pressure A five-degree-of-freedom model of a light aircraft running along measurement at the test section walls in a subsonic wind-tunnel the ground after landing is proposed Unsteady lateral forces acting (Opredeleme pod'emnoi sily profilia po izmerennu davlenn na on the tires are modeled as linear functions of sideslip, camber angle, stenkakh rabochei chasti dozvukovoi aerodmamicheskoi truby) V S and steady aerodynamic forces The equations of motion are derived Gavnsev, V M Gadetskn, and A S Mozol'kov TsAGI, Uchenye with the aid of the Boltzmann-Hamel equations for holonomic Zapiski, vol 7, no 6, 1976, p 57 62 In Russian systems The dominating influence of two forms of natural vibration The theory of a method for measuring the lift of an airfoil is revealed high-frequency snaking of the aircraft nose section and section is outlined Measurements are made in a subsonic rectangular low-frequency yaw P T H closed throat wind tunnel, the lift being determined with a pneumat- ic integrator from the mean value of the static pressure at the top and bottom walls of the test section A single manometer reading is sufficient for determining the lift of an airfoil section in the case of attached flow V P A78-21084 Effect of a conical break of delta-wings on the aerodynamic characteristics A L Conor, V V Kravets, and A I Shvets (Akademna Nauk SSSR, Izvestua, Mekhanika Zhidkosti i Gaza, Nov-Dec 1976, p 100-104) Fluid Dynamics, vol 11, no 6, July 1977, p 904-908 1 leafs Translation A78-20984 # Rational arrangement of the structural and The paper reports the results of experimental investigations of load-bearing elements of the wing with allowance for certain the aerodynamical coefficients and pressure on the windward side of aerodynamic requirements (O ratsional'noi konstruktivno-silovoi delta wings with a conical break A comparison was also made komponovke kryla s uchetom nekotorykh aerodmamicheskikh tre- between the aerodynamic quality parameters of delta wings with bovanu) V I BinukandV M Frolov TsAGI, Uchenye Zapiski, vol conical break and of wing-cone models with caret-shaped symmetric 7, no 6, 1976, p 134-138 In Russian arrangement at a Mach number of 5 96 P T H It is shown that the effect of reduced torsional wing strain for transverse loads and corresponding aerodynamic conditions can be obtained not only by increasing the general rigidity of the structure but by a choice of a rational scheme of structural and load-bearing A78-21090 Experimental investigation of the charac- elements The procedure for obtaining this rational arrangement teristics of small-sized nozzles V A Butenko, lu P Rylov, and V P involves use of a parameter which characterizes the static stability for Chikov (Akademna Nauk SSSR, Izvestua, Mekhanika Zhidkosti i wing strain in air flow ML Gaza, Nov-Dec 1976, p 137-140 ) Fluid Dynamics, vol 11, no 6, July 1977, p 936-939 7 refs Translation The momentum and discn

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A78-21093 Effect of nozzle shape on characteristics of symmetric and unsymmetric trapezoids Results obtained by the three-dimensional subsonic and supersonic flows V M Dvoretskn method are shown to be m close agreement with an exact solution lAkademna Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza, obtained by Timoshenko and Womowsky Krieger V P Nov-Dec 1976, p 147-151 ) Fluid Dynamics, vol 11, no 6, July 1977, p 948-952 lOrefs Translation _ The characteristics of three dimensional subsonic and supersonic flows of an inviscid and nonheat-conductmg gas in nozzles of A78-21219 # Perturbing forces in the hydrodynamic interac- complex shape were analyzed The investigation was based on tion of thin-blade cascades m a potential flow (Vozbuzhdamshchie numerical integration of a system of gas dynamics equations with the sily pn gidrodmamicheskom vzaimodeistvn reshetok tonkikh profilei aid of monotonic finite difference schemes of first-order accuracy v potentsial'nom potoke) V E Saren and V A ludm Problemy Flow in the whole nozzle channel, including subsonic and supersonic Prochnosti, Sept 1977, p 104-109 In Russian regions, was computed, and the results show how a suitable choice of The paper deals with the theoretical determination of the nozzle profile shape can affect the distribution of the nonumformity perturbing forces generated by the interaction of two blade rings in a characteristics of the flow P T H potential incompressible flow (quasi-stationary formulation ot the problem) The results of the present analysis make it possible to determine some characteristic properties of the perturbing forces For illustration, the relative level of the perturbing forces is A78-21098 Computation of the base pressure in ejector calculated for the hydrodynamic interaction of neighboring blade nozzles of different length with zero coefficient of ejection N L rings in an axial-flow compressor V P Efremov and R K Tagirov (Akademna Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza, Nov Dec 1976, p 164 166 ) Fluid Dynamics, vol 11, no 6, July 1977, p 966-968 Translation A78-21374 H Elastic deformations of rapidly-rotating prismatic mirrors (Uprugie iskazhenna bystrovrashchaiushchikhsia priz- maticheskikh zerkal) V S Trachuk (Vsesoiuznyi Nauchno Issledovatel'skn Institut Optiko-Fizicheskikh Izmerenn, Moscow, USSR) Zhurnal Nauchnoi i Prikladnoi Fotograf/i i Kmematografn, A78-21132 Entropy layer in two-dimensional flows IM E vol 22, Sept Oct 1977, p 335-342 8 refs In Russian Ermolin (PMTF - Zhurnal Prikladnoi Mekhaniki i Tekhnicheskoi The article discusses the elastic deformations of rapidly-rotating Fiziki, Nov Dec 1976, p 38 48) Journal of Applied Mechanics and prismatic mirrors often used in photorecordmg instruments Equa- Technical Physics, vol 17, no 6, July 1977, p 779-787 10 refs tions are developed for calculating such deformation, noting the Translation influence of rotor parameters and the material characteristics of the Steady plane and ax (symmetric hypersonic flows of a perfect gas mirror surfaces It is shown that the most effective mirror optimiza- behind a shock wave are analyzed, assuming that the angle between tion, yielding minimal deformation, is achieved by consideration of the shock wave and the velocity vector of the uniform oncoming the mirror configuration and the magnitude of the Poisson coeffi- flow is small everywhere with the exception of a small region at the cient of the mirror material The optimization of 6, 7, and 8 sided apex of the body. A solution beyond this region is obtained, by the mirrors is discussed with regard to their manufacture on the basis of method of matched asymptotic expansions, for a shock whose widely used construction materials S C S generatrix vanes according to a (near) power law at the apex The asymptotic solution obtained yields an implicit relationship between steady two-dimensional gas flows with entropy layer and unsteady one-dimensional flows V P A78-21632 ff An experimental study of three-dimensional characteristics of propeller wakes under stalling conditions D Favier, J Rebont (CNRS, Paris, France), and C Maresca (CNRS, Paris, Aix-Marseille I, Universite, Marseille, France) ASME, Trans- A78-21133 Semiempirical theory of the generation of actions, Series I • Journal of Fluids Engineering, vol 99, Dec 1977, discrete tones by a supersonic underexpanded jet flowing over an p 745-752 18 refs obstacle V N Glaznev and V S Demm (PMTF - Zhurnal The three-dimensional flow field of a four-bladed propeller wake Prikladnoi Mekhaniki i Tekhnicheskoi Fiziki, Nov-Dec 1976, p has been investigated by use of an anemometnc hot film technique 49-55 ) Journal of Applied Mechanics and Technical Physics, vol 17, The paper does not deal with the measuring procedure, which has no 6, July 1977, p 787-793 18 refs Translation been previously described by the authors, but describes the results An elementary theory of the mechanism of the Hartmann air let obtained for the three-dimensional wake To gain insight into the generator is proposed It is assumed that oscillations develop in a process by which local blade stalling influences the wake structure, one-dimensional resonant cavity in the form of a subsonic flow four advance ratios have been investigated The two lower values of between a Mach disk and a wall The acoustic waves emitted from the advance ratio correspond to a local blade stalling which first the cavity, having reached the nozzle exit section, generate distur- affects the blade tip and grows towards the hub with decreasing bances at the jet boundary These disturbances grow during values of the advance ratio The resultant velocity profiles of u, v, w propagation downstream and are damped at the wall The pressure in the azimuthal direction are investigated and compared at different pulse thus generated at the wall will lead to self-oscillations if the advance ratios and at various radii These experimental results reveal pulse is strong enough and is phase correlated with the cavity that a local flow separation has considerable influence on the three oscillations V P velocity components It is concluded that for an advance ratio with rotor stalling, the flow separation increases the rotational wake speed effect generated by an increasing tangential component u The radial flow diminishes as shown by the v velocity profiles A sharp A78-21205 % Stress-strain state of simply-supported three- thickening of the blade wake is also observed from the axial layer trapezoidal plates (Napnazhenno deformirovannoe sostoianie component w (Author) svobodno opertykh trekhslomykh trapetsievidnykh plastm) A V Vestiak and E A Khvilon (Moskovskn Aviatsionnyi Institut, Moscow, USSR) Problemy Prochnosti, Sept 1977, p 37-41 5 refs In Russian A78-21635 jf A method for the construction of flow nozzles An approximate method is proposed for calculating the stress- and wind tunnel contraction sections R Eichhorn (Kentucky, strain state of thin elastic three-layer trapezoidal plates subjected to a University, Lexington, Ky ) and T S Fox (Institute of Paper uniformly distributed transverse load The method is applicable to Chemistry, Appleton, Wis ) ASME, Transactions, Series I - Journal

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of Fluids Engineering, vol 99, Dec 1977, p 772-774 5 refs NSF Propagation, vol AP-26, Jan 1978, p 64-76 35 refs USAF- Grant No GK-15251 supported research A method is described for forming a flow nozzle whose cross The external coupling of nuclear EMP to metal aircraft and section varies smoothly from one shape to another The flow passage missile structures is discussed, with particular attention given to the consists of fiber glass cloth saturated with epoxy resin cast in place cases of the EC-135 and the B 1 aircraft Experimental data for the about an elastic water filled rubber diaphragm An example of such a skin current and charge densities induced on the two types of aircraft nozzle, with a circular inlet section and a rectangular exit section was are presented, the experiments involve continuous wave testing and constructed and incorporated in a wind-tunnel design The flow the construction of the response to the nuclear EMP through use of distribution, excluding the exit boundary layer, is uniform to within Fourier frequency superposition The experimental results are 0 5 percent The exit boundary layer is laminar and steady and the compared with numerical calculations developed on the basis of discharge coefficient is 0 989 (Author) aircraft models formed by bodies of revolution or intersecting sections of wires J M B A78-21838 Design to cost/life cycle costing, Proceedings A78-21990 Surface current and charge density induced on of the Conference, Washington, D C, November 76-18, 1977 aircraft Y M Hwang (Ford Aerospace and Communication Corp , Conference sponsored by the American Institute of Industrial Palo Alto, Calif ), L Peters, Jr, and W D Burnside (Ohio State Engineers Edited by D T Newman (Management Education Corp , University, Columbus, Ohio) IEEE Transactions on Antennas and Santa Monica, Calif ) Santa Monica, Calif, Management Education Propagation, vol AP-26, Jan 1978, p 77-81 13 refs Corp, 1977 845 p $50 The usefulness of the geometrical theory of diffraction (GTD) in Government and industry experience in the management of computing the surface current and charge density induced on aircraft acquisition programs is discussed, with particular attention given to is illustrated This is a high-frequency solution for an arbitrary the impact of life cycle costing on design to cost principles The incident plane wave and fuselage observation points A pattern is recent Office of Management and Budget directive on systems presented for an arbitrary incident plane wave as well as a series of acquisition, design to cost guidelines of federal agencies, source frequency and time domain plots for roll plane incidence A selection directives and parametric cost modeling figure in the 3-dimensional pattern is presented for plane wave incidence (as a discussions In addition, tracking of performance versus goals, the function of incidence angle) as well as examples of roll plane results trade-off process and cost reduction procedures are considered Case in both the frequency and time domain (Author) studies involve such problems as development of solar power systems for military bases, and avionics subsvstem development J M B A78-21992 EMP response of aircraft antennas. K S H Lee, L Mann (Dikewood Corp , Los Angeles, Calif), and T K Liu A78-21971 Concerning the relationship between element (Science Applications, Inc , Berkeley, Calif ) IEEE Transactions on stability and system stability in wing-truss structure made from Antennas and Propagation, vol AP-26, Jan 1978, p 94-99 22 refs elastic and elasto-plastic materials (Uber den zusammenhang von Contracts No F29601 74-C-0010, No F29601-75-C-0120 Elementstabihtat und Systemstabilitat von Tragwerken aus elasti- The responses of aircraft antennas to a broadband electro- schem und elastisch-plastischem Werkstoff) W Brocks and K Burth magnetic wave such as the nuclear electromagnetic pulse (EMP) are (Berlin, Technische Universitat, Berlin, West Germany) Forschung analyzed For convenience of analysis the antennas are divided into im Ingenieurwesen, vol 43, no 6, 1977, p 190-198 26 refs In German five classes blades, loops, slots, bowls, and long wires From each class a few specific antennas are selected as examples for detailed A finite element method is employed to analyze deformations in elastic materials used for wing-trusses A system of geometric, discussion For each exemplary antenna the detailed equivalent nonlinear equations is developed, making use of Drucker's postulate circuit, input impedance, and effective height at the antenna's in both limited and expanded versions The effect of single unstable connector are given Measurements of input impedance on some elements is examined, as well as branch loading within the antennas are compared with the corresponding calculated results. (Author) framework of the entire system Finally, loading parameters are discussed in terms of stability and plasticity theories D M W A78-21995 Broad-band analysis of VLF/LF aircraft wire antennas L Mann, K S H Lee (Dikewood Corp, Los Angeles, A78-21976 Glass-fiber data bus systems for signal trans- Calif ), and J P Castillo (USAF, Weapons Laboratory, Kirtland mission on board (Glasfaser-Bussysteme zur Signalubertragung in AFB, Albuquerque, N Mex ) IEEE Transactions on Antennas and Bordnetzen) K Erdel and H Strehl (Siemens AG, Munich, West Propagation, vol AP-26, Jan 1978, p 141 145 9 refs Contract No Germany) Frequenz, vol 31, Dec 1977, p 364-368 11 refs In F29601-76-C-0133 German Research supported by the Bundesmmistenum der Verteidi- The broad-band response of a VLF/LF dual-wire aircraft gung antenna is analyzed The impedance properties and the induced The organizational forms of a v ionic networks for flight control currents on the two wires of different lengths are obtained via a applications are examined Difficulties with a decentralized system superposition procedure in which the original problem is split into led to the design of data bus systems Specif ications were developed two transmission-line (differential-mode current) problems and two by the US Air Force (1975) for an aircraft internal time division antenna (common-mode current) problems Results for the input command/response multiplex data bus It is expected that the copper admittance and short-circuit current of a representative VLF/LF data bus communications links of the current avionic systems will be dual-wire antenna are presented (Author) replaced in the systems of the next generation by optical glass fiber communication links A study of an experimental system using glass A78-22078 ff Hypersonic flow past a conical wing with fibers has been conducted by Shannfield and Biard (1976) Advan- detached shock wave at the leading edges (K zadache o giper- tages of a use of optical communication media include an immunity zvukovom obtekann V-obraznogo kryla s otsoedmennoi udarnoi against electromagnetic interference, the galvanic separation between volnoi na peredmkh kromkakh) N A Ostapenko Moskovsktt transmitter and receiver, the impossibility of spark formation, a wide Gosudarstvennyi Universitet, Institut Mekhaniki, Nauchnye Trudy, bandwidth, and low weight Attention is given to point to-pomt no 44, 1976, p 21-29 7 refs In Russian glass-fiber connections and glass-fiber data bus systems G R Hypersonic conical flow past a conical wing with detached shock at the leading edge is analyzed The aerodynamic coefficients are calculated, and the dependence of the hft-to-drag ratio on the A78-21989 External interaction of the nuclear EMF with opening angle of the wing is obtained The analysis reveals a gam in aircraft and missiles C D Taylor (Mississippi State University, lift to-drag ratio in conical wings with detached shock as compared Mississippi State, Miss ) IEEE Transactions on Antennas and to that of flat delta wings in hypersonic flow P T H

169 A7822079

A78-22079 ff Study of supersonic separated flow past coni- strip theory that includes tip-loss The approach entails a local cal wings and inside a right angle (Issledovanie sverkhzvukovogo optimization of blade element parameters to maximize power otryvnogo techenna pri obtekann V-obraznykh kryl'ev i vnutri output Examples are presented that illustrate the optimum design pnamogo uglal V N Alekseev and A L Conor Moskovskn generation procedure and off-design performance _ (Author) Gosudarstvennyi Universitet, Institut Mekhamki, Nauchnye Trudy, no 44. 1976, p 30-35 In Russian Models of a conical wing representing a control organ and A78-22269 Big fans for the airlines W Gunston Shell two-sided right angle corners were investigated in Mach 3 wind Aviation News, no 444 1977, p 28-34 tunnel tests, where flow on the surfaces was visualized by an oil A review of developments in commercial |et engine technology technique and the flow in transverse planes was observed by the is presented, stressing modifications of low by-pass ratio engines schlieren method The interaction of the characteristic branching which led to the production of today's engines, having a higher shock with the boundary layer was observed Criteria for separation by-pass ratio High by-pass ratio turbofans are especially effective in of flow were used to correlate flow data The evolution of the reducing noise levels and fuel consumption Attention is given to boundary layer displacement thickness was followed P T H three shaft turbofans, which simultaneously increase thrust and provide improved engine cooling Cost considerations are mentioned, especially in relation to engines in the 10/15 ton class D M W A78-22080 ff Nearly wedge-shaped antisymmetric wing in supersonic flow (Antisimmetnchnoe krylo, blizkoe k klmu, v sverkhzvukovom potokel M I Folle Moskovskn Gosudarstvennyi A78-22347 Airborne navigation systems M Hirst Flight Universitet, Institut Mekhamki, Nauchnye Trudy, no 44, 1976, p International,^ 113, Jan 14, 1978, p 110-113 36-42 7 refs In Russian The accuracy of airliner navigation systems has not increased Supersonic flow past a surface which is nearly a wedge of finite markedly since the late 1960s, but operational flexibility and thickness is analyzed under the assumption that the gas velocity installation and operating costs have continued to improve Modern behind the attached shock remains supersonic The surface of the area-navigation systems are still not fully utilized The automatic wing is centrally symmetric (antisymmetric) when viewed from the navigation systems fitted to the airliners that fly across oceans have direction of the incident flow The mathematical fojrnulation of the problem leads to two infinite chains of integrodifferential equations, been revolutionized various times over the last few decades The which are solved with the aid of the rule of indices The similarity of mertial navigation systems (INS) brought great accuracies and lower thp solution to that for a symmetric wing is noted PT H operating costs About ten years ago tnple-INS installations became standard for wide-bodied aircraft At present the dominance of INS is being challenged by very-low-frequency (VLF) aids such as Omega, and VLF communications systems relying on U S Navy trans- A78-22091 // Boundary layers in dissipative media (Pogra- missions for reference signals Most airlines now prefer dual INS with nichnye sloi v dissipativnykh sredakh) V P Stulov Moskovskn Omega In the near future the U S could make its long-awaited Gosudarstvennyi Universitet, Institut Mekhamki, Nauchnye Trudy, decision about the deployment of the Navstar GPS (Global Position- no 48, 1977 79 p 32 refs In Russian ing System) This 24-satellite system will have its transmitters in Applications of boundary-layer theory to problems in gas and three circular orbits at 10,900 n m altitude G R fluid mechanics that contain small parameters associated with the higher derivatives in the relevant equations are outlined It is noted that such an approach can be used in principle to develop uniformly in the whole region under consideration exact solutions that are in A78-22355 Transonic swirling gas flow through a nozzle accord with the boundary conditions of the initial problem V B Gorsku lAkademua Nauk SSSR, Izvestna, Mekhamka Zhidkosti i Gaza, Mar -Apr 1977, p 75-80 ) Fluid Dynamics, vol Emphasis is placed mainly on the zero approximation in fluid- and gas-mechanics problems, and boundary-layer structure in compres- 12, no^ 2, Oct 1977, p 226231 13 refs Translation The swirling gas flow in the transonic portion of a nozzle is sible gases, chemically reactive mixtures, and plasmas is studied analyzed, assuming that the flow is a steady axisymmetnc potential Regular degeneracy and boundary layers for linear differential flow and that the gas is mviscid and non-heat-conducting An equations with a small parameter are investigated along with viscous equation describing swirling potential transonic gas streams is derived incompressible fluid flows near perforated and unperforated surfaces and is shown to generalize both the transonic Karman-Falkovich Attention is also given to parabolic boundary layers, an evaluation of equation anrl its solution describing continuous nozzle flows V P the terms in the Navier-Stokes equations, the Prandtl equations, boundary-layer corrections in the analysis of a viscous incompressible A78-22359 Calculation of nonlinear aerodynamic charac- fluid flow at large Reynolds numbers, shock-wave structure, the teristics of wing of complex planform allowing for nose vortex sheet relaxation zone behind a shock wave, and the chemical boundary V A Aparmov (Akademua Nauk SSSR, Izvestna, Mekhamka layer in a viscous gas F G M Zhidkosti i Gaza, Mar -Apr 1977, p 107-111 ) Fluid Dynamics, vol 12, no 2, Oct 1977, p 253-256 Translation A78-22108 ff Fatigue of AMg6M sneet with Sprut 5M and Belotserkovskii's (1968) method, modified by Aparmov et al VAK coatings in the linear and plane states of stress under (1976) is applied to the determination of the characteristics of wings high-frequency loads (Ustalosf listovogo matenala AMgSM s pokryti- of complex planform The modification of the method makes allowance for the vortex sheet at the nose of delta wings Results of lami Sprut 5M i VAK pn linemom i ploskom napnazhennom computer-aided calculations for delta wings, small aspect ratio wings sostoiannakh v uslovnakh vysokochastotnoi nagruzki) R I with a kinked leading edge, and swept wings are examined It is Stefanpv_frob/emy Prochnosti, Oct 1977, p 45. 46 In Russian shown that the method under consideration can be used to determine moments and distributed and total loads on wings, and A78-22232 Performance-optimized horizontal-axis wind also to determine flow structures in the form of vortex sheets and turbines R E Wilson and S N Walker (Oregon State University, velocity vector fields V P Corvallis, Ore ) In International Symposium on Wind Energy Systems, Cambridge, England, September 7-9, 1976, Proceedings Cranfield, Beds, England, British Hydro- mechanics Research Association, 1977, p B1 1 to 61 28, X23, Discussion, p X24, X25 17 refs NSF Grant No AER- A78-22361 Experimental investigation of asymmetric La- 74-04014-A03 val nozzles A B Bobovich, V B Kormlovich, B N Maslov, and A Design procedures for optimum wind turbines is shown to be A Shishkov (Akademua Nauk SSSR, Izvestna, Mekhamka Zhidkosti different from that used for propellers An optimum design i Gaza, Mar Apr 1977, p 123-128 ) Fluid Dynamics, vol 12, no 2, generation approach for wind turbines is developed from a modified Oct 1977, p 266-271 11 refs Translation

170 A78-22561

The paper deals with the experimental determination of the fields, is described Data obtained in a cylinder wake are presented, magnitude of a transverse force generated in a Laval nozzle due to and its structure in both the Eulenan and Lagrangian frames is the asymmetry of the pressure field The nozzles employed included discussed Turbulence data obtained by conventional and conditional Mach 1 nozzles with subsonic portions of different design, various averaging of the velocity fluctuations are also presented These data supersonic nozzles with subsonic portions deviating from the provide details of the small- and large-scale contributions to the total supersonic portion by different angles, and nozzles with axisym- turbulent field (Author) metric supersonic and axisymmetric subsonic portions The behavior of the transverse force is illustrated for each type of nozzle, and A78 22555 * # Wake vortex measurements of bodies at high expressions approximating the transverse force are derived V P angle of attack F K Owen (Owen International Inc, Palo Alto, Calif ) and D A Johnson (NASA, Ames Research Center, Moffett Field, Calif ) American Institute of Aeronautics and Astronautics, A78-22364 Electrical fluctuations in turbulent electrogas- Aerospace Sciences Meeting, 16th, Huntsville, Ala , Jan 16-18, 1978, dynamic flows A B Vatazhm, V A Likhter, A M Rushailo, and Paper 78-23 10 p 7 refs USAF-supported research. Contract No V I Shul'gm (Akademiia Nauk SSSR, Izvestiia. Mekhanika NAS2-9168 Zhtdkosti i Gaza, Mar-Apr 1977, p 148-159 ) Fluid Dynamics, vol Three-dimensional laser velocimeter measurements have been 12, no 2, Oct 1977, p 285295 12refs Translation made of the wake vortices of a slender tangent-ogive body which had Some processes occurring in turbulent flows containing charged nose and body fineness ratios of 3 5 and 12, respectively Data were particles are examined It is shown that the presence of charged fuel obtained for an angle of attack to semmose angle ratio of 2 3 at a droplets in jets of aircraft engines leads to electric charge pulsations free-stream Mach number of 0 6 and unit Reynolds number of 2 The problem of determining the turbulence characteristics of jets million/ft Details of the mean flow field are presented and features from electric pulsations measured with electrostatic probes is of the turbulent and unsteady nature of the vortex flow field are formulated Laboratory measurements of electric pulsations in actual discussed Problems associated with obtaining meaningful vortex aircraft-engine jets are described Good correlation between electric measurements in high-speed flows are addressed (Author) and acoustic pulsations is established V P

A78-22556 * # Analysis of heat transfer in a simulated wmg- A78-22551 * ff The effect of ambient conditions on the elevon cove in hypersonic flow E G Keshock (Tennesse, University, emissions of an idling gas turbine C W Kauffman (Michigan, Knoxville, Tenn ) American Institute of Aeronautics and Astro- University, Ann Arbor, Mich ), A K Subramanian, D W Rogers, nautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala, Jan and R W Claus American Institute of Aeronautics and Astro- 16-18, 1978, Paper 78-40 9p 11 refs Grant No NsG-1318 nautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala, Jan A simplified analytical model of leakage into a wmg-elevon cove 16-18. 1978, Paper 78-3 13 p 19refs Grant No NsG-3045 under high speed external flow conditions is presented The model Changes in ambient conditions - pressure, temperature, and accounts for convection from the high temperature gas stream humidity - affect the exhaust emissions of a gas turbine engine Such leaking into the cove, radiation exchanges between walls and with variations must be compensated for during engine certification The the environment, and axial conduction within the channel walls results of a test program employing a JT8D-17 combustor are Comparisons are made of predicted and measured wall temperatures presented which quantize the effect of carefully controlled changes of an experimental wing elevon-cove model that was tested in a on unburned hydrocarbons, carbon monoxide, and oxides of hypersonic wind tunnel Analytically determined Nusselt numbers nitrogen at simulated idle operating conditions Analytical results are for laminar flow entrance conditions are compared with those given to explain the observed hydrocarbon and carbon monoxide calculated from experimentally measured gas temperatures, wall behavior It is shown that for a complete range of possible ambient temperatures and wall heating rates Although reasonable agreement variations, significant changes do occur in the amount of pollutants appears to be indicated, testing times much larger than those of the emitted by an idling gas turbine (Author) present test program (5 seconds) would be desirable in evaluating the reliability and accuracy of the simplified model (Author) A78-22553 * # A split-recoupled-semidirect computational technique applied to transonic flow over lifting airfoils E D Martin (NASA, Ames Research Center, Moffett Field, Calif ) American A78-22558 ff Research needs for U S Army aircraft propulsion C L Walker (US Army, Propulsion Laboratory, Cleveland, Institute of Aeronautics and Astronautics, Aerospace Sciences Ohio) American Institute of Aeronautics and Astronautics, Aero- Meeting, 16th, Huntsville, Ala, Jan. 16-18. 1978, Paper 78-11 15 p 40 refs space Sciences Meeting, 16th, Huntsville, Ala, Jan 16-18, 1978, Paper 78-45 8p 18 refs A new version of the semidirect iterative method eliminates Army aviation propulsion research, directed primarily toward significant restrictions of previous versions of the method A the development of fuel-economizing gas turbine helicopter engines, semidirect method solves finite-difference equations by a rapid is discussed High pressure ratio single-stage centrifugal compressors globally implicit iterative process driven by a fast direct elliptic are under investigation, centrifugal compressor impeller design, solver The new approach can treat complex systems of equations in thermal barrier coatings for turbine blades, and radial turbine an efficient 'correction form', and allows the use of general, lamination processes figure in the development program In addition, nonorthogonal, boundary-fitted coordinate transformations These high-speed shafting, spiral-groove seals, small-bore high-speed ball and features are expected to lead to significant practical applications with roller bearings, and squeeze film dampers for bearing supports are conservation-equation systems in either two or three dimensions The under study in the research program Characteristics of a 800- present application to the full potential equations for steady horse-power Advanced Technology Demonstrator Engine are present transonic flow over an airfoil at angle of attack illustrates the utility ed J MB of the technique (Author)

A78-22554 * # Measurements of unsteady vortex flow fields F K Owen (Owen International, Inc , Palo Alto, Calif) and D A A78-22561 ff A study of the mviscid flow about conically Johnson (NASA, Ames Research Onter, Moffett Field, Calif ) cambered delta wings F Marconi and M J Sidan (Grumman American Institute of Aeronautics arid Astronautics, Aerospace Aerospace Corp , Bethpage, N Y ) American Institute of Aeronautics Sciences Meeting. 16th, Huntsville, Ala, Jan 16-18, 1978. Paper and Astronautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala. 78-18 10 p USAF-supported research, Contract No NAS2-9168 Jan 16-18. 1978, Paper 78-58 12 p 13 refs Contract No A combined surface hot film and laser velocimeter measurement F33615-77-C-3126 technique, used to obtain new information on the mean, constant Finite difference methods were used to solve the Euler phase-averaged and turbulent structure of time-dependent flow equations for the three-dimensional supersonic mviscid flow about

171 A78-22570

elliptic cones and spanwise conically cambered wings with subsonic This paper presents distributed load aircraft design concepts that leading edges Explicit shock fitting techniques were used to have as a major goal the significant increase in payload from compute both the bow shock and embedded cross flow shocks New reduction of the bending moments that are responsible for a large computational procedures were adopted in order to resolve the large percentage of the structural weight The judicious use of advanced flow field gradients developed in the vicinity of the leading edge of technology including composite structure and digital control of thin wings The effect of spanwise cambering was investigated and active control surfaces for gust alleviation, flutter suppression, and was found to reduce the leading edge suction peaks, but this maneuver load control all contribute to reductions in bending reduction was accompanied by a corresponding loss in lift .The moment to achieve significantly lower structural weight fractions computed nonlinear results were compared to linearized theory The paper is based on a performance and economics study of a iAuthor) 2 8 million-pound gross weight distributed load freighter The results show significant potential improvements in energy conservation and A7ff-2257TT* ff Stress analysis study in cooled radial inflow operating economics when compared to today's aircraft (Author) turbine A Hamed, Y Sheoran, and W Tabakoff (Cincinnati, University, Cincinnati, Ohio) American Institute of Aeronautics and A78-22575 * ff Computational wing optimization and wind Astronautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala, tunnel test of semi-span model H P Haney, E G Waggoner Jan 16-18, 1978. Paper 78-94 10 p 9 refs Contract No (Vought Corp , Dallas, Tex ), and W F Ballhaus (NASA, Ames NAS2-7850 Research Center, Computational Fluid Dynamics Branch, U S Army, With increased turbine inlet temperatures, numerical methods of Air Mobility Research and Development Laboratory, Moffett Field, thermal and stress analysis are becoming more valuable in the design Calif ) American Institute of Aeronautics and Astronautics, Aero- of air-cooled turbines This paper presents a study of the stresses space Sciences Meeting, 16th, Huntsville, Ala, Jan 16-18, 1978, associated with different cooling patterns in a radial inflow turbine Paper 78-102 7p 13 refs rotor The finite element method is used in the stress calculations A computational transonic wing design procedure has been taking into consideration centrifugal, thermal and aerodynamic developed and verified by a wind tunnel test of a variable camber loading The effects of temperature distribution and the presence of semi-span wing model The Bailey-Ballhaus transonic potential flow internal cooling passages are discussed (Author) analysis code linked to Vanderplaat's constrained minimization routine was used to optimize test configurations at 0 9 Mach number Based on wind tunnel test results, computationally opti- A78-22571 # Application of laminar flow control to large mized designs were as efficient as the best configurations determined subsonic_military transport airplanes C E Jobe (USAF, Flight by previous parametric testing and performed better at off-design Dynamics Laboratory, Wright Hatterson AFB, Ohio), R M Kuiran, points Wind tunnel wing pressures agreed well with predictions from and J D Vachal (Boeing Commercial Airplane Co , Seattle, Wash ) the improved Bailey-Ballhaus code at moderate CL's Computational American Institute of Aeronautics and Astronautics, Aerospace optimization was shown to be an effective transonic wing design Sciences Meeting, 16th, Huntsville, Ala, Jan 16-18, 1978, Paper tool (Author) 78-95 15 p A study of performance increase that could result from applying A78-22576 * ft Computational transonic flow about realistic advanced aerodynamic concepts to large, long range military trans- aircraft configurations C W Boppe (Grumman Aerospace Corp, port aircraft showed that laminar flow control (LFC) offered the Bethpage, N Y) American Institute of Aeronautics and Astro- largest potential A more in-depth design study then investigated the nautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala, Jan impact of LFC on the performance, weight, fuel consumption, and 16-18, 1978, Paper 78-104 11 p Urefs Contract No NAS1-14732 economics of a military transport designed to carry 350,000 Ib A numerical method has been developed to compute transonic 10,000 nmi The design study identifies the optimum wing planform flows about realistic wing-fuselage configurations The finite differ- and cruise speed, the relative performance increases from different ence scheme employs an improved small disturbance flow equation amounts of LFC, and sensitivities to the major LFC uncertainty A unique grid embedding technique, which was heretofore applied to items, i e , increased systems weight, complexity, and maintenance, airfoils and wings, has been extended to include the treatment of which can only be quantified by design, development, and flight test both body and wing-body shapes The resulting high-density mesh is (Author) shown to be a valuable asset in resolving details of the three A78-22S72 # Aerodynamic optimization and analysis as part dimensional flow A mathematical modeling system is used to of the computer-aided design process P E Divan, III (Rockwell process arbitrary fuselage geometries for body boundary conditions International Corp, Los Angeles, Calif) American Institute of Correlations with experimental data for simple isolated bodies, an Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, isolated fuselage, and wing-fuselage combinations are included Huntsville, Ala, Jan 16-18, 1978, Paper 78-97 6 p (Author) The general philosophy and methodology behind a computer- aided conceptual aircraft design process are discussed The building blocks of the computer system are examined, with emphasis on aerodynamic optimization and design Drag reduction at design conditions is performed in an interactive process including internal A78-22577 ff Transonic computational design moamcations component arrangements and preliminary structural design, pro of the F-111 TACT A W Chen (Boeing Commercial Airplane Co , ducmg a highly cohesive air vehicle evolution When interactive Seattle, Wash ), E N Tmoco, and H Yoshihara (Boeing Aerospace computer graphics and analysis techniques are used throughout the Co .Seattle, Wash ) American Institute of Aeronautics and Astro- process, from initial design to analysis output, a consistent data base nautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala, Jan is developed which provides an added integrity and realism to 16-18, 1978, Paper 78-106 8 p 10 refs evolving configurations Finally, the improved efficiency of the F-111 TACT tests at M = 0 9 and an angle of attack of 6 deg design system over previous fragmented methods is demonstrated showed severe wing unloading in the inboard region over the glove illustrating time and cost reductions Improved interface between and fuselage and a shock wave unsweeping in the tip region disciplines which were previously decentralized is also achieved deteriorating the cruise performance A computational model is (Author) developed for use on the Bailey-Ballhaus transonic small disturbance A78-22573 H Distributed load aircraft concepts P C code which allows a good simulation of the complex fuselage Whitener (Boeing Commercial Airplane Co , Seattle, Wash ) Ameri- geometry, including inlet effects, of the F-111 TACT Comparisons can Institute of Aeronautics and Astronautics, Aerospace Sciences with experiments show good agreement 'Fixes' are demonstrated Meeting, 16th, Huntsville, Ala , Jan 16-18, 1978, Paper 78-100 10 which alleviate some of the aerodynamic deficiencies of the original i P aircraft (Author)

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A78-22578 * # Measured wake-vortex characteristics of air- A78-22586 tt Real flow limitations in supersonic airplane craft m ground effect. D L Ciffone (NASA, Ames Research Center, design R M Kulfan and A Sigalla (Boeing Commercial Airplane Moffett Field, Calif) and B Pedley American Institute of Aero- Co , Seattle, Wash ) American Institute of Aeronautics and Astro- nautics and Astronautics, Aerospace Sciences Meeting, 16th, Hunts- nautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala, Jan ville, Ala, Jan 16-18, 1978, Paper 78-109 10 p 13refs 16-18, 1978, Paper 78-147 31 p 30 refs In support of the NASA wake vortex alleviation program, Experimental studies, including pressure measurements, force measurements were made of the influences of a ground plane on measurements and flow visualization techniques, have shown that vortex trajectories and velocity profiles within lift generated wakes predicted aerodynamic performance levels of supersonic wings can be The wakes were generated by towing 0 61-m (2-ft) span models of achieved only when the flow remains attached over the entire wing two jumbo jets under water in a ship model basin The models were surface The nature of the breakdown of potential flow on configured with landing flaps and flight spoilers to investigate the supersonic wings is discussed and illustrated with experimental flow wake characteristics of these aircraft in ground effect at simulated visualization pictures and wind-tunnel data Various types of flow full-scale distances of 19 m (62 ft) to 116 m (380 ft) above the breakdown are examined Simplified flow analogies that explain ground The ground plane caused modifications in the vortex these flow phenomena are developed Practical procedures that '.rajectones but did not alter vortex interactions and merging patterns ensure design for attached flow at prescribed conditions are in these multiple vortex wakes Some distortions in vortex vertical described Flow analogies are used to explore the impact of various (tangential) velocity profiles were recorded as a result of vortex airplane design parameters on the breakdown of attached flow lateral motions and vortex interactions with the viscous boundary (Author) layer on the ground plane, however, maximum tangential velocities remained unchanged (Author) A78-22587 H Configuration development of a supersonic cruise strike-fighter R C Meyer (Grumman Aerospace Corp, A78-22579 * // The role of atmospheric shear, turbulence and Bethpage, N Y ) and W D Fields (USAF, Flight Dynamics Labora- a ground plane on the dissipation of aircraft vortex wakes A J tory, Wright-Patterson AFB, Ohio) American Institute of Aero- Bilanin, M E Teske, and J E Hirsh American Institute of nautics and Astronautics, Aerospace Sciences Meeting, 16th, Hunts- Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, ville, Ala , Jan 16-18, 1978, Paper 78-148 9 p Huntsville, Ala. Jan. 16-18, 1978, Paper 78-110 11 p 14 refs Plans for a supersonic aircraft with both advanced cruise and air Contract No NAS1-14707 combat capabilities are discussed with attention to air-frame design Enhanced dispersion of two-dimensional trailed vortex pairs The aircraft is intended to be operational in the 1985+ time period within simplified neutral atmospheric backgrounds is studied numeri and will use either side inlets or pods m its engine configuration, with cally for three conditions when the pair is imbedded in a constant the engines based on today's technology The capabilities forseen, turbulent bath (constant dissipation), when the pair is subjected to a e g , air combat maneuverability of 3 5-4 0 G at Mach 0 9 at 10,000 mean cross-wind shear, and when the pair is near the ground meters, cruise speed of Mach 2, and SRAM payload of 5000 pounds, Turbulent transport is modeled using second-order closure turbulent call for high lift/drag and thrust/weight ratios To achieve these goals, transport theory The turbulent background fields are constructed aircraft configuration features include twin nacelle arrangement, using a superequilibnum approximation The computed results allow two dimensional wedge nozzles, variable geometry inlet, fully sub- several general conclusions to be drawn with regard to the reduction merged tandem stores, variable attitude cockpit-canopy, control m circulation of the vortex pair and the rolling moment induced on a confmured canard arrangement, variable twist/variable camber wing following aircraft (1) the rate of decay of a vortex pair increases D M W with increasing background dissipation rate, (2) cross-wind shear disperses the vortex whose vorticity is opposite to the background, A78-22588 ff Arrow wings Tor supersonic cruise aircraft B and (3) the proximity of a ground plane reduces the hazard of the R Wright, F Bruckman, and N A Radovcich (Lockheed-California pair by scrubbing The phenomenon of vortex bounce is explained in Co, Burbank, Calif) American Institute of Aeronautics and terms of secondary vorticity produced at the ground plane Qualita- Astronautics, Aerospace Sciences Meeting, 16th, Huntsville, Ala, tive comparisons are made with available experimental data, and Jan 16-18, 1978, Paper 78-151 12 p 5 refs inferences of these results upon the persistence of aircraft trailing The arrow wing planform has a far greater range potential than vortices are discussed (Author) the delta wing planform for utilization on a commercial supersonic cruise vehicle An SCV concept must be configured to favor cruise efficiency The arrow wing planform cruise lift-drag ratio is approxi mately one unit higher than the delta wing The small weight A78-22584 ff Numerical simulation of the interaction of jet advantage of the delta wing cannot offset the large cruise efficiency and freestream flows in engine exhaust systems C K Forester advantage of the arrow wing The low speed aerodynamic charactens (Boeing Aerospace Co, Seattle, Wash ) American Institute of tics of the arrow wing are acceptable and can be further improved by Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, continued research and development For this, additional analytical Huntsville, Ala , Jan 16-18, 1978, Paper 78-144 9 p 41 refs tools need to be developed and wind tunnel tests conducted to A computer program with emphasis on computational efficiency provide verifications and empirical adjustments to the analytical tools The major emphasis to arrow wing development should be in and accuracy is being developed to analyze the plane or axisym- the low speed regime The design challenge is to seek out design metric two-dimensional flow fields of an engine exhaust nozzle features and refinements that improve any deficiencies of the arrow When developed, the program will yield the drag, loads, and internal wing while not sacrificing the superior cruise efficiency (Author) losses on candidate engine nozzle installations The enormous variations in characteristic length scales featured by these flow situations are treated by matching different computational strategies together into a harmonious package The compressible inviscid A78-22589 * ff An interaction solution algorithm for viscous portion of the flow field is computed with a shock-capturing code aerodynamic performance prediction A J Baker (Tennessee, Uni- Gross separation is treated by a very efficient turbulent Navier- versity, Knoxville, Tenn ) and P D Manhardt (Computational Stokes equation solver A compressible boundary layer code is used Mechanics Consultants, Inc, Knoxville, Tenn ) American Institute for the unseparated wall viscous flows Shear layers, slip surfaces, of Aeronautics and Astronautics, Aerospace Sciences Meeting, 16th, gross separation domains^ and the wall boundary layers have fitted Huntsville, Ala, Jan 16-18, 1978. Paper 78-153 13 p 28 refs mesh structure for computational efficiency The entire matched Contracts No NAS1-14307, No NAS1-14855 solution is achieved through an empirically tuned interactive scheme A weak-interaction solution algorithm is established for aero- Progress on this code is reported in this paper (Author) dynamic flow field prediction about an isolated airfoil It requires

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numerical solution of differential equations governing potential flow, outlined, and its applicability for any combination of local charac- viscous and turbulent boundary layer flow, and the turbulent wake teristics is demonstrated V P flow downstream of a trailing edge The algorithm accounts for computed viscous displacement effects on the potential flow These A78-22639 # Distribution of reliability characteristics in turn alter the viscous flow through imposed pressure gradients among aircraft units to ensure a given flight-safety level (O Closure for turbulence is accomplished using a second order model raspredelenn kharaktenstik nadezhnosti mezhdu agregatami samolet- Numerical evaluations assess factors affecting solution accuracy, nykh sistem dha obespechenna zadannogo urovnia bezopasnosti convergence and stability for the combined potential, boundary poletov) G N Kotel'mkov Aviatsionnaia Tekhnika, vol 20, no 2, layer, and parabolic Navier-Stokes equation systems as solved using a 1977, p 80-84 In Russian finite element algorithm (Author) A78-22640 jj Determination of the longitudinal lines of an A78-22590 * # Two-dimensional separated wake modeling aircraft fuselage by the special-contour method (Zadame prodol'- and its use to predict maximum section lift coefficient M L nykh linn fiuzeliazha samoleta metodom spetsial'nogo kontura) S I Henderson (Boeing Commercial Airplane Co , Seattle, Wash ) Ameri- Leliushenko and F K Chistiakov Aviatsionnaia Tekhnika, vol 20, can Institute of Aeronautics and'Astronautics, Aerospace Sciences no 2, 1977, p 85-88 In Russian Meeting, 16th, Huntsville, Ala, Jan 16-18, 1978, Paper 78-156 8p In order to optimize a complex program of designing 'fuselage- 6refs Contract No NAS1-14742 nacelle' type surfaces, it is proposed to calculate all transverse and A technique for computing the lift of separating multielement longitudinal lines of an aircraft fuselage by the special-contour airfoils in incompressible flow is presented The procedure employs method A block diagram for computing longitudinal lines is given as repeated application of a panel method to solve for the separated a complement to the block diagram for designing a complex surface wake displacement surface using entirely inviscid boundary condi- that satisfies a priori optimahty criteria V P tions Results are presented that compare computed pressure distributions with those measured in the wind tunnel for airfoils with A78-22642 ft Uniformly precise conformal mapping of the one, two, and four elements with separation on each element A exterior of a circle onto the exterior of a wing section (Ravnomerno method employing this technique is presented which shows promise tochnoe konformnoe preobrazovame vneshnosti kruga na vneshnost' in predicting airfoil section lift through stall (Author) krylovogo profilia) N M Monakhov Aviatsionnaia Tekhnika, vol 20, no 2, 1977, p 94-98 In Russian A78-22627 H A superelement technique for designing heli- In the present paper, the local irregular part of the conformal copter fuselages (Superelementnyi metod rascheta fiuzeliazha verto- mapping function is determined with a precision to quantities of leta) O M Aksenov and Z I Burman Aviatsionnaia Tekhnika, vol second-order smallness, for the conformal mapping of the exterior of 20, no 2, 1977, p 12-17 7 refs In Russian the sharp trailing edge of a wing section Using an irregular conformal In the finite element technique proposed, the helicopter fuselage mapping function it proved possible to map the entire region with a is broken down into bays in the frame planes These superelements precision to quantities of fifth-order smallness The zero-lift angle are then joined to a precison equal to that of a 'nonpartioning' which affects all the aerodynamic characteristics of the wing section scheme Using the method of forces, a theory and a general matrix is determined with a precision to quantities of fourth-order small- algorithm for calculating a helicopter fuselage are developed Cutouts ness V P are taken into consideration by the principle of superposed initial strains, either before or after joining For illustration, the method is A78-22645 # Dynamic model of a system of scientific applied to the calculation of an actual fuselage V P research and industrial plants (Dinamtcheskaia model' sistemy nauchno-issledovatel'skikh i proizvodstvennykh ob'ektov) T K A78-22630 § Analysis of the determination of acceptance- Sirazetdinov Aviatsionnaia Tekhnika, vol 20, no 2, 1977, p inspection parameters for gas-turbine engines (Anahz formirovaniia 112-117 In Russian parametrov dopuskovogo kontrolia GTD) M Kh Bikchantaev and In this paper, an organization devoted to target science, that is, lu V Kozhevnikov Aviatsionnaia Tekhnika, vol 20, no 2, 1977, p scientific research into means of perfecting specific aspects of 31-35 In Russian production, is called a target scientific research plant The study Formulas are derived for calculating the tolerances of gas- concerns the derivation of equations for the development of a target turbme-engine parameters The determination of tolerances as a scientific-research plant, where the output of such a plant is function of measurement errors and of permissible values of the measured by the values of the economic indices of the production engine parameters is analyzed on the basis of extensive computa- plant which it is investigating and serving P T H tional data, assuming that the permissible values are symmetrical with respect to the mathematical expectation V P A78-22646 # An evaluation of weight optimization of air- A78-22634 ff Modeling the influence of the ground effect on craft radioelectronic equipment (Ob otspnke vesovogo sovershenstva the aerodynamic characteristics of a wing by means of a flat screen samoletnoi radioelektronnoi apparatury) V G Gogol in and I A of finite dimensions (K voprosu o modehrovami vlnanna bhzosti Iskhakov Aviatsionnaia Tekhnika, vol 20, no 2, 1977, p 118, 119 poverkhnosti zemli na aerodmamicheskie kharakteristiki kryla s In Russian pomoshch'iu ploskogo ekrana konechnykh razmerov) S D Ermolenko and lu A Rogozin Aviatsionnaia Tekhnika, vol 20, no A78-22647 ff A study of the influence of slits on the 2, 1977, p 50-54 In Russian effectiveness of wing mechanization and controls in separated flow (Issledovame vlnanna shchelei na effektivnost' mekhamzatsu kryla i A78-22636 ff Analysis and calculation of plane skew sym- organov upravlenna pri sryvnom obtekann) V V Guliaev, A A metric contours of second-order smoothness (Anahz i raschet Mikhailov, and M I Nisht Aviatsionnaia Tekhnika, vol 20, no 2, ploskikh znakoperemennykh obvodov vtorogo ponadka gladkosti) 1977, p 119-121 In Russian V P Zelev and V A Osipov Aviatsionnaia Tekhnika, vol 20, no 2, 1977, p 62-66 In Russian A78-22649 # Fatigue crack growth in a pressure-fuselage The calculation of complex three-dimensional lines of flow of panel (O roste ustalostnykh treshchm v paneli germofiuzeliazha) A second-order smoothness forms the basis for designing channel B Kaplun and V D Kuliev Aviatsionnaia Tekhnika, vol 20, no 2, surfaces In the present paper, it is proposed to use cubic parabolas, 1977, p 124-127 In Russian which in the general case possess five independent parameters, for In the present paper, the growth of fatigue cracks in an airliner designing skew symmetric contours of second-order smoothness A panel under the combined effect of acoustic-pressure stresses and method of designing such contours with the aid of cubic parabolas is stresses associated with the difference in external and internal

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pressure is analyzed within the framework of fracture mechanics involved in developing the system are seen as soluble within the The spectrum of alternating stresses generated by acoustic pressure is framework of present technology D M W described by a Rayleigh distribution A method of evaluating the influence of acoustic-pressure stresses on the growth of fatigue cracks A78-22852 H Testing a modern strike aircraft navigation in a fuselage panel is proposed It is shown that under certain system J B V Collins (Aeroplane and Armament Experimental conditions, the influence of acoustic loads on crack growth exceeds Establishment, Boscombe Down, Wilts, England) Journal of Naviga- by far that of the pressure difference V P tion, vol 31, Jan 1978, p 29-37, Discussion, p 37,38 Consideration is given to the testing of a military aircraft A78-22652 # The experimental determination of the param- navigation system in the United Kingdom The system is planned for eters of a mathematical model of an aircraft passenger compartment a low-level strike role and for the continuous presentation of position as a control plant with respect to air temperature (Eksperimental'noe and steering information The navigation system employs mertial •opredeleme parametrov matematicheskoi modeli salona samoleta kak navigation and a Doppler radar Testing consists of a sequence of reguliruemogo ob'ekta po temperature vozdukha v nem) V I steps (1) an indepth systems appraisal, (2) the development of Krutov, V G Voronin, and A V Shcherbakov Aviatsionnaia simple system models, (3) the identification of factors which explain Tekhmka,vo\ 20, no 2, 1977, p 133-136 In Russian system behavior, (4) gathering statistics on operational factors, (5) the structuring of flight and ground trials, and (6) establishing mathematical models S C S A78-22724 Fracture analvsjs of aerospace metals H J Oberson, Jr (Boeing Commercial Airplane Lo, Renton, Wash ) SAMPE Journal, vol 13, Nov-Dec 1977, p 4-11 A78-22900 Fire detection devices L Graham Aviation Engineering and Maintenance, Nov Dec 1977, p 14,17-20 The intent of this paper is to outline, first, the value of fracture analysis, and then, the analytical methods employed in establishing Fire detection devices for aircraft cabins are evaluated on the the specific mechanism(s) responsible for crack initiation and basis of their reliability, ease of maintenance, and scope of function subsequent growth Next, the cracking modes associated with the throughout the aircraft operating envelope Three atmospheric early most widely used structural metals on commercial aircraft will be warning signals are discussed, together with the most effective discussed Finally, two examples, one for an aluminum component methods for their detection aerosols, best detected by lonization and the other a low-alloy steel component, have been selected for and photoelectric techniques, gases, best detected by using a detailed discussion based on the extensive analysis required and the gas-sensitive polymer film attached to a semi conductor, and heat interesting characteristics of the initial phase of crack propagation energy, best detected by UV and IR sensors Laser beam, condensa- (Author) tion nuclei, and resonant quartz crystal detectors are also considered A table is presented outlining operating parameters for the detection A78-22737 ff Airworthiness criteria for aluminum alloy systems discussed D M W covering with uniform corrosion damage (Krrtern tekhntcheskogo sostoianua obshivok iz aliumimevykh splavov s ravnomernymi A78-22937 Special areas of gas dynamics Sonic, hyper- korrozionnymi porazheniiami) A I Radchenko and A E Sultanov sonic, lifting surfaces, wave propagation (Spezialgebiete der Gas- (Kievsku Institut Inzhenerov Grazhdanskoi Aviatsn, Kiev, Ukrainian dynamik Schallnahe, Hyperschall, Tragflachen, Wellenausbreitung) SSR) Fiziko-Khimicheskaia Mekhanika Matenalov, vol 13, Sept- K Oswatitsch (Wien, Techmsche Umversitat, Vienna, Austria) Oct 1977, p 98-101 In Russian Vienna, Sprmger-Verlag, 1977 384 p 157 refs In German $90 80 Fatigue tests were performed on 2mm thick D16 ATV Significant differences In gas dynamics result from varying aluminum alloy aircraft sheath specimens subjected to a cyclic aircraft speeds To account for the differences, the study of gas tension of 40-45 cycles/mm at maximum stresses varying between dynamics has been subdivided into specialized areas Among the 13 88 and 22 kg/sq mm Uniform corrosion damage was produced by topics discussed are influence of Mach number on flow distribution, 3% NaCI solution The fatigue life of corrosion-attacked specimens stationary flow, friction-free flow, spatial and time-dependent was compared to that of specimens with stress raisers in the form of wave-propagation, and stationary flow around a wing of infinite 1-mm diam holes The life of corroded specimens fluctuated between length Equations illustrating both generalized and exact solutions 2900 and 260,000 cycles A least-squares statistical analysis of for specific flow problems are presented D M W experimental data yielded airworthiness criteria in the form of correlational equations expressing service life in terms of corrosion A78-23049 Atmospheric turbulence loads on aircraft J depth in percents of initial plate thickness S D Taylor Aeronautical Journal, vol 81, Dec 1977, p 528-553 21 refs A78-22848 # The weight of fuel tanks in aircraft (Sul peso The problems encountered by aircraft operating under condi- dei serbatoi del carburante nei vehvoli) G Gabnelli (Torino, tions of turbulence are discussed with respect to determination of Pohtecmco, Turin, Italy) Ingegneria, Nov -Dec 1977, p 321-324 In gust structure, aircraft reaction to gusts of known structure, and the Italian determination of operating statistics A two-dimensional spectral Semi-empirical relations are presented for determining the density analysis is presented in which the rms velocity, vertical, and weight of aircraft fuel tanks as a function of structural factors, shape, lateral components of air turbulence are evaluated in terms of their the specific weight of the tank material, and the thickness of the effects on roll, pitch, and angular velocity of an aircraft Load tank envelope Both flexible envelope (nylon rubber) and metal parameters are considered in relation to isotropic, homogeneous (aluminum, magnesium or duralummum) fuel tank designs are taken turbulence, with attention given to a Rayleigh distribution of level into account in the design program J M B crossings Finally, digital data from flight recordings is given, in which an empirical estimation is made of the boundaries of a turbulence encounter D M W A78-22851 The collision risk J M Ramsden Flight International, vol 113, Jan 21.1978, p 188-190 The rapidly expanding volume of air traffic expected between A78-23050 An aerofoil with control surface in in- now and the end of the century necessitates a renewed emphasis on compressible viscous flow B C Basu (Indian Institute of Tech- pilot responsibility for collision avoidance A system called 'Flight- nology, Kharagpur, India) Aeronautical Journal, vol 81, Dec 1977, watch' based on digital electronics is proposed as an on-board p 554,555 8 refs back-up to ground based air traffic control The system would A two-dimensional airfoil with a conventional trailing edge function independently of the air traffic control loop, and would control surface is considered in terms of boundary layer effects A warn the pilot when a nearby aircraft is, or can be expected, at the mathematical model is presented to analyze the respective roles of same altitude Based on information from Flightwatch, a pilot could pressure distribution, lift and moment coefficients, and flow parame- choose to override ground based instructions Technical problems ters D M W

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A78-23058 fi Why the flexible wing II (Dlaczego sprezyste available measurements The results demonstrate that the calculation skrzydlo II) J Wolf Technika Lotmcza i Astronautyczna, vol 31, procedure is general and economic and that the k-epsilon turbulence Nov 1977, p 13-18 10refs In Polish model involving the assumption of an isotropic eddy viscosity The paper discusses the stability and dynamic characteristics of provides reasonable predictions for the quantities of engineering the flexible wing Models are presented for a pure wing Data interest (Author) demonstrating the superior performance of the flexible wing over the first- and second-generation Rogallo type wings and the wing used in A78-23219 Two point correlations of jet noise H S the Eagle II glider are presented P T H Ribner (Toronto, University, Downsview, Ontario, Canada) Journal of Sound and Vibration, vol 56, Jan 8, 1978, p 1 19 23 refs Grant A78-23059 # Application of light-emitting diodes /LEDs/ in No AF-AFOSR-75-2808B aircraft analog indicators (Zastosowame diod elektro- luminescencyjnych /LED/ w lotmczych wskazmkach analogowych) A78-23247 An experimental study OT sound diffraction at J Tomaszewicz (Instytut Lotnictwa, Warsaw, Poland) Technika an airfoil trailing edge S N Heavens (Cambridge University, Lotnicza i Astronautyczna, vol 31, Nov 1977, p 28-31 In Polish Cambridge, England) Journal of Fluid Mechanics, vol 84, Jan 30, The paper discusses the general features of control circuits for 1978, p 331-335 12 refs Research supported by the Ministry of LED indicators An example of the development of an analog Defence and Science Research Council indicator using 13 luminous elements is given The system features a Spark photography with a sensitive schlieren system has been zero in the middle of the scale, a sensitivity of better than 1 mV per used to show the interaction between an incident acoustic wave and scale interval, and a four-bit A/D converter P T H the flow around an airfoil trailing edge Impact of the wave did not show any significant observable effect on the wake or trailmg-edge A78-23133 ft Observational computation in the case of boundary layer The intensity of the wave diffracted from the edge redundant measurements (Observatsionnoe schislenie pn izbytoch- varied considerably with the prevailing flow conditions In the event nykh izmerennakh) G la Dolgmtseva, A A Ignatov, and N V of unsteadiness in the flow or boundary-layer separation the Makarova (Lenmgradskn Institut Aviatsionnogo Priborostroenna, diffracted wave was strongly visible In smooth flows with attached Leningrad, USSR) Priborostroenie, vol 20, no 8, 1977, p 65-69 6 boundary layers the diffracted wave was very weak These observa- refs In Russian tions tend to support the recent conclusion of Howe (1976) that Observational computation refers here to the continuous mode trailmg-edge flows are quieter if they do not show singular behavior of determination of coordinates from data of position sensors in a This is in contrast to the predictions of earlier theoretical models of radio navigation system The system considered consists of several the edge diffraction problem (Author) position sensors and an autonomous system of computation, with constraints on memory capacity and the speed of the special digital A78-23274 Method of calculating the compressible flow computer As an example, a Kalman filter approach is used for the round an aerofoil or a cascade up to the shockfree transonic range. simultaneous processing of Loran and Shoran data B J T-S Luu and G Coulmy (CNRS, Laboratoire d'lnformatique pour la Mecanique et les Sciences de I'lngemeur, Orsay, Essonne, France). A78-23185 H Analysis of unsteady viscous flow past an Computers and Fluids, vol 5, Dec 1977, p 261-275 19 refs airfoil II - Numerical formulation and results Z M Cielak and R B A numerical scheme based on discrete-distribution singularities Kmney (Arizona, University, Tucson, Ariz ) AIAA Journal, vol 16, is used to analyze compressible flow past a single airfoil or cascade Feb 1978, P 105-110 5 refs Research supported by the Alexander When the freestream Mach number is beyond the upper limit of the von Humboldt-Stiftung, NSF Grant No ENG-73-03855-A01 shock-free regime, the computation becomes divergent Thus for A numerical formulation of the analysis presented in Part I is each airfoil or cascade, this method indicates the upper limit of the developed The integral equation for the bound-vorticity distribution freestream Mach number under which the shock-free flow may be is cast into a system of linear simultaneous equations The unsteady realized Although the method involves a discrete treatment of space, vorticity transport equation is solved in finite-difference form using a it differs fundamentally from finite difference or finit element standard technique which is explicit in time A semianalytical methods B J procedure is developed for the calculation of the velocity field via the Biot-Savart law The utility of the numerical method is A78-23295 Some special boundary layer problems /20th demonstrated through calculations performed for the flow past a Ludwig Prandtl Memorial Lecture/ A D Young (Queen Mary symmetrical Joukowski airfoil impulsively set into motion The College, London, England) Zeitschnft fur Flugwissenschaften und airfoil thickness is approximately 12%, and results are presented for Weltraumforschung, vol 1, Nov-Dec 1977, p 401-414 30 refs. angles of attack of 0 deg and 30 deg for a Reynolds number of 400 Laminar separation of bubbles is analyzed in relation to stall Representative vorticity contours, velocity profiles, and pressure characteristics of aircraft wings The parameters of a reverse-flow distributions over the airfoil surface are given An important feature vortex between the transition and reattachment components of a of the method is that the pressure distribution is inherently flow beneath the turbulent part of the shear layer are discussed single-valued, this being calculated directly from an integral of the Attention is given to comparisons between two-dimensional, or bound-vorticity distribution over the surface The precision of the unswept, short bubbles and swept bubbles Also analyzed are flow results is found to be quite good, even near the cusped trailing edge characteristics in corners and junctions, especially the wing-fuselage (Author) junction Laminar and transition flows are described in terms of their effect on total airframe structure D M W A78-23188 ff Calculation of general three-dimensional turbulent boundary layers A K Rastogi and W Rodi (Karlsruhe, Umversitat, Karlsruhe, West Germany) AIAA Journal, vol 16, Feb A78-23297 The low-speed air tunnel of the Institute of 1978, p 151-159 28 refs Hydromechanics at the University of Karlsruhe (Der Niedergeschwm- A finite-difference calculation method is described for three- digkeitswmdkanal des Instituts fur Hydromechamk an der Umversitat dimensional boundary layers in which the flow depends on all three Karlsruhe) R Ermshaus and E Naudascher (Karlsruhe, Umversitat, space variables The method employs the k-epsilon turbulence model Karlsruhe, West Germany) Zeitschnft fur Flugwissenschaften und and is applied to the following three flow situations boundary layer Weltraumforschung, vol 1, Nov-Dec 1977, p 419-425 7 refs In on a flat plate approaching a circular cylinder mounted on the plate, German Research supported by the Stiftung Volkswagenwerk boundary layer beneath the leading-edge vortex on a delta wing, and A variety of research projects in the fields of Environmental boundary layer on the upper surface of a curved duct with both zero Fluid Mechanics and Building Aerodynamics require for their and adverse longitudinal pressure gradients The calculated skin solution an air-tunnel facility combining an accurately adjustable friction, momentum thickness, shape factor, wall crossflow angle, uniform flow (including flow of low turbulent intensity) with a very and a few velocity and shear stress profiles are compared with long working section The following report describes the design and

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construction of the low-velocity wind tunnel of the Institute of A78-23412 Power conditioning systems for high-power, Hydromechanics at the University of Karlsruhe whose octogonally- airborne, pulsed applications A S Gilmour, Jr (New York, State shaped closed test-section has a length of 8 m and a diameter of 1 5 University, Buffalo, N Y ) /Pulsed Power Systems Workshop, Silver m The turbulence intensity of the axial velocity fluctuations in the Spring, Md, Sept 19761 IEEE Transactions on Aerospace and test section over the whole range of mean velocity (0 to 45 m/sec) Electronic Systems, vol AES-13, Nov 1977, p 660-678 23 refs does not exceed 0 1% The feasibility to position the remotely- USA F-supported research controlled probe carriage is a great help in the conduct of Power conditioning systems and critical component develop- experiments. Initial tests for the determination of flow charac- ments are defined which will be required to interface airborne 10-50 teristics are reported (Author) MW sources Power conditioning systems for use with MHD generators and turbine driven alternators, both conventional and A78-23372 # Spectrum crack growth in adhesively bonded superconducting, are considered Component analyses include esti- structure W S Johnson, W C Rister, and T Spamer (General mations of necessary development efforts and of specific weights and Dynamics Corp , Fort Worth, Tex ) (American Society of Mechani- volumes for components The primary components considered are cal Engineers, Winter Annual Meeting, Atlanta, Ga, Nov 27-Dec 2, transformers, (for alternator as well as inverter use), switches, 1977, Paper 77-WA/Mat-7) ASME, Transactions, Journal of Engi- capacitors, and inductors Weight algorithms are developed for each neering Materials and Technology, vol 100, Jan 1978, p 57 63 21 of these components Subsystems such as inverters, and rectifier and refs. filter packages are also examined BJ A method is presented by which crack growth of damage tolerance type flaws can be predicted m adhesively bonded structure A78 23420 ,7 Where aerospace can serve afresh - Paths to subjected to spectrum loading The method accounts for a laminate energy independence W M Hawkins (Lockheed California Co, stress intensity correction factor, induced bending and axial load Burbank, Calif) Astronautics and Aeronautics, vol 16, Feb 1978, transfer between plies, as well as a crack growth analysis procedure p 32-36 to predict the crack growth retardation behavior under spectrum The national goal of independence from foreign energy sources, load Analytical predictions are compared to several test results to i e , Mid east oil, is considered with respect to the relationship show the applicability of the prediction method presented (Author) between industry and government, and the feasibility of developing new energy technologies Attention is given to the role the aerospace A78-23373 # Development of random fatigue data for industry could play in contributing to U S energy self-sufficiency adhesively bonded and weldbonded structures subjected to dynamic Assets of the aerospace industry include a proven diversity of excitation K R Wentz and H F Wolfe (USAF, Flight Dynamics engineering talent, experience with technological risk, and experience Laboratory, Wright-Patterson AFB, Ohio) (American Society of in dealing with a wide variety of government agencies Among the Mechanical Engineers, Winter Annual Meeting, Atlanta, Ga , Nov new technologies proposed are using fusion explosions to generate 27-Dec 2, 1977, Paper 77WA/Mat-1) ASME, Transactions, Journal superheated steam, nuclear-based conversion of seawater to hvdro- of Engineering Materials and Technology, vol 100, Jan 1978, p gen, methane production from plants and waste, ocean thermal 70-76 9 refs energy conversion and coal gasification D M W Prediction methods are being developed to determine the sonic fatigue life of various weldbonded and adhesively bonded aircraft A78-23421 * # Toward scramjet aircraft R A Jones and P structures when exposed to high intensity acoustic excitation This W Huber (NASA, Langley Research Center, Hypersonic Propulsion paper describes the results of the experimental investigations Branch, Hampton, Va ) Astronautics and Aeronautics, vol 16, Feb performed by the AF Flight Dynamics Laboratory to obtain the 1978, p 38-48 11 refs factors that affect the random fatigue life of typical aircraft The possibility for civil, military, and remotely piloted aviation structural joint configurations The structures tested included full- above Mach 5 is discussed with reference to the scramjet Actively scale components, simple beam sections, and acoustic panel configu- cooled aircraft structures of low weight are described, together with rations A variety of aluminum skin thicknesses, stiffener configura- jet nozzle design and combustion parameters The scramjet is seen as tions, and bond systems have been tested under dynamic excitation operating alone or in tandem with ramjet propulsion, which would The bond systems tested begin with the weldbond systems developed power an aircraft up to scramjet speeds Attention is given to the in the early 1970s up to the present bond systems Random flexural specific impulse of the scramjet engine, with hydrogen as the primary fatigue curves for two modes of failure have been developed fuel Applications include advanced reconnaissance and interceptor adhesive bond system failure and metal fatigue failure These curves aircraft, strategic cruise (both aircraft and missiles), highly- are part of the design criteria needed to predict the sonic fatigue life maneuverable interceptor missiles, transports, aircraft-type launch of weldbonded and adhesively bonded structures (Author) vehicles, first stages for Space Shuttle launching craft, and single- stage-to-orbit vehicles Research has focused on increasing the propulsion power of the scramjet engine, while reducing drag on the A78-23398 If Prediction of the ascending speeds of gliders in accompanying airframe D M W thermal convection over a plain (Prevision des vitesses ascendantes des planeurs en convection thermique de plaine) R Vaillant (Meteoiologie Nationale, Boulogne-Billancourt, Hauts-de-Seine, A78-23433 * Wear studies on aircraft brake materials T L France) La MetiSorologie, Sept 1977, p 77-91 In French Ho (Rensselaer Polytechnic Institute, Troy, NY) In Wear of The paper provides a meteorological analysis of the problem and materials - 1977, Proceedings of the International Conference, St presents a graph procedure for calculating the ascending speed of Louis, Mo , April 25-18, 1977 New York, gliders that rise in thermal convection over a plain The mam input American Society of Mechanical Engineers, 1977, p 70-76 19 refs parameter is the desired height of flight, which is equal to the Grant No NGR-33-018-152 altitude of the top of the thermal convection system or to the An investigation of both worn surfaces of friction pads and steel altitude of the base of a cumulus cloud (since gliding within a cloud rotors which are being applied in current aircraft brakes has been is illegal) The nebulosity as expressed in an 8-pomt scale must also carried out by employing an X-ray diffraction technique It consists be determined The relationship between the desired height and the of the analysis of chemical element distribution in the surface layers ascending speed is found to be linear, and the y-mtercept is The wear particles were also examined by using the scanning electron determined by the nebulosity (the relationship of which to the microscope The initiation and growth of surface cracks and the ascending speed is roughly bell-shaped) The relationship of the oxidation were emphasized in this investigation A wear model was ascending speed to the maximum ascending speed is linear, this latter proposed for the current aircraft brake materials Essentially this quantity, produced by vertical gusts, is of interest to gliders who will model proposed that cracks are formed in the surface layer of the often wait for the gusts A table of corrections sometimes required brake material due to the normal and fnctional stresses It is when clouds other than cumulus are present is provided M L primarily surface temperature dependent (Author)

177 A78 23439

A78-23439 Mechanism of wear in helicopter hydraulic and the superposition of at least two N waves in space and time The systems O Johari, S V Samudra, I Corvm, and J Staschke (NT location of the ground focus line produced by an aircraft which is Research Institute, Chicago, III ) In Wear of materials - 1977, accelerating while traveling at supersonic speed is also determined for Proceedings of the International Conference, St Louis, Mo , April the case of travel in a linear flight path Although some focussing is 25-28, 1977 New York, American Society of considered inevitable because of the necessity of aircraft to vary Mechanical Engineers, 1977, p 265-273 Grant No DAAJ01- speed for corrective maneuvers, it is thought that it will be possible 73-C 0781 to avoid disturbing populated areas with sonic booms caused by The operational safety of helicopter hydraulic systems is aircraft M L monitored presently by periodic checks of oil using spectrographic oil analysis Such analysis does not explain the mechanism of wear or A78-23470 ft Systems analysis of safety in aviation I (Sys- which particular component is wearing SEM/X-ray spectroscopy of temowa analiza bezpieczenstwa w lotmctwie I) J Morawski and T the wear participates, however, shows a wealth of information on Smolicz Technika Lotntcza i Astronautyczna, vol 32, Dec 1977, p morphology and origin of the wear particles The nature of wear 2022 In Polish patterns of different components and their relation to the wear A logical basis for analyzing safety in aviation is proposed Four particles is explained here The major cause of the wear is shown to classes of likelihood of an event and three classes of seriousness of be the contamination of the system by sand particles entering the consequences of the event are suggested Events are either through seals and the embedding of particles in the seals lesultmg in malfunctions (eg, of aircraft equipment or ground control equip- polishing type of wear Evidence is presented for the nature of these ment), external random events (eg, atmospheric ones), and errors contaminant particles and sources of their entry into the system, and (due to improper action or failure of action on part of personnel) recommendations are made for minimizing such contamination Classifications are discussed for quality of giving an instruction, through design modifications (Author) understanding an instruction, performance skills, equipment and working conditions, time factor, and final result Some reasons for A78-23441 Coatings for fretting prevention B K Gabel the greater percentage of pilot errors causing accidents in civil and J J Bethke (U S Naval Material Command, Naval Air aviation than in commercial aviation are discussed P T H Development Center, Warmmster, Pa ) In Wear of materials - 1977, Proceedings of the International Conference, St Louis, Mo, April A78-23471 ff Airports for short takeoff and landing (Lot- 25-28, 1977 New York, American Society of niska krotkiego startu i ladowania) B Rzeczynski Technika Mechanical Engineers, 1977, p 331-336 6 refs Lotmcza i Astronautyczna, vol 32, Dec 1977, p 23-26 6 refs In The purpose of the considered program was to determine the Polish optimum fretting fatigue resistant coatings for titanium steel mating The future growth of passenger air traffic in Poland is predicted, surfaces found in helicopter rotor hub assemblies Several problems and the desirability of introducing short takeoff and landing airports have been encountered during component accelerated fatigue tests of into the passenger air network is discussed These airports may serve the hub assembly, where fatigue failures of the titanium hub initiated minor provincial capitals or industrial and tourist centers, or they at areas of severe fretting In order to address this problem, a may be located in large cities and operate in coniunction with program was developed to evaluate candidate coatings in terms of conventional airports P T H their ability to reduce or eliminate fretting of Ti 6AI-4V when in contact with 17-4 PH steel This paper will describe the new fretting A78-23574 The strength of structures and the applications test apparatus, the results obtained thus far on screening selected of the fracture mechanics W Barrois Engineering Fracture coatings which might have potential for fretting protection, and an Mechanics, vol 10, no 1, 1978, p 109-114 7 refs evaluation of bend bar test specimen configuration designed to Documentation on the application of fracture mechanics to the achieve fretting fatigue under conditions comparable to those selection of aluminum alloys subject to fatigue cycling is briefly experienced in the actual rotor hub assemblies (Author) reviewed Attention is given to the role of fracture mechanics in A78-23451 * ," Friction and wear of sintered fibermetal abrad- determining the stress intensity factor and fatigue crack growth rate able seal materials R C Bill (NASA, Lewis Research Center, U S as related to the strength of structures It is expected that the Army, Air Mobility Research and Development Laboratory, Cleve- maximum useful knowledge for the designer would be provided by land, Ohio) and L T Shiembob (United Technologies Corp, Pratt detailed theoretical and experimental analyses of each case of local and Whitney Aircraft Group, East Hartford, Conn ) ASME, ASTM, failure or damage occurring during static strength tests and full-scale ASM, SME, ASLE, and SAE, International Conference on Wear of fatigue tests as well as of damage occurring during operations in Materials, St Louis, Mo , Apr 25-28, 1977, Paper 26 p 10 refs actual aircraft structures S D Three abradable gas-path seal-material systems based on a sintered NiCrAlY fiber metal structure were evaluated under a range A78-23575 Stresses and displacements due to load transfer of wear conditions representative of those likely to be encountered by fasteners in structural assemblies W Barrois Engineering Frac- in various knife-edge seal (labyrinth or shrouded turbine) applica- ture Mechanics, vol 10, no 1, 1978, p 115-176 23 refs tions Conditions leading to undesirable wear of the rotating knife Theoretical aspects of stress concentration and subsequent were identified, and a model proposed based on thermal effects displacement in critically loaded structural assemblies are examined arising under different rub conditions It was found, and predicted for the cases of a loaded hole (double symmetrical shear) and rivet or by the model, that low incursion (plunge) rates tended to promote bolt shanks stresses in single shear For the first case, the concept of smearing of the low-density sintered material with consequent wear reference lines on strips at cross sections, where stress distributions to the knife edge Tradeoff benefits between baseline 19 percent through the strip widths are fairly uniform, is applied, this allowed dense material, a similar material of increased density, and a approximate computation of strip strains and relative displacements self-lubricating coating applied to the 19 percent dense material were between assembled strips The second case is discussed relative to identified on the basis of relative rub tolerance and erosion absolutely rigid fastener shanks, flexible pin or fastener shank, and resistance (Author) side plates and reinforcements Since fatigue cracks originate from the material surface, at a notch root or at a hole edge, the relevant A78-23457 ff The location of the ground focus line pro- terms of comparison are the surface stress at the crack origin and its duced by a supersonic aircraft R Makarewicz (Poznan, Uniwersytet, stress gradient S D Poznan, Poland) Archives of Acoustics, vol 2, no 3, 1977, p 167-176 7 refs A78-23801 YAH-64 advanced attack helicopter design Algorithms are derived for determining where shock waves tradeoffs J C Dendy (Hughes Helicopters, Culver City, Calif) caused by a sonic boom will be focussed on the earth's surface The Society of Automotive Engineers, Aerospace Meeting, Los Angeles, analysis considers the 'coupled cone' associated with the Mach cone Calif, Nov 14-17. 1977, Paper 770950 13 p

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A description of the U S Army's advance attack helicopter, A78-23815 747 Shuttle Carrier Aircraft/Space Shuttle YA-64, is presented A comparison is made between various crew Orbiter mated ground vibration test • Data via transient excitation station configurations, and the final design selection is discussed The and fast Fourier transform analysis N L Olsen and M J Walter target acquisition/designation system, the primary sighting system, is (Boeing Co, Seattle, Wash ) Society of Automotive Engineers, described along with the design criteria of the landing gear The mam Aerospace Meeting, Los Angeles, Calif, Nov 14-17, 1977, Paper features of the tail rotor drive system are identified and attention is 770970 10 p 6 refs given to specifications of the aircraft's performance margin and operational flexibility S C S A78-23816 Fluitci tests of the mated 747 Shuttle Carrier Aircraft-Orbrter L V Andrew (Rockwell International Corp , Space A78-23802 The Bell Model 222 J R Garrison and H H Div , Downey, Calif ) Society of Automotive Engineers, Aerospace Waldrup (Bell Helicopter Textron, Fort Worth, Tex ) Society of Meeting, Los Angeles. Calif, Nov 14-17, 1977, Paper 770971 14 p Automotive Engineers, Aerospace Meeting, Los Angeles, Calif, Nov 6 refs 14-17, 1977, Paper 770951 15 p Flutter tests of the mated 747 Shuttle Carrier Aircraft-Orbiter The design objectives, features and performance of the recently are discussed from the viewpoint of the flutter engineer of the prime developed Bell Model 222 is described in terms of primary design Space Shuttle contractor, the Space Division of Rockwell Interna- objectives, including safety, efficiency, reduced cost of ownership, tional The telemetered data that he and the other test team and superior handling qualities From the test results, the Model 222 members monitored on real-time displays are described, as are the is a fuel conservative, productive aircraft with excellent flying safety criteria applied during buffet tests The instrumentation and qualities The 222 far exceeds the FAA requirements for fail safe telemetering of orbiter data are treated for both the unpowered design and crashworthmess Redundancy, 8g seats, crash resistant (inert) and the powered up (active) orbiter Highlights of each flight, fuel tanks, and real twin-engine safety are examples The latter refers including the crew's comments, are reported, along with details to the fact that for any altitude at which the helicopter can hover pertinent to the structural dynamics of the system (Author) OGE, it can continue to cruise if one engine fails The first flight was in August 1976 and development is essentially complete The aircraft A78-23818 Transient expansion of the components of an will be delivered in early 1979 (Author) air seal on a gas turbine disc N R L Maccallum (Glasgow, University, Glasgow, Scotland) Society of Automotive Engineers, Aerospace Meeting, Los Angeles, Calif, Nov 14-17, 1977, Paper A78-23803 Army UTTAS program R A Wolfe (U S 770974 11 p 11 refs Army, Aviation Research and Development Command. St Louis, Using simple finite-difference models with appropriate boundary Mo ) Society of Automotive Engineers, Aerospace Meeting, Los conditions, methods have been developed for predicting the move- Angeles, Calif, Nov 14-17, 1977, Paper 770952 11 p 7 refs ments of the critical components of an air seal on the face of the first A brief history into the background of the Army's requirements High Pressure Turbine Disc of a typical two-spool Gas Turbine The and need for a UTTAS, history of development, general description methods have been applied to two testing transients - the accelera- with intended missions, planned activities and significant capabilities tion and the deceleration between the Ground Idling and Maximum is presented It is shown that concentrated efforts on reliability and Speeds In the acceleration, seal openings of double the equilibrium maintainability characteristics when combined with stringent per- value are predicted to persist for 30 s after completion of the speed formance and survivabihty requirements provide an aircraft with transient (Author) enhanced operational capabilities on the modern day battlefield (Author) A78 23819 Holographic inspection of jet engine composite fan blades E J Delgrosso and C E Carlson (United A78-23804 * XV-15 tilt rotor test - Progress report. J H Technologies Corp , Hamilton Standard Div , Windsor Locks, Conn ) Brown, Jr, H K Edenborough (U S Army, Aviation Research and Society of Automotive Engineers, Aerospace Meeting, Los Angeles, Development Command, Moffett Field, Calif), and D D Few Calif, Nov 14-17, 1977, Paper 770975 9p (NASA, Ames Research Center, V/STOL Aircraft Technology Div , A holographic inspection method was developed for composite Moffett Field, Calif ) Society of Automotive Engineers, Aerospace spar/shell fan blades, such as an experimental fan blade and an Meeting, Los Angeles, Calif, Nov. 14-17, 1977, Paper 770953 10 p advanced fan blade This method was employed to insure the quality In a continuing effort to expand the versatility of their aircraft, of newly fabricated blades Holographic inspection also was used to VTOL designers have for many years tried to combine the desirable indicate initiation and growth of cracks as a result of resonant fatigue features of various concepts into a single aircraft This is a formidable testing and spin testing Metallographic examinations were conducted task and most efforts have met with limited success This paper to show the good correlation between the holographic data and explores the need for an aircraft combining the efficient VTOL actual blade structures (Author) capability of a helicopter with the efficient high speed characteristics of a fixed wing turboprop The ability of the tilt rotor concept to fill A78-23820 Turbine engine slip ring technology - A survey this requirement and examples as to its potential usefulness in both J A Young, T H Gogoll, and E W Glossbrenner (Litton Industries, military and civil missions is discussed The history of the concept Poly-Scientific Div , Blacksburg, Va ) Society of Automotive Engi- and the status of the current Army/NASA/Bell XV 15 program and its role in proving the viability of the concept are reviewed (Author) neers, Aerospace Meeting, Los Angeles, Calif, Nov 14-17, 1977, Paper 770976 9 p Aircraft turbine engine development is requiring more and more A78-23805 Status report on the Advancing Blade Concept spool data to be recorded during testing This data, which normally /ABC/ technology demonstrator program V P Bailey (United consists of thermocouple and strain gage type signals, demands so Technologies Corp, Sikorsky Aircraft Div, Stratford, Conn ) many channels of quality transmission as to preclude bulky and Society of Automotive Engineers, Aerospace Meeting, Los Angeles, Calif, Nov 14-17, 1977, Paper 770954 14 p 8 refs costly telemetry devices Miniature slip ring capsule assemblies, The Advancing Blade Concept (ABC), employing a coaxial, originally developed for mertial navigation equipment, have been counter-rotating, extremely stiff rotor system, is described, the ABC adapted and used in turbine applications at speeds in excess of is intended to circumvent high-speed limitations of rotorcraft 30,000 revolutions per minute These slip ring and brush contacts are resulting from retreating blade stall Rigidly attached to the rotor characterized by low resistance variation or other electrical inter hub, the opposing advancing blades function as wings and permit ference The principal adaptation required to achieve these life times high-speed cruise, good climb characteristics, and a high degree of is the provision of an adequate coolant/lubricant supply (Author) maneuverability A flight demonstrator utilizing the ABC has attained a 156-knot velocity at 10,000 feet, and a maximum forward A78-23821 Impact of engine cycle parameters on V/STOL dive speed of 192 knots JMB Type A configuration and commonality J D Louthan (Vought

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Corp , Dallas, Tex ) Society of Automotive Engineers, Aerospace Results of a parametric test program of low pressure ratio Meeting, Los Angeles, Calif, Nov 14-17, 1977, Paper 770980 19 p deflected nozzles show the performance changes to be significant for Selection of thrust geometry, lift cruise fan parameters and the vectoring nozzles and variations in nozzle thrust coefficients should number of core engines is discussed for a Naval V/STOL aircraft be included in engine cycle trade studies to obtain realistic aircraft capable of a wide variety of missions A tandem fan design, featuring performance Low pressure ratio deflected nozzle performance is a common propulsion system, common wings and tails, and a shown t6 be sensitive to nozzle pressure ratio, nozzle contraction common basic fuselage structure for both conventional and VTOL ratio, turning radius, diffuser area ratio and the presence of an flight, is described The tandem fan propulsion system uses four fans integral core flow exhaust stream The effectiveness of venting the to generate VTOL thrust and permits compact nacelle and fan inside surface of the nozzle turn is also demonstrated (Author) design An analysis is presented to illustrate the effects of various degrees of commonality on the cost-effectiveness of V/STOL A78-23826 A clutch for V/STOL W H Thomas (General aircraft J M B Motors Corp, Detroit Diesel Allison Div , Detroit, Mich ) Society of Automotive Engineers, Aerospace Meeting, Los Angeles, Calif, Nov A78-23822 Sensitivity studies for several high perfor- 14-17, 1977, Paper 770989 9 p mance VSTOL concepts H H Driggers (Vought Corp , Dallas, Tex ) This paper describes the requirements, design, and early testing \ Society of Automotive Engineers, Aerospace Meeting, Los Angeles, of a flight weight V/STOL clutch A clutch is required between the Calif, Nov 14-17, 1977, Paper 770982 10 p \ combiner box and the forward or nose fan for some versions of Several VSTOL fighter/attack study configurations employing V/STOL aircraft This clutch has been designed to transmit 11,000 alternative propulsion concepts were evaluated to common mission, HP at fan drive speeds, and be capable of minimum engagement performance and technology groundrules This paper describes each times and rapid cycling This paper will cover the mechanical concept and compares weight sensitivities for variations in mission arrangement and control system of this clutch (Author) and combat performance constraints The lowest takeoff weight and highest performance was achieved by the vertical attitude takeoff A78-23827 Modular engine maintenance concept consider- and landing (VATOL) configurations A similar lift plus lift/cruise ations for aircraft turbine engines D B Edmunds (USAF, Propul design was typically 10 percent heavier for equal performance sion Performance/Stability Div, Wright-Patterson AFB, Ohio) Ejector and fan augmentors were not competitive with jet lift Society of Automotive Engineers, Aerospace Meeting, Los Angeles, concepts on a performance basis All configurations were capable of Calif, Nov 14-17, 1977, Paper 770991 7p vertical landing with one engine inoperative (Author) Maintenance of modular gas turbine aircraft engines is discussed, with emphasis on experience gained from the U S Air Force F100 A78-23823 * Development of the propulsion simulator - A engine, which consists of fan, core, fan drive turbine, augmentor and test tool applicable to V/STOL configurations M F Eigenmann mam gear box modules The five modules are tracked as separate (McDonnell Aircraft Co, St Louis, Mo ) and R 0 Bailey (NASA, entities in maintenance programs, resulting in more efficient fault Ames Research Center, Moffett Field, Calif ) Society of Automotive isolation and decreased repair times, though also an increase in Engineers, Aerospace Meeting, Los Angeles, Calif, Nov 14-17, 1977, record-keeping A gas path analysis program and measurements Paper 77 0984 13 p obtained from engine trim runs provide information about the A turbine engine multi-mission propulsion simulator, capable of performance of the individual engine modules Structural failure representing mlet/airframe/nozzle flowfield interactions for super- detection techniques as applied to modular engines are also men- sonic V/STOL aircraft wind tunnel models, is described The tioned J M B propulsion simulator replaces conventional aero flow-through and jet effects models with a single model, flow field interactions modeled A78-23828 Gas turbine module performance analysis A by the simulator may include close-coupled inlets and nozzles, R Ebstein (United Technologies Corp , Pratt and Whitney Aircraft non-axisymmetric vectoring exhaust nozzles, and forward canards Group, East Hartford, Conn ) Society of Automotive Engineers, mounted near the inlets and wings Wind tunnel tests of the Aerospace Meeting, Los Angeles, Calif, Nov 14-17, 1977, Paper simulation system at Mach numbers up to 12 are reported for a 770992 15p model typical of a F-15 aircraft installation The possibility of A new approach to analyzing changes in gas turbine engine applying the simulator to advanced V/STOL design programs is also module performance levels has been developed This method utilizes discussed J M B two dimensional vector space digrams and nomographs which describe module performance changes as a function of dependent gas A78-23824 The impact of emerging technologies on tacti- path parameter changes The slopes and magnitudes of the vectors cal V/STOL airplane design and utility I H Rettie and R C Sutton are determined from influence coefficients for the engine cycle being (Boeing Co , Seattle, Wash ) Society of Automotive Engineers, analyzed (Author) Aerospace Meeting, Los Angeles, Calif, Nov 14-17, 1977, Paper 770985 11 p A78-23829 Gas path analysis applied to pre and post A new look at tactical combat V/STOL design and utility as overhaul testing of JT9D turbofan engine S-G Damelsson (Scandi- affected by emerging technology and mission concepts is given in this navian Airlines System, Stockholm, Sweden) Society of Automotive paper History has shown that a certain level of useful load fraction Engineers, Aerospace Meeting, Los Angeles, Calif, Nov 14-17, 1977, must be attained before an airplane system can be considered Paper 770993 23 p operationally successful Technology trends reviewed in this paper suggest that the time is here or at least near for V/STOL tactical A78-23830 Condition monitoring experience on CF6 aircraft to achieve a truly viable useful load fraction Propulsion, engines H Kent and R Kroc Society of Automotive Engineers, structure, and controls technologies will contribute to the success of Aerospace Meeting, Los Angeles, Calif, Nov 14-17, 1977, Paper the tactical V/STOL system In addition, aerodynamic technology as 770994 23 p related to interference effects in hover and transition, and as required Condition monitoring of the CF6 aircraft engine may involve for efficient supersonic cruise and combat, significantly impacts the trend plots of gas path and mechanical parameters, spectrographic oil design solution A unique approach to system design risk assessment analysis programs, borescope inspection and radiography. Three is described with results giving technology leverage as a function of methods of obtaining trend plots are considered manual plotting design options (Author) base on flight logs and calculation sheets, semiautomatic plotting which involves computerized presentation of manually recorded A78-23825 Development of low pressure ratio vectoring data, and the Airborne Integrated Data System, which provides a nozzles for V/STOL aircraft C R Limage (Vought Corp, Dallas, complete flight record of parameters, including trends recorded Tex ) Society of Automotive Engineers, Aerospace Meeting, Los during takeoff Examples of gas path parameter trend analysis and Angeles, Calif. Nov 14-17, 1977, Paper 770988 10 p vibration data monitoring are mentioned J M B

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A78-23831 Concorde AIDS • Powerplant applications P of Automotive Engineers, Aerospace Meeting, Los Angeles, Calif, J Wheeler (British Airways, Hounslow, Middx , England) and N J Nov. 14-17, 1977, Paper 771002 10 p Essex (Rolls-Royce, Ltd, London, England) Society of Automotive A description is presented of the operation, design, per- Engineers. Aerospace Meeting, Los Angeles, Calif. Nov 14-17, 1977, formance, and application of high reliability, variable speed constant Paper 770995 18 p frequency (VSCF) aircraft electric power generating systems A high The Airborne Integrated Data System (AIDS) has been adopted frequency, multiphase, brushless generator supplies power to a as an analytic tool for Concorde propulsion system maintenance frequency converter which conditions the variable frequency genera- programs, the AIDS data are used in performance trend monitoring, tor output into precision 3-phase, 115/200V, 400 Hz aircraft power, engine control law verification, and low cycle fatigue life assess- using the cycloconverter principle Systems have been built with ments Trend plots of such parameters as rear and front vibrations, ratings from 20 to 150 kva For a 75 kva system, the weight to rating jet pipe pressure, turbine cooling air temperature and primary nozzle ratio is about 1 6 Ibs/kva and rated load efficiency is 80% Predicted area are recorded for takeoff, subsonic climb, supersonic climb, and MTBF for current systems is in the 2000 to 6000 hour range supersonic cruise (The thermodynamic parameter values are correct (Author) ed to account for the various engine inlet conditions and running A78-23837 Electronic converter electric power supply points) Objectives of the AIDS powerplant monitoring program include assessment of long-term component deterioration and avoid /ECEPS/ - KC-135 R Kautz (Bendix Corp, Electric and Fluid ance of overseas engine changes J M B Power Div , Eatontown, N J ) Society of Automotive Engineers, Aerospace Meeting, Los Angeles, Calif, Nov 14-17, 1977, Paper 771003 6p A78-23833 Twenty year evolution of the WR2/WR24 The ECEPS Package for the KC-135 aircraft is a direct series of small turbojet engines R J Mandle (Williams Research replacement for the 40 KVA CSD Generator Package that now exists Corp, Walled Lake, Mich ) Society of Automotive Engineers, in that aircraft It is a 60 KVA system and fits in the same area It Aerospace Meeting, Los Angeles, Calif, Nov 14-17, 1977, Paper consists of a gearbox, a generator, a dc link converter, and an 770998 19p air-to-oil heat exchanger The entire system is oil cooled (Author) Development of miniature turbojet engines, which have been applied to reconnaissance drone propulsion, is described At their A78-23838 Electromechanical flight control actuation D origin in the late 1950s, the miniature turbojet engine created 50 Ib K Bird (USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, of thrust, while present models are capable of more than 200 Ib of Ohio) Society of Automotive Engineers, Aerospace Meeting, Los thrust Particular attention is given to the integrated governor and Angeles, Calif, Nov 14-17, 1977, Paper 771004 10 p alternator assembly incorporated in the small turbojets Recently, a Electromechanical actuation design, recently revolutionized by miniature turbojet engine has been developed with the capability of a the introduction of rare-earth samarium-cobalt magnets, now offers one hour flight, a maximum altitude of 20,000, and variable-speed the possibility of efficient electromechanical actuation for flight flight The advanced design employs oil mist lubrication and is control Weight, space and power requirements of electromechanical intended to be reusable up to 20 times following recovery in sea actuators are compared with those of hydraulic actuators An water J M B electromechanical actuator to drive a trailing edge control surface is described, fail-safe measures designed to insure that the surface does A78-23834 Design and analysis of propellers for tow not become a flutter exciter are also considered In addition, the Reynolds number application to mim-RPV's. H V Borst Society of difficulty of reconciling maximum instantaneous horsepower require- Automotive Engineers, Aerospace Meeting, Los Angeles, Calif, Nov ments and the need for low weight actuators is mentioned J M B 14-17, 74177, Paper 770999 "27" p 27~ refs Grant No DAAJ02 C-0031 A78-23839 Flight testing an 8000 psi Lightweight Hydrau- This report presents the design and analysis of propellers applied lic System J N Demarchi (Rockwell International Corp, El to mim-remotely piloted vehicles along with the methods used Segundo, Calif) and J Ohlson (U S Naval Material Command, Naval Modifications to the airfoil data used for predicting the profile drag Air Development Center, Warmmster, Pa ) Society of Automotive losses were necessary to account for operation at the low Reynolds Engineers, Aerospace Meeting, Los Angeles, Calif, Nov 14-17, 1977, number encountered by mmi-RPV propellers The correction was Paper 771007 15 p 9 refs determined from the available airfoil data and low Reynolds number This paper describes the flight testing of an 8000 psi Light- propeller test data Using the revised methods of propeller analysis, weight Hydraulic System The objective was to reduce weight and optimum propellers were designed and analyzed The study showed space requirements of the hydraulic system in future, high density that improved performance can be obtained with new propeller Navy aircraft An 8000 psi Lateral Control System was installed in a designs (Author) T-2C (basic Navy trainer) airplane Four different pilots evaluated the test installation, accumulating a total of 11 5 flight hours No A78-23835 Constant speed generating systems J V Burns malfunctions occurred in the 8000 psi system, pilot comments were (Sunstrand Aviation Corp , Rockford, III ) Society of Automotive favorable Operational characteristics of the 8000 psi system were Engineers, Aerospace Meeting, Los Angeles, Calif, Nov 14-17, 1977, very similar to the T-2C 3000 psi lateral control system The test Paper 771001 17 p installation performed exceptionally well, fluid temperatures were Synchronous generators operating at constant speed are used to nominal, pressure fluctuations were small, fluid paniculate genera- supply the electric power systems of most modern aircraft The tion was low, and component endurance was projected to be constant speed salient pole generator inherently develops the output satisfactory (Author) power in the desired form, a sine wave of 400 hertz frequency The hydromechamcal constant speed drive, a straightforward, rugged A78-23840 * Preliminary QCSEE program - Test results C combination of a planetary gear set and hydraulic units, is most C Ciepluch (NASA, Lewis Research Center, Cleveland, Ohio) frequently chosen to achieve the constant speed The design of the Society of Automotive Engineers, Aerospace Meeting, Los Angeles, constant speed generating system has evolved through experience, Calif, Nov 14-17, 1977, Paper 771008 11 p development, and state-of-the-art advances The current system, the Preliminary results are reported for the Quiet Clean Short haul integrated drive generator, has the advantages of weight, perfor- Experimental Engine (QCSEE) program initiated by NASA in 1974 mance, reliability, and ease of maintenance Continued engineering to develop propulsion system technology suitable for powered-lift effort is dedicated to achieving further advances (Author) short-range commercial aircraft The QCSEE technology also has applications to the proposed U S Navy V/STOL aircraft Emphasis A78-23836 Variable speed constant frequency A/SCF/ in the QCSEE program is placed on developing engines with low aircraft electrical power E B Canfield and J. W Summerford noise characteristics, in addition, the power plants are required to (General Electric Co , Aircraft Equipment Div , Utica, N Y ) Society conform to EPA 1979 pollutant emissions standards Thrust perfor-

181 A78 23841

mance, fan design, ano thrust/weight ratio are discussed for both the Two concepts are developed, one based on frequency domain over-the-wing and under-the-wmg engine configurations under study techmques'and the other using Kalman filtering These are designed JM B to interface with comparison monitors of a dual sensor-dual computer system on board the A-7D multi-mode research aircraft A78-23841 _ Advanced turboprop propulsion system reli- The structure creates a fail-operative condition after one failure and ability and maintenance cost P^C Stolp (General Motors Corp, fail safe after two for redundant pairs of like sensors and fail safe for Detroit Diesel Allison Div , Detroit, Mich ) and JVA Baum (United single sensor failures A third concept is also developed which Technologies Corp, Hamilton Standard Div , Windsor Locks, Conn ) provides fault detection and isolation through analytical redundancy Society of Automotive Engineers, Aerospace Meeting, Los Angeles, Two monitor algorithms are described, a constant or scheduled trip ^Calif.Nov 14-17, 1977, Paper 771009^18? 13>refs level criteria and a sequential likelihood ratio test (SLRT) Design The reliability and maintenance cost (R&MC) for an advanced techniques for obtaining low rms error signals and consistant turbine engine and prop-fan propulsion system is projected for high responses with parameter variations are also described Finally, speed commercial airline use in the 1990s The R&MC values are hybrid simulation is used to evaluate the performance of these compared with current turboprop values and detailed discussion of designs A combination of Concept I and II algorithms and the SLRT the advances necessary to achieve the projected R&MC is provided to monitor is recommended for further evaluation through flight test substantiate maintenance cost reductions on the order of 50 to 60% (Author) These advances include an on-condition maintenance philosophy in A78-23873 * Integrity in flight control systems P R conjunction with diagnostics to monitor system performance, Kurzhals and R Deloach (NASA, Washington, DC) In Joint improved reliability in the initial design that is consistent with airline Automatic Control Conference, San Francisco, Calif , June 22-24, usage and life requirements, improved modularity to reduce line 1977, Proceedings Volume 1 New York, maintenance time and aircraft down time, and simplified hardware in Institute of Electrical and Electronics Engineers, Inc, 1977, p conjunction with modularity to reduce shop maintenance cost 489-497 17 refs Comparison of the advanced turboprop system maintenance cost In connection with advances in technology, mainly in the with that of an advanced turbofan system shows it has competitive electronic area, aircraft flight control applications have evolved from levels (Author) simple pilot-relief autopilots to flight-critical and redundant fly-by-wire and active control systems For flight-critical implementa- A78-23842 Advanced supersonic transport propulsion tions which required accommodation of inflight failures, additional systems R A Howlett and M G Smith, Jr (United Technologies levels of redundancy were incorporated to provide fail-safe and Corp , Pratt and Whitney Aircraft Group, East Hartford, Conn ) fail-operative performance The current status of flight control Society of Automotive Engineers, Aerospace Meeting, Los Angeles, systems reliability is examined and high-reliability approaches are Calif .Nov 14-17, 1977, Paper 771010 18 p discussed Attention is given to the design of ring laser gyros and A Supersonic Cruise Airplane Research program (SCAR) has magnetohydrodynamic rate sensors, redundanc/ configurations for been initiated by NASA to evaluate the performance of various component failure protection, improvements of hydraulic actuators engines for commercial supersonic flight The mam requirement for made on the component level, integrated actuators, problems of the engines is that they combine high thrust capability with low software reliability, lightning considerations, and failure detection noise The most important parameter in this regard is the bypass methods for component and system failures G R ratio All other aircraft parameters must be designed around bypass ratio performance Different Variable Cycle Engines (VCE) are A78-23879 Filtered sequential regression parameter identi- evaluated, including front, rear, and dual valve VCE's, low-bypass fication applied to a gas turbine engine model D E Warner and E engines, turbofan, and ramjet engines The most promising concept is D Ward (Purdue University, West Lafayette, Ind ) In Joint the Variable Stream Control Engine (VSCE) because it meets the Automatic Control Conference, San Francisco, Calif , June 22-24, performance requirements mentioned above, and can operate ef- 1977, Proceedings Volume 2 New York, ficiently over a wide range of temperatures, at both sonic and Institute of Electrical and Electronics Engineers, Inc, 1977, p supersonic speeds D M W 697-703 14 refs A78-23843 * Ramjet propulsion for single-stage-to-orbit In this paper a filtered sequential regression parameter identifi- vehicles J A Martin (NASA, Langley Research Center, Hampton, cation technique is developed which is feasible for on-board digital Va ) Society of Automotive Engineers, Aerospace Meeting, Los computer implementation on gas turbine engines When applied to a Angeles, Calif, Nov 14-17, 1977, Paper 771011 7p test second order system, this filtered sequential technique is The concept of single stage earth-to-orbit transportation is superior to a nonfiltered sequential technique for noisy data The studied with respect to existing and projected ramjet technology practicality of the technique is demonstrated by application to data Four types of ramjet are analyzed fan ejector, fan ramjet, supersonic generated from a twin-spool gas turbine engine model A simplified combustion ramjet, and fan ramjet with turbojet boosters A fan linear set point model was identified using the two spool speeds as ramjet with a removable fan, with separate rockets for the state variables The model obtained with this filtered sequential non-air-breathing flight phase, is considered superior to an ejector regression technique matched the system state response to within 2 ramjet, for both ease of orbit insertion and payload boost capability percent accuracy (Author) Vehicle design is also discussed in terms of trajectory integration and optimization, aerodynamic trim and stability, and complete mass A78-23883 * New frequency domain methods for system estimation Graphs are presented showing Mach number for air- identification N K Gupta (Systems Control, Inc , Palo Alto, Calif ) breathmg and non-air-breathing flight, specific impulse from various In Joint Automatic Control Conference, San Francisco, Calif, June ramjet engines, and orbital-insertion parameters D M W 22-24, 1977, Proceedings Volume 2 New York, Institute of Electrical and Electronics Engineers, Inc, 1977, p A78-23862 Sensor failure detection using analytical redun- 804-808 10 refs Contracts No N00014-76-C-0420, No NAS2- dancy T B Cunningham (Honeywell, Inc , Minneapolis, Minn ) and 8799 R D Poyneer (USAF, Flight Dynamics Laboratory, Wright- This paper presents two new techniques for frequency domain Patterson AFB, Ohio) In Joint Automatic Control Conference, San identification of linear system parameters The first technique uses Francisco, Calif, June 22-24, 1977, Proceedings Volume 1 the instrumental variables approach The frequency domain formula- New York, Institute of Electrical and Electronics tion is shown to give a considerable insight into the selection of Engineers, Inc, 1977, p 278-287 29 refs Contract No efficient and convergent instrumental variables The new maximum F33615-76-C-3031 likelihood formulation affords simpher numerical solution and Analytical redundancy is investigated to replace costly re- provides a way to select parameter starting values in the gradient dundant sensors currently needed to maintain reliable flight control based optimization method (Author)

182 A78-23901

A78-23889 System identification principles applied to New York, Institute of Electrical and Electronics Engineers, Inc, multivanable control synthesis of the F100 turbofan engine R L 1977, p 1029-1037 12 refs De Hoff and W E Hall. Jr (Systems Control, Inc , Palo Alto, Calif) Minimum time accelerations of the F100 turbofan engine are In Joint Automatic Control Conference, San Francisco, Calif, June presented A piecewise-lmear engine model, having three state 2224, 1977, Proceedings Volume 2 New York, variables and four control variables, is used to obtain the minimum- Institute of Electrical and Electronics Engineers, Inc, 1977, p time solutions The linear model which applies at a given time in the 1007-1012 8 refs Contract No F33615-75-C-2053 trajectory is determined by calculating a normalized 'distance' from An evaluation of engine control technology has demonstrated the current state to the equilibrium state associated with each linear that engine functions for future aircraft engine requirements should model The linear model associated with the closest equilibrium be implemented with digital, multivanable designs relying on point is then used The control histories for the minimum-time hydromechanical hardware for back-up and fail-operate functions solutions are used as input to a nonlinear simulation of the F100 One potential tool for achieving these objectives is based on engine to verify the accuracy of the piecewise-lmear solutions quadratic synthesis methods A description is presented of two types (Author) of algorithms which produce linear models for control synthesis on turbine engines The offset derivative procedure requires a detailed A78-23893 * Optimal controls for an advanced turbofan nonlinear digital simulation Models generated represent simulation engine G L Slater (Cincinnati, University, Cincinnati, Ohio) In variables and dynamics, and a reduction procedure is required to Joint Automatic Control Conference, San Francisco, Calif, June produce low order design systems These procedures are computa- 2224, 1977, Proceedings Volume 2 New York, tionally efficient but may be sensitive to system nonlmeanties and Institute of Electrical and Electronics Engineers, Inc, 1977, p perturbation step size System identification procedures are com- 1038-1043 10 refs Contract No NAS3-18021 putationally more demanding The resulting models tend to represent Linear optimal control theory is applied to the control synthesis the behavior of the engine over a wider range of input magnitudes of a high bypass ratio, variable pitch, turbofan engine The basic and trim conditions G R control philosophy is to use only a low order dynamic model of the plant coupled with the concept of integral-output states so as to A78-23890 * Frequency domain compensation of a maintain control simplicity yet guarantee integral control of thrust, DYNGEN turbofan engine model R M Schafer, R R Ge|ji, P W turbine temperature and other important engine outputs Linear Hoppner, W E Longenbaker, and M K Sam (Notre Dame, simulation results indicate that the control system developed University, Notre Dame, Ind ) In Joint Automatic Control Con- provides rapid control of small thrust perturbations and_ quickly ference, San Francisco, Calif, June 22-24, 1977, Proceedings eliminates the effect of unmodelled thrust and temperature distur- Volume 2 New York, Institute of Electrical and bances Large thrust accelerations are obtained in about one half Electronics Engineers, Inc, 1977, p 1013-1018 Srefs NSF Grant second while the control maintains negligible overshoot in tempera- No ENG-75-22322, Grant No NsG-3048 ture and stall margins (Author) Following Rosenbrock's ideas regarding the advantages of dominance in linear multivanable control systems, a new graphical A78-23900 A singular perturbation analysis of optimal technique is used for the design of compensators that achieve aerodynamic and thrust magnitude control A J Calise (Dynamics dominance The technique is illustrated with an application to the Research Corp, Wilmington, Mass ) In Joint Automatic Control problem of designing compensators for a linear turbofan-engme Conference, San Francisco, Calif, June 22-24, 1977, Proceedings model The resulting design is put into perspective by examining it in Volume 2 New York, Institute of Electrical and the light of two other multivanable frequency-domain methods One, Electronics Engineers, Inc, 1977, p 1248-1260 19 refs Contract MacFarlane's method of characteristic loci, is used to realize a final No F49620-76-C-0037 design for stability and low interaction The other is a direct This paper illustrates the application of singular perturbation technique based upon the algebraic expansion of the determinant of methods to optimal thrust magnitude control (TMC) and optimal lift the return difference in terms of it's elements Results from control in flight mechanics A multiple time scale analysis results in simulations carried out on the NASA DYNGEN software are nonlinear feedback control solutions for lift and thrust during a turn included (Author) to a specified down range position The analysis is carried out to first order with respect to the position state variables Numerical results for a medium range and a short range air-launched missile are given, A78-23891 * The application of the Routh approximation and comparisons are made to two alternative propulsion control method to turbofan engine models W C Merrill (NASA, Lewis concepts The multiple time scaling procedure used here is applicable Research Center, Cleveland, Ohio) In Joint Automatic Control to solving a wide class of optimal control problems It avoids the Conference, San Francisco, Calif, June 22-24, 1977, Proceedings problem in asymptotic methods of picking the unknown adjomts to Volume 2 New York, Institute of Electrical and suppress unstable modes in the boundary layer and reduces the Electronics Engineers, Inc, 1977, p 1019-1028 9 refs two-point boundary value problem to a series of point-wise function The Routh approximation technique is applied in the frequency extremizations Hence the optimal control solution is essentially domain to a 16th order state variable turbofan engine model The analytic and algebraic (Author) results obtained motivate the extension of the frequency domain formulation of the Routh method to the time domain to handle the A78-23901 Singular perturbation analysis of optimal flight state variable formulation directly The time domain formulation is profiles for transport aircraft R Aggarwal, A J Calise, and F derived and a new characterization, which specifies all possible Goldstein (Dynamics Research Corp, Wilmington, Mass ) In Joint Routh similarity transformations, is given This characterization is Automatic Control Conference, San Francisco, Calif, June 22-24, computed by the solution of two eigenvalue-eigenvector problems 1977, Proceedings Volume 2 New York, Insti- The application of the time domain Routh technique to the state tute of Electrical and Electronics Engineers, Inc, 1977, p variable engine model is described and some results are given 1261-1269 10 refs Contract No F33615-76-C-3104 Additional computational problems are discussed including an This paper carries out a multiple time scale analysis of optimal optimization procedure which can improve the approximation flight profiles for transport aircraft Nonlinear feedback solutions for accuracy by taking advantage of the transformation characterization the optimum altitude and throttle setting as a function of the aircraft (Author) energy state are derived The analysis takes into account the decrease in aircraft weight as fuel is consumed during the flight It is shown A78-23892 * Minimum-time acceleration of aircraft turbo- that a f'rst order analysis corrects the optimal control solution for fan engines F Teren (NASA, Lewis Research Center, Cleveland, fuel consumption during climb Numerical results for a C-141 aircraft Ohio) In Joint Automatic Control Conference, San Francisco, for short range and long range profiles are given These are compared Calif . June 22-24, 1977, Proceedings Volume 2 to a gradient solution for the full state problem The paper concludes

183 A78-23906

with a discussion on the real time implementation aspects of the aircraft The design of the flare control is formulated as an LQSF optimal control algorithm (Author) tracking problem SD

A78-23906 Failure state detection of aircraft engine out- A78-23918 * # Failure detection and correction for turbofan put sensors W R Wells (Wright State University, Dayton, Ohio) and engines R C Corley (General Electric Co , Group Engineering Div , C W de Silva (MIT, Cambridge, Mass ) In Joint Automatic Control Cincinnati, Ohio) and H A Spang, III (GE Research and Develop- Conference, San Francisco, Calif, June 22-24, 1977, Proceedings ment Center, Schenectady, N Y ) AlChE, ASME, IEEE, ISA, and Volume 2 New York, Institute of Electrical and SME, Joint Automatic Control Conference, San Francisco, Calif, Electronics Engineers, Inc , 1977, p 1493-1497 9 refs June 22-24, 1977, Paper 7p Contract No NAS3-18021 In this work a technique to detect the failure state of aircraft In this paper, a failure detection and correction strategy for engine output sensors is developed The technique automatically turbofan engines is discussed This strategy allows continuing control makes optimal estimates of the outputs corresponding to failed of the engines in the event of a sensor failure An extended Kalman states These estimates can in turn be used to control the engine until filter is used to provide the best estimate of the state of the engine the normal operation of engine sensors is restored The technique is based on currently available sensor outputs Should a sensor failure then applied to a realistic turbojet engine model (Author) occur the control is based on the best estimate rather than the sensor output The extended Kalrnan filter consists of essentially two parts, A78-23907 * Design of turbofan engine controls using out- a nonlinear model of the engine and up-date logic which causes the put feedback regulator theory W C Merrill (NASA, Lewis Research model to track the actual engine Details on the model and up-date Center, Cleveland, Ohio) In Joint Automatic Control Conference, logic are presented To allow implementation, approximations are San Francisco, Calif, June 22-24, 1977, Proceedings Volume 2 made to the feedback gain matrix which result in a single feedback New York, Institute of Electrical and Electronics matrix which is suitable for use over the entire flight envelope The Engineers, Inc , 1977, p 1504-1509 9 refs effect of these approximations on stability and response is discussed A multivanable control design procedure based on output Results from a detailed nonlinear simulation indicate that good feedback regulator (OFR) theory is applied to the F100 turbofan control can be maintained even under multiple failures (Author) engine Results for the OFR design are compared to a design based on linear quadratic regulator (LOR) theory This LQR design was A78-24007 # Approaches to improving aircraft efficiency obtained as part of the FIDO Multivanable Control Synthesis C J SIivmsky (Rockwell International Corp , General Aviation Div , (MVCS) program In the MVCS program the LQR feedback control Bethany, Okla ) American Institute of Aeronautics and Astro- was designed in a reduced dimension state space and then applied to nautics, Annual Meeting and Technical Display, 14th, Washington, the original system However, the OFR feedback control is designed DC.Feb 7-9, 1978, Paper 78-305 4 p in the full order state space and thus eliminates any need for model Investigations have been conducted concerning the approaches reduction techniques Using the performance measure and control which can be used to increase the cost effectiveness of general structure of the MVCS program LQR design, an equivalent OFR aviation type aircraft It was found that the utilization of larger feedback control is obtained The flexibility of the OFR as a control propellers turning more slowly develops the highest thrust per design procedure is demonstrated and differing feedback control horsepower ratio The employment of such propellers in connection structures are evaluated (Author) with aerodynamic and material improvements being developed will permit aircraft to go faster and carry more payload while flying at A78-23909 * Solution of transient optimization problems higher altitudes for longer periods of time Turboprop engines have by using an algorithm based on nonlinear programming F Teren demonstrated both a lighter weight per horsepower and a higher (NASA, Lewis Research Center, Cleveland, Ohio) In Joint Auto- degree of reliability than higher powered piston engines Configura- matic Control Conference, San Francisco, Calif, June 22-24, 1977, tions which use two turboprop engines driving a single propeller and Proceedings Volume 2 New York, Institute of tied together by a combined gear box offer twin engine reliability Electrical and Electronics Engineers, Inc, 1977, p 1549-1560 11 and could obtain aircraft efficiency well beyond those presently refs available G R A new algorithm is presented for solution of dynamic optimization problems which are nonlinear in the state variables and linear in A78-24008 # Engine development toward lower energy con- the control variables It is shown that the optimal control is sumption and reduced environmental impact E L Smith and H R bang-bang A nominal bang-bang solution is found which satisfies the Bishop (Pratt and Whitney Aircraft of Canada, Ltd , Longueuil, system equations and constraints, and influence functions are Quebec, Canada) American Institute of Aeronautics and Astro- generated which check the optimality of the solution Nonlinear nautics, Annual Meeting and Technical Display, 14th, Washington, optimization (gradient search) techniques are used to find the DC.Feb 7-9, 1978, Paper 78-307 12 p 7 refs optimal solution The algorithm is used to find a minimum time The paper discusses the current state of development of small acceleration for a turbofan engine (Author) gas turbine engines for General Aviation Areas examined include powerplant types, developments in component efficiency and prob- A78-23917 * Robustness of linear quadratic state feedback able future improvements Over the next 10 year period, small gas designs in the presence of system uncertainty R V Patel, M Toda, turbine engines are expected to evolve further towards still lower fuel and B Sndhar (NASA, Ames Research Center, Moffett Field, Calif ) consumption, continued high reliability, low operating cost and In Joint Automatic Control Conference, San Francisco, Calif, June minimum environmental impact in terms of noise and emissions 22-24, 1977, Proceedings Volume 2 'New York, Fixed wing powerplants are addressed in the paper but the engine Institute of Electrical and Electronics Engineers, Inc, 1977, p improvements considered will be equally applicable to helicopter 1668-1673 15 refs powerplants (Author) The paper deals with the problem of expressing the robustness (stability) property of a linear quadratic state feedback (LQSF) design quantitatively in terms of bounds on the perturbations A78-24009 # Flight on 0 33 horsepower - The Gossamer (modeling errors or parameter variations) in the system matrices so Condor P B MacCready (AeroVironment, Inc, Pasadena, Calif) that the closed-loop system remains stable Nonlinear time-varying American Institute of Aeronautics and Astronautics, Annual Meeting and linear time-invariant perturbations are considered The only and Technical Display, 14th, Washington, D C. Feb 7-9, 1978, computation required in obtaining a measure of the robustness of an Paper 78-308 7 p LQSF design is to determine the eigenvalues of two symmetric Flight testing experience and performance calculations are matrices determined when solving the algebraic Riccati equation discussed for a human-powered aircraft which won the Kremer Prize corresponding to the LQSF design problem Results are applied to a in 1977 The aircraft is based on computer aided propeller and airfoil complex dynamic system consisting of the flare control of a STOL designs, the structure consists of Mylar over aluminum tubing with

184 A78-24O18

piano wire for support The 96-foot span vehicle, having a gross Ind ) American Institute of Aeronautics and Astronautics, Annual weight of 207 Ibs, performed the 7 1/2 minute flight (including a Meeting and Technical Display, 14th, Washington, D C, Feb 7-9, figure-eight maneuver) at an average power of 0 42 horsepower 1978, Paper 78-312 9p 12refs J M B A review of the aircraft trailing vortex system is presented Particularly the transport and decay of the vortex system and its A78-24010 H Conversion of an automotive engine for air- potential hazard to other aircraft is discussed In addition an analysis craft application L J Yuhas (Rutgers University, New Brunswick, of trailing vortex decay data is presented Although various theories NJ, General Electric Co, Aircraft Engine Div, Cincinnati, Ohio) have been proposed for predicting the decay of a vortex system, and G E Sumka (Rutgers University, New Brunswick, N J , General most of them have failed when compared with flight test data Electric Co , Technical Marketing Div , Bridgeport, Conn ) American Recently Iversen proposed a method for correlating trailing vortex Institute of Aeronautics and Astronautics, Annual Meeting and data based upon a variable eddy viscosity vortex decay model His Technical Display, 14th, Washington, D C, Feb 7-9, 1978, Paper model was applied to previously uncorrelated flight test data The 78-309 8p 10refs data used, which was obtained by the National Aviation Facilities Experimental aircraft require lightweight, dependable, and low Experimental Center (NAFEC), includes measurements of the vortex cost power plants Automotive internal combustion engines may be structure behind nearly all the large commercial jet transports The used for this application In this investigation, an air cooled Corvair correlation technique was found to successfully collapse the trailing automotive engine was selected for possible conversion To develop a vortex data to a single curve Thus, Iversen's assumption of variable high torque at low crankshaft speeds without gear reduction, several eddy viscosity is the key factor that enables a universal collapse of modifications were considered These changes included exhaust both the model and flight test data (Author) system modifications to reduce exhaust manifold back pressures, carburetor modification which allows for controlled air-fuel mixtures, and modification of the ignition system to dual-magneto A78-24016 # VSTOL - Can Navy needs be met D F Mow ignition which increased performance and dependability The paper (US Navy, Office of the Chief of Naval Operations, Washington, describes these modifications and their effects on the converted D C ) American Institute of Aeronautics and Astronautics, Annual power plant's performance (Author) Meeting and Technical Display, 14th, Washington, D C, Feb 7-9, 1978, Paper 78-322 6 p A78-24011 tf A solution to the direct problem of an open The U S Navy has made the decision to transition its Sea Based propeller using the streamline curvature method M J Pierzga Air forces to VSTOL This decision is subject only to a validation (Pennsylvania State University, State College, Pa ) American that the VSTOL concept of operations will satisfy the Navy's needs Institute of Aeronautics and Astronautics, Annual Meeting and A broad matrix of studies are ongoing to investigate thoroughly the Technical Display, 14th, Washington, DC, Feb 7-9, 1978, Paper role that VSTOL aircraft can play in the Navy of the future VSTOL 78-3W 9p 9refs permits greater flexibility in aircraft carrier design and extends the A method is presented of analyzing the flow field and predicting advantages of Sea Based Air across a broader spectrum of ships the performance characteristics of an open propeller The flow field Greater tactical flexibility and strategic mobility are available to the is calculated using the streamline curvature method, an iterative task force commander and higher authority in operating naval forces procedure which simultaneously satisfies the principles of conserva in support of national policy (Author) tion of total energy, momentum and continuity The direct problem solution requires the calculation of the outlet flow angles for the A78-24017 # 'New look' in assurance technology - The propeller blade sections These flow angles are a combination of the Hornet' D Malvern and J P Capellupo (McDonnell Aircraft Co , St measured blade outlet angles and the deviation angles due to real Louis, Mo ) American Institute of Aeronautics and Astronautics, fluid effects The method of calculating these deviation angles is Annual Meeting and Technical Display, 14th, Washington, D C, Feb described in detail Once the flow field has been established, the 7-9, 1978, Paper 78-323 6 p propeller performance parameters can then be calculated using Assurance technology, i e , the reliability and maintainability of simple momentum and energy considerations Good correlation aircraft, has taken on an increasingly important role in light of between predicted data and experimental measurements has been concern with military spending The F/A-18 Hornet is presented as obtained using this direct analysis method (Author) an aircraft with state-of-the-art assurance technology, including A78-24012 ff Digital simulation of aircraft flight path built-in-test and on-aircraft maintenance, providing rapid fault- dynamics using quaternions R J Goodman (Virginia Polytechnic isolation, short repair time, and low failure rates Deployment of the Institute and State University, Blacksburg, Va ) American Institute F/A-18 during the 1980's is expected to substantially reduce aircraft of Aeronautics and Astronautics, Annual Meeting and Technical down-time, and allow for efficient operation over a wide range of Display, 14th, Washington, D C, Feb 79, 1978, Paper 78-311 12 p environments D M W 7refs A summary is presented on the development of a computer program which provides a flexible inexpensive easy-to-use tool for A78-24018 H Airborne electronic warfare in the modern solving general vehicle performance problems The equations used in military force A R Salzmann (Grumman Aerospace Corp, describing the instantaneous dynamic motions of a vehicle in flight Bethpage, N Y ) American Institute of Aeronautics and Astro- are reviewed However, the description obtained from these equa- nautics, Annual Meeting and Technical Display, 14th, Washington, tions is incomplete due to mathematical singularities at vehicle D C.Feb 7-9, 1978, Paper 78-324 10 p flight-path angles of + or - 90 deg This incompleteness is eliminated The development of electronic warfare is traced from its by introducing the concept of the quaternion as an unambiguous beginnings in World War 2 to the present oay Attention is given to means of representing body orientations The incorporation of the Navy EA 6B and the Air Force EF-111 A, designed for the F-111 quaternions into the equations of motion is discussed in detail Brief aircraft These jamming systems are seen as operating in three basic comments are also made on the structuring of the program to give a modes barrier stand-off, in which a few F 11 Ts operate in a holding better understanding of its adaptability to solve a wide range of pattern behind friendly lines and foil enemy reconnaissance of our performance problems and yet still be simple and inexpensive to use own forces, close air support, where F 111 's venture just over enemy The validity of the program's solutions for different performance lines and jam enemy radar so that tactical aircraft can strike at their problems is then illustrated by comparing the results from modeling targets, and penetration escort, in which electronic warfare is several flight paths directly with solutions obtained using other conducted well behind enemy lines Modern electronic warfare performance analysis techniques (Author) systems are fully integrated into the operation of an aircraft^digitally controlled, and computerized to handle routine chores, so that the A78-24013 " An analysis of the aircraft trailing vortex human operator can deal with the unusual and the unexpected system J J Tartaglione (Notre Dame, University, Notre Dame, D MW

185 A78-24022

A78-24022 ff A least square finite element technique for on an informed understanding of user characteristics This paper transonic flow with shock A R Wadia (Cornell University, Ithaca, provides an overview of several facets of commercial aviation fuel N Y ) American Institute of Aeronautics and Astronautics, Annual consumption the merits of its public services, the conservation Meeting and Technical Display, 14th, Washington, D C, Feb 7-9, measures taken to date, the consequences of future shortages, energy 1978, Paper 78-328 13 p 18 refs Grant No AF-AFOSR-74-2659 conservation strategies, modal efficiency comparisons, and alternate The governing differential equation for the one-dimensional, fuel considerations The conclusion is reached that commercial transonic flow in a laval nozzle in the vicinity of the throat was aviation should be designated as a high-priority user of petroleum obtained in the non-dimensional form A least square finite element fuels in any government allocation program (Author) technique was used with a linearly interpolating polynomial to reduce the governing equation to a system of non-linear algebraic A78-24033 ff Planning for the next generation aircraft - An equations which were solved numerically by Newton's method The airline view D J Lloyd Jones (American Airlines, Inc , New York, system of partial differential equations for the two dimensional flow N Y ) American Institute of Aeronautics and Astronautics, Annual in a laval nozzle was also obtained in the non-dimensional form The Meeting and Technical Display, 14th, Washington, D C, Feb 7-9, method of integral relations was used to replace the original system 1978, Paper 78-361 9p of partial differential equations by a system of ordinary differential External factors such as fuel costs and government regulations, equations Using the least square finite element technique a specifically. Part 36 noise requirements, play a decisive role in airline computer program was developed for the construction and solution plans for aircraft procurement The American Airlines fleet is of the non-linear equations for the laval nozzle problem The results evaluated in terms of composition and profitability through the year including the location of the shock in the flow are presented 1984 In order to comply with Part 36, the airline has three options (Author) other than scrapping its 707's completely retrofit, re-engimng, and gradual replacement of older aircraft types, i e outfitting the fleet A78-24025 /?' An investigation into the effects of shear on with current wide-body aircraft Load factors and operating costs are the flow past bluff bodies C Piscina American Institute of analyzed, and new technologies, such as improved engines and Aeronautics and Astronautics, Annual Meeting and Technical Dis- composite-materials, are discussed as ways to increase profitability play, 14th, Washington, DC, Feb 7-9, 1978, Paper 78-331 10 p 11 DMW refs NSF Grant No GK-42991 A78-24034 # The challenge of advanced fuel-conservative A curved screen was used to produce a low-turbulence shear aircraft - A manufacturer's view R E Hage and J A Stern (Douglas flow in a wind tunnel test section The turbulence intensity was less Aircraft Co , Long Beach, Calif ) American Institute of Aeronautics than 0 5%, and a 20% linear shear profile was produced Experiments and Astronautics, Annual Meeting and Technical Display, 14th, were performed on four rectangular cylinders 60, 45, 30, and 15 cm Washington, D C, Feb 7-9, 1978, Paper 78-362 18 p in height with 2 1 and 1 2 aspect ratios Measurements were made to Costs and technological problems associated with advanced determine the frequency of vortex shedding in the wake of the fuel-conservative aircraft are discussed, with particular attention model with shear and without shear Frequency measurements of the given to the current NASA Aircraft Energy Efficiency (ACEE) vortex shedding showed a number of cells across the span of the program, which focuses on engine component improvement, cylinder, each with a different frequency The flows were influenced turboprops, laminar flow control and composites In addition to the strongly at the top of model due to the finite height The cells results of the ACEE program, aircraft manufacturers will need to boundaries fluctuated with time At certain times the frequency deal during the next decade with the noise requirements established spectra showed a broadening with dual peak frequencies corre- by FAR Part 36 Due to high costs and noise considerations, DCS sponding to the unsteadiness in cell structure (Author) and 8707 fleets are expected to be replaced by the 1980s, and the demand for fuel-efficient aircraft in the 100- to 200-seat category A78 24031 # Technology readiness for an SST R D will be significant Fuselage cross sections for such a category are FitzSimmons (Douglas Aircraft Co , Long Beach, Calif ) American considered, a comparison of the effectiveness of twin-jets and tn-jets Institute of Aeronautics and Astronautics, Annual Meeting and for medium-range transport is also reported J M B Technical Display, 14th, Washington, DC, Feb 7-9, 1978, Paper 78-356 7p 16 refs A78-24035 ff Prospects for a new generation air transport J The NASA Supersonic Cruise Aircraft Research program has L McLucas (COMSAT General Corp , Washington, D C ) American identified promising solutions to the noise, range, and economic Institute of Aeronautics and Astronautics, Annual Meeting and problems which led to the cancellation of the previous U S Technical Display, 14th, Washington, D C, Feb 7-9, 1978, Paper supersonic transport research program However, the NASA program 78-363 7 p has not been large enough to prove that the solutions are viable Such The market for new technology airplanes is good and new proof requires large-scale development testing The results of the designs will be offered in 1978 Airlines earnings are up but still recent efforts are illustrated by examining the improvements inadequate for fleet replacement Legislation to permit ticket tax obtained in a hypothetical airline aircraft Relative to the Concorde a revenues to go to new aircraft purchase is likely as is limited 50-percent increase in range can be shown, which would open up regulatory reform Recent CAB flexibility on routes and fares is practical, supersonic operations for the Pacific where distances are encouraging Both government and private actions to keep foreign great and the savings in travel time are very large The aircraft markets open is essential Purchases of new airplanes sparked by payload could be significantly increased, shown here at 250 traffic growth and replacement of 'non-complying' noisy aircraft can passengers, which directly improves operating economics G R lead to $50B market over next decade (Author)

A78-24032 # Fuels outlook I - Transportation and the U S A78-24085 ff Successive-approximation calculation of a petroleum resource, an aviation perspective M P Miller and R A steady subsonic gas flow about an airfoil lattice (Raschet statsionar- Mays (Boeing Commercial Airplane Co , Seattle, Wash ) American nogo obtekaniia reshetki profilei dozvukovym potokom gaza meto- Institute of Aeronautics and Astronautics, Annual Meeting and dom posledovatel'nykh priblizhenn) V P Riabchenko (Akademiia Technical Display, 14th, Washington, DC, Feb 7-9, 1978, Paper Nauk SSSR, Institut Gidrodmamiki, Novosibirsk, USSR) Akademiia 78-357 11 p 24 refs Nauk SSSR, Sibirskoe Otdelenie, Izvestua, Serua Tekhnicheskikh The U S commercial aviation industry is meeting the continuing Nauk, Oct 1977, p 11-15 6 refs In Russian challenges of reduced fuel consumption, higher fuel prices, and increased passenger traffic A disturbing fact is that the country has A78-24096 ft Calculation of the three-dimensional super- become increasingly dependent on imported petroleum fuels In the sonic viscous heat-conducting gas flow past blunted bodies (Raschet event that import restrictions are imposed or that some form of prostranstvennogo obtekaniia zatuplennykh tel sverkhzvukovym rationing is required, federal fuel-allocation policies should be based potokom viazkogo i teploprovodiashchego gaza) V E Kanakm and

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F D Popov Zhurnal Vychislitel'noi Matematiki i Matematicheskoi (Tiagovye kharaktenstiki sistern UVT so vduvom khimicheski Fiziki,vo\ 17, Nov Dec 1977, p 1545-1555 6 refs In Russian neitral'nykh gazov) B S Vinogradov and Z G Shaikhutdinov Approaches to the numerical solution of the three-dimensional Aviatsionnaia Tekhnika, vol 20, no 3, 1977, p 23-29 In Russian supersonic flow problem under consideration are studied, treating The thrust characteristics of thrust vector control systems which the shock wave as a discontinuity surface and assuming that the employ secondary nonsymmetncal injection of gas into the super- simplified Navier-Stokes equations containing only the terms of the sonic jet-engine nozzle were determined experimentally Various test inviscid-flow and boundary-layer equations are valid in the entire setups were used, distinguished by the type of working gas air, region of the flow Results of calculations of a M = 4 flow at an angle combustion products of air and kerosene, combustion products of of 10 degrees past an ellipsoid of revolution with an axial ratio of 1 5 air, kerosene and AI2O3, and combustion products of a solid fuel are analyzed, along with results obtained at Re = 3333, 1000, and The effects of various structural and operational conditions on the 333 for the case of a heat-insulated surface and a surface with a given thrust characteristics were determined by studying two major thrust temperature V P parameters the gam coefficient and the quality coefficient B J

A78-24149 # The start-up of a gas turbine engine using A78-24259 ff The effect of fluid oscillations in a fuel line on compressed air tangentially fed onto the blades of the basic turbine the pressure head of a pump operating in a regime without reverse (Zapusk GTD szhatym vozdukhom, podvodimym tangentsial'no na streams (O vlnanii kolebanu zhidkosti v toplivnoi magistrali na napor lopatki osnovnoi turbiny) L I Slobodianiuk and V I Daineko nasosa, rabotaiushchego na rezhimakh bez obratnykh tokov) V G (Sevastopol'skn Pnborostroitel'nyi Institut, Sevastopol, Ukrainian Kmelev Aviatsionnaia Tekhnika, vol 20, no 3, 1977, p 52-57 In SSR) Energetika, vol 20, Sept 1977, p 135-137 In Russian Russian Consideration is given to the effect of fluid self-oscillations in a A78-24156 ff Steady-state bulk temperature field in cooled fuel line on the pressure-head and cavitation flow characteristics of turbine blades (Ob'emnoe pole statsionarnykh temperatur v okhla- the pump These oscillations are conditioned by the formation of zhdaemykh lopatkakh turbinyl V I Lokai and E I Gunchenko separated vortex regions in the screw pump As pressure drops in the (Kazansku Aviatsionnyi Institut, Kazan, USSR) Inzhenerno- pump entrance, vortex regions become visible due to the appearance Fizicheskii Zhurnal, vol 33, Oct 1977, p 687693 7 refs In of cavitation in the centers of the vertices that produce these regions Russian Experimental data are examined for the case of a centrifugal It is shown how a Green's function can be used to calculate screw-pump B J steady-state bulk temperature fields in bodies of complex configuration for variable boundary conditions and a temperature dependent heat-transfer coefficient The effectiveness of the method is demon- A78-24273 n Investigation of the inclination of nozzle strated by comparing the surface and bulk temperature distributions blades on the alternating stress level in working turbine blades (thermal state) calculated for a turbine blade employing combined (Issledovame vlnanna naklona soplovykh lopatok na uroven' pere- convective and film cooling with the measured values V P mennykh napriazhenu v rabochikh lopatkakh turbiny) A A Kovalev, V A Strunkin, and I I Kurtseva Aviatsionnaia Tekhnika, A78-24252 # The effect of angle of attack on the aero- vol 20, no 3, 1977, p 129-131 In Russian damping of wing profile vibrations (Vlnanie ugla ataki na aero- dempfirovame kolebanu krylovykh profilei) V B Avdeev Avia- A78-24274 # Calculation of the thermal state of turbine blades with film cooling (K raschetu temperaturnogo sostoianna tsionnam Tekhnika, vol 20, no 3, 1977, p 11-16 In Russian turbmnykh lopatok s plenochnym okhlazhdemem) V I Lokai, E I Wind-tunnel vibration tests were performed on a turbme-blade- Gunchenko, and A V Shchukin Aviatsionnaia Tekhnika, vol 20, cascade model for flow velocities of M = 0-3 The method of determining the aerodampmg characteristics of the model consisted no 3, 1977, p 132-135 11 refs In Russian of measuring the energy dissipation of forced resonant vibrations, An analysis of experimental data is used to derive boundary first for the case without flow, then for flow with a constant level of conditions of the third kind (stipulating a local heat transfer resonant excitation Aerodampmg was characterized by an aero- coefficient for film cooling and an adiabatic wall temperature) for a dynamic vibration decrement It is found that there is no clear and turbine blade with film cooling These boundary conditions were smglevalued relationship between aerodampmg and angle of attack used to calculate the thermal stress state (temperature distributions) B J for such a blade A comparison of computational and experimental results shows that recommendations in the literature on the establishment of boundary conditions for this problem are in- A78-24253 # Theory of two frequency ranges of unstable adequate for calculating the thermal states of such blades with oscillations of turbulent combustion in a jet-engine chamber I - equired accuracy B J Formulation of the stability problem, the characteristic equation (Teorna dvukh chastotnykh diapazonov neustoichivykh kolebanu A78-24275 ff Statistical evaluation of the effect of a jet protsessa turbulentnogo gorenna v kamere reaktivnogo dvigatelia I - reverser on the parameters of a turbofan engine in the direct thrust Formulirovka zadachi ob ustoichivosti, kharaktensticheskoe uravne- regime (Statisticheskaia otsenka vlnanna reversivnogo ustroistva na nie) S K Aslanov Aviatsionnaia Tekhnika. vol 20, no 3, 1977, p parametry TRDD na rezhime priamoi tiagi) E D Nesterov, I I 17-22 7 refs In Russian Plakhova, and E L Simkin Aviatsionnaia Tekhnika, vol 20, no 3, The theory of one-dimensional perturbations is used in 1977, p 135-139 In Russian formulating the problem of stability for averaged steadystate combustion in a jet-engine chamber The physical-chemical nature of the A78-24346 The Low-Level Wind Shear Alert Program process are interpreted in the framework of time lag of evaporation Journal of Air Traffic Control, vol 19, Oct-Dec 1977, p 5-7 and ignition, the boundary conditions are acoustic conditions at the The Low Level Wind Shear Alert System has been designed as entrance and exit of the chamber and conservation laws at the part of the FAA Wind Shear program which was developed in turbulent flame front with consideration of turbulent pulsations The response to a number of airline accidents that were probably caused mathematical problem is closed by means of two relations, obtained by wind shear An analysis of such accidents revealed that substantial by varying the laws of turbulent combustion and kinetics of preflame differences existed between the reported surface winds measured at processes An eigenvalue equation is derived, describing the stability centerfield and the surface winds existing in the approach and of the combustion process B J departure corridor It was concluded that the accidents might have been prevented if the pilots had -received also prior information regarding the surface wind conditions in the approach and departure A78-24254 # Thrust characteristics of thrust vector control corridors The considered system has the objective to alert auto- systems with blowing injection of chemically nonreactive gases matically the air traffic controllers whenever a vector difference of

187 A78-24347

greater than a predetermined value exists between the reported equation where the final velocity at the end of the deployment centerfield wind and the wind at any other anemometer on the process is unknown Two expressions are derived and presented airport surface The system was installed at six airports to verify the graphically, showing that the final velocity tends quite sharply to an concept during the thunderstorm season of 1977 G R asymptotic value which determines an upper bound to the peak deployment stress S D A78-24347 Wake turbulence • Gone with the wind M ClarK (FAA, Washington, D C) Journal of Air Traffic Control, vol A78-24367 * jf Comments on 'Feasibility study of a hybrid 19, Oct-Dec 1977, p 10-12 airship operating in ground effect' M D Ardema (NASA, Ames In May 1976 a Vortex Advisory System (VAS) was installed at Research Center, Moffett Field, Calif ) Journal of Aircraft, vol 15, Chicago's O'Hare airport The VAS is based on wind measurements Feb 1978, p 126, 127, Author's Reply, p 127,128 9 refs around the airport which make it possible to predict movement and behavior of aircraft generated wake vortices The VAS installation A78-24374 A study on the capacity of runway systems includes a network of meteorological towers sited near the middle (Etude de la capacite des systemes de pistes) F Collet and Y marker locations The wind data from the anemometers on the Breant France Transports - Aviation Civile, Winter 1977-1978, p towers are transmitted to a central computer The computer 62-68 In French transmits through a digital display to the controller advising whether Models of the operational parameters of civil-aviation runways he can use reduced (3 n mi) separations in place of standard are presented in terms of a runway's ability to handle airport traffic separation between arriving aircraft NASA has been engaged in an Runway capacity is defined as the amount of time a given number of extensive research program for the aerodynamic alleviation of wake aircraft have to spend on the runway waiting to take-off, and the vortices Aerodynamic alleviation is a general term describing amount of time spent in the air waiting to land A matrix of modifications to the aircraft or airfoil to alter the vortex structure constraints is presented, together with a statistical analysis of average and thereby minimize the adverse effects of the wake G R and peak-capacity waiting times Also discussed are construction, maintenance, and time-in-service factors as they pertain to runway A78-24356 A severe downslope windstorm and aircraft use D M W turbulence event induced by a mountain wave D K Lilly (National Center for Atmospheric Research, Boulder, Colo ) Journal of the A78-24375 In-state delivery and reinforcement of rigid Atmospheric Sciences, vol 35, Jan 1978, p 59-77 17 refs airport causeways - Some technical problems and attempts using A detailed observational analysis is presented for the large-scale special coatings (Remise en etat et renforcement de chaussees rigides mesoscale, and especially the turbulent-scale features of the 11 d'aerodromes - Quelques problemes techniques et essais d'enrobes January 1972 downslope windstorm in central Colorado, USA speciaux) R Pech and G Burelle France Transports - Aviation Attention is focused on an analysis of the structure, dynamics and Civile, Winter 1977-1978, p 69-72 In French energy budget of the mid and upper tropospheric turbulence zone Airport causeways must have a high resistance to large capacity and to air safety in severe wave events It is shown that the mesoscale traffic, be able to retard cracks and fissures, be able to withstand structure of the mountain wave and windstorm system have severe changes in climate, and be easily maintained Comparisons are undergone an important oscillation in wavelength which is closely presented between standard asphalt causeways and causeways made related to the question of where and how wave momentum flux is from newer materials Epoxy-resms fulfill most design criteria, but ultimately transported to the ground The 11 January wave is found are prohibitively expensive Asphalt combined with other materials, to be exceptional because it involved a region of dynamically eg vinyls, kerosine derivatives, is found to offer the best alternative unstable shear in the middle troposphere The classical mechanism of for causeway construction and repair, especially because it resists shearing instability in the presence of stable thermal stratification is fissunng Two such combination materials are discussed in detail, responsible for the generation of turbulence The observed large Compo 1005 and Compof lex DMW vertical motions and severe turbulence are demonstrated to be hazardous to aircraft, especially when unaware of the location of the A78-24402 ff Future development of commercial aircraft principal wave and turbulence regions S D Technological challenge - Economic constraints (Kunftige Verkehrs- flugzeugentwicklungen Technologische Herausforderung - Wirt- A78-24364 i< Turbulent airfoils for general aviation R schaftliche Zwange) H Hoppner (Veremigte Flugtechmsche Werke- Eppler (Stuttgart, Universitat, Stuttgart, West Germany) Journal of Fokker GmbH, Bremen, West Germany) Deutsche Gesellschaft fur Aircraft, vol 15, Feb 1978, p 93-99 21 refs Luft- und Raumfahrt, Jahrestagung, 10th, Berlin, West Germany, Several new airfoils are presented which have short pieces of Sept 13-15, 1977, Paper 77-005 33 p In German steep favorable pressure gradient followed by an early pressure The future development of commercial aircraft for European recovery which is a compromise between the Stratford distribution use is discussed with attention to technical and market factors It is and soft stall The drag polars are computed by a mathematical thought likely that the maximum need for 120-160 passenger aircraft model, which is briefly described For comparison, NACA 65(2) - will occur before 1986, while the maximum need for wide-body 415 and NASA GA(W)-1 airfoils are evaluated using the same model, aircraft (210 to 270 or more passengers) will occur in the 1983-1990 in this case the results are also compared with experimental drag period Problems associated with the transition to wide-body aircraft polars (Author) are considered The annual growth of air traffic for the next ten years is estimated with attention to the mix of aircraft types that will A78-24365 # Deployment forces in towing systems Y be required Savings derived from technological advances and Narkis (Techmon - Israel Institute of Technology, Haifa, Israel) expenses associated with interest rates are estimated M L Journal of Aircraft, vol 15, Feb 1978, p 123,124 5 refs A towing airplane usually climbs with a towed vehicle unde- A78-24404 ~ Problems of supersonic transport (Probleme ployed to a certain prescribed altitude where deployment takes des Uberschallverkehrs) U Ganzer (Berlin, Techmsche Universitat, place When the cable is fully extended, it experiences a sudden Berlin, West Germany) Deutsche Gesellschaft fur Luft- und Raum- stretch due to the velocity difference between the airplane and the fahrt, Jahrestagung, 10th, Berlin, West Germany, Sept 13-15, 1977, towed vehicle This stretch generates tension forces in the attach- Paper 77-007 19 p 30 refs In German ment point to the airplane that are much higher than in equilibrium Some of the main engineering problems encountered in the flight In this note, an approximate solution is presented to the design of supersonic civil transport aircraft are mentioned, and their deployment forces in towing systems It is assumed that the entire treatment in the design of the Concorde is briefly described The deployment process occurs in a horizontal plane and that the cable is mam part of the paper is then devoted to developing methods of uniform, with linear elasticity and negligible tangential drag forces characterizing the performance of the Concorde and the cost of its The peak stress in the cable during deployment is given by an operations (Author)

188 A78-24421

A78-24410 Wing with fork tips as means of increasing cost considerations in the realization of a thick wing profile are discussed effectiveness of transport aircraft (Der Flugel mit Gabelspitzen als along with aerodynamic profile-loading considerations and design Mittel zur Erhohung der Wirtschaftlichkeit von Transport- stage monitoring of wing loading An isobaric concept of wing design flugzeugen) G Lobert (Messerschmitt-Bolkow-Blohm GmbH, Otto- is outlined followed by a description of aerodynamic design As an brunn, West Germany) Deutsche Gesellschaft fur Luft- und Raum- example, wing designs for the B10 and A300B airbuses are fahrt, Jahrestagung. 10th, Berlin, West Germany, Sept 13-15, 1977, compared B J Paper 77-017 47 p 7 refs In German (MBB-UFE-1344) A method is described for discretizing the circulation distribu- A78-24418 H Profile design for an advanced-technology air- tion for planar and nonplanar lifting surfaces, and it is applied to a foil for general aviation aircraft (Profilentwurf fur emen Tragflugel wing with fork tips This enables the induced drag for such a wing to neuer Technologic fur Flugzeuge der allgememen Luftfahrt) D be compared with that of a flat wing of equal washed surface and Welte (Dormer GmbH, Friednchshafen, West Germany) Deutsche equal weight With a carefully designed fork tip, an 8% reduction in Gesellschaft fur Luft- und Raumfahrt, Jahrestagung, 10th, Berlin, induced resistance can be obtained over the reference planar wing West Germany, Sept 13-15, 1977, Paper 77-027 25 p 5 refs In The savings in fuel weight and engine weight can amount to up to 7% German Research supported by the Bundesministerium fur For- of the useful load P T H schung und Technologic NACA profiles and a profile from the NASA General Aviation- A78-24411 ii Navigation procedure - Present systems and Whitcomb series are used as a starting point in designing an advanced development trends (Navigationsverfahren - Gegenwartige Systeme airfoil for general aviation aircraft Potential theory pressure distribu- und Entwicklungstrends) H Winter (Deutsche Forschungs- und tion calculations, together with boundary layer calculations, permit a Versuchsanstalt fur Luft- und Raumfahrt, Institut fur Flugfuhrung, decrease in the null moment and an optimization of the lift Braunschweig, West Germany) Deutsche Gesellschaft fur Luft- und characteristics of the wing Trailing edge flap design is also improved Raumfahrt, Jahrestagung, 10th, Berlin, West Germany, Sept 13-15, Wind tunnel tests are used to compare the conventional profiles, the 1977, Paper 77-018 21 p 5 refs In German NASA profile and the improved design J M B At present, aircraft navigation and tracking is carried out by separate systems (VOR, DME, INS, Doppler Systems) Proposals for A78-24419 Wings with controlled separation (Flugel mit integrating these systems are discussed, together with a description of kontrollierter Ablosung) W Staudacher (Messerschmitt- their shortcomings when used individually Attention is given to Bolkow-Blohm GmbH, Munich, West Germany) Deutsche Gesell- improvements in accuracy (using a Kalman filter), and better schaft fur Luft- und Raumfahrt, Jahrestagung, 10th, Berlin, West data links between ground stations and aircraft, eg DABS Micro- Germany, Sept 13-15, 1977, Paper 77-028 28 p 22 refs In wave landing systems (MLS) and micro-electronics, which permit German (MBB-UFE-1343) greater use of on-board systems, are also seen as improving navigation A description is presented of selected results obtained by a accuracy D M W German study group concerned with investigations of wings with controlled separation The objectives of the investigation are related A78-24412 ff The technical potential of instrument landing to an improvement of flight characteristics and flight performance systems in the present and in the future (Das techmsche Potential des limits in the region of large angles of attack by various techniques Instrumenten-Landesystems in Gegenwart und Zukunft) G Hofgen These techniques involve partly a generation of concentrated stable (Standard Elektrik Lorentz AG, Stuttgart, West Germany) Deutsche vortex systems which produce positive interference effects in relation Gesellschaft fur Luft- und Raumfahrt, Jahrestagung, 10th, Berlin, to the wings The stabilization and the control of the separated West Germany, Sept 13-15, 1977, Paper 77-019 19 p In German vortex layers is also considered The studies conducted are concerned The basic principles of instrument landing systems (ILS) are with the development of hybrid wings and the optimization of described with reference to the usual frequencies of the ground based concentrated spanwise blowing Basic experimental data were ob- guiding transmitter, and the angle of approach around the mid-line of tained in wind tunnel tests. The effectiveness of strakes, flap systems, the runway The accuracy and dependability of ILS is discussed in and spanwise blowing are compared G R terms of the stability and consistancy of both on-board and ground transmitting equipment Attention is given to the present state-of- the-art in ILS, and to suggestions for improvement, eg the use of A78-24420 ft Basic considerations concerning the possibili- two independent frequencies to reduce interference, and DME to ties of wing families in civil aviation (Grundsatzbetrachtungen zur improve distance measurement The use of a micro-wave landing Moghchkeit von Flugelfamihen bei zivilen Verkehrsflugzeugen) H -G system (MLS) is also discussed, but in general, ILS is considered Klug, B Fischer, and J Hempel (Messerschmitt-Bolkow Blohm sufficient for the present and short-term future D M W GmbH, Hamburg, West Germany) Deutsche Gesellschaft fur Luft- und Raumfahrt, Jahrestagung. 10th, Berlin, West Germany, Sept 13-15, 1977, Paper 77-029 27 p In German A78-24414 ff Touch input as alternative to keyboard and Economic considerations make a high degree of commonality rolling ball for the radar controller at the display-screen place of among aircraft parts desirable Even for aircraft of widely differing operation in ground-based flight control (Erne Beruhreingabe als Alternative zu Tastenfeld und Rollkugel des Radarlotsen am Schirm- range, capacity, and body type, common parts can be manufactured, bildarbeitsplatz bei der bodenseitigen Flugfuhrung) K -P Holzhausen although the task is made considerably easier when the aircraft is produced by the same company Tables are presented analyzing the and K P Gartner (Forschungsinstitut fur Anthropotechnik, Mecken- performance parameters of different aircraft when fitted with a heim. West Germany) Deutsche Gesellschaft fur Luft- und Raum- fahrt, Jahrestagung, 10th, Berlin, West Germany, Sept 13-15, 1977, common (rather than an optimized) wing Although performance Paper 77-021 11 p 12 refs In German suffers slightly, this is more than offset by substantial savings in development and maintenance costs. D M W A78-24417 Design of a transomcally profiled wing (Ent- wurf transsomsch profiherter Tragflugel) B Kiekebusch A78-24421 ff The significance of wing end configuration in (Messerschmitt-Bolkow-Blohm GmbH, Hamburg, West Germany) airfoil design for civil aviation aircraft (Die Bedeutung der Flugelend- Deutsche Gesellschaft fur Luft- und Raumfahrt, Jahrestagung, 10th, formen beim Tragflugelentwurf fur Flugzeuge der zivilen Luftfahrt) Berlin. West Germany, Sept 13-15, 1977, Paper 77-026 75 p 45 H Zimmer (Dormer GmbH, Friednchshafen, West Germany) refs In German (MBB-UM-12 77) Deutsche Gesellschaft fur Luft- und Raumfahrt, Jahrestagung, 10th, So-called 'organic' design criteria are combined with the isobar Berlin, West Germany, Sept 13-15, 1977, Paper 77-030 41 p 31 concept of wing design and applied to the optimization of a refs In German Research supported by the Bundesministerium fur transonic wing Consideration is given to pre-optimization of wing Forschung und Technologic aspect ratio and thickness, to design variations in the projection stage Lift dependent induced drag in commercial aviation aircraft is and to optimal structural weight and wing geometry Aerodynamic discussed, with emphasis on the necessary compromises between

189 A78-24422

wing end configuration modifications which better lift performance Efforts concerning the development of more effective mission and the weight gains that accompany such modifications Triangular, management procedures are related to predictions regarding an rectangular and elliptical configurations for wing ends are considered, average yearly growth of the international air traffic of 7 9% A attention is also given to airfoil designs incorporating wmglets Water primary objective in this connection is the design of a digital tunnel tests of several configurations are reported In addition, integrated flight control system The automation of control processes applications of wing end modifications to advanced technology within the terminal maneuvering area (TMA) for the approach phase commercial aviation aircraft and to the Airbus A-300 are mentioned is discussed together with the development of cost-effective flight JMB procedures in the TMA Data for the fuel consumption as a function of the flight path angle are considered The optimal path angle found A78-24422 ff Aircraft performance improvement through is 2 8 deg A description is presented of two different approach retrofitting of wmglets (Em Beitrag zur Leistungsverbesserung von procedures, called TMA1 and TMA2 TheTMA! procedure provides Flugzeugen durch Nachrusten von Wmglets) B Ewald (Veremigte an optimum approach with respect to fuel consumption The TMA2 Flugtechmsche Werke-Fokker GmbH, Bremen, West Germany) program makes a four-dimensional navigation possible The described Deutsche Gesellschaft fur Luft- und Raumfahrt, Jahrestagung, 10th, flight procedures were verified with the aid of a computer program Berlin, West Germany, Sept 13-15, 1977, Paper 77-031 41 p 9 refs Attention is given to the hardware configuration and the software of In German the considered flight control system G R Wind tunnel tests are employed to study the lift performance improvements provided by the addition of wmglets or additional A78-24433 ff Advanced quiet propulsion for general aviation span length to the VFW-614 wing profile In general the gain in lift is (Fortschnttliche leise Antnebe fur die Allgememe Luftfahrt) U somewhat greater for the model with lengthened wing span, under Kramer (Veremigte Flugtechmsche Werke-Fokker, Bremen, West conditions of constant lift, the wmglet configuration reduces drag Germany) Deutsche Gesellschaft fur Luft- und Raumfahrt, Jahres- more effectively than the lengthened span model For typical landing tagung, 10th, Berlin, West Germany, Sept 13-15, 1977, Paper and takeoff conditions, the lift gams provided by the two types of 77-044 51 p 11 refs In German wing modification are approximately equivalent The effect of The problem of noise regulation applies to propeller craft as well wmglets of lateral maneuvering is also discussed JMB as jets Demonstration flights with K- and E-class aircraft using motors generating up to 200 hp yielded noise reductions of 10 dB A A78-24425 tt Integrated flight control system for future reduction in the propeller's basic rate of rotation was also noted with transport aircraft (Integnertes Flugfuhrungssystem fur zukunftige the quieter engine, but an application of proven aviation-engineering Transportflugzeuge) H Bohret (Bodenseewerk Geratetechnik principles should prove adequate to correct the problem Tables are GmbH, Uberlmgen, West Germany) Deutsche Gesellschaft fur Luft- presented outlining operating parameters of both present propeller und Raumfahrt, Jahrestagung, 10th, Berlin, West Germany, Sept systems and those still under development D M W 13-15, 1977, Paper 77-035 18 p 7 refs In German The paper discusses the increased requirements placed on the A78-24434 ff The integrated shielded propeller as a drive flight control and guidance systems of future transport aircraft, and system for general aviation aircraft (Die integrierte Mantelschraube describes the architecture of an integrated flight control system All als Antnebssystem fur Flugzeuge der allgememen Luftfahrt) H functions will be distributed between two computers, the flight Fischer (Rhem-Flugzeugbau GmbH, Monchengladbach, West control computer and the flight management computer Sensor data Germany) Deutsche Gesellschaft fur Luft- und Raumfahrt, Jahres- are prepared in the sensor data management unit The reduced tagung, 10th, Berlin, West Germany, Sept 13-15, 1977, Paper number of computer units in conjunction with a digital bus system 77-045 27 p In German will result in considerable savings in hardware costs An experimental The advantages of an integrated shielded propeller design are system has been developed, which performs, besides the usual discussed In a comparison of shielded and free propellers it is shown functions, such functions as TMA navigation, 4D navigation, and that the cross section of the air stream behind the shielded propeller minimum noise approach A special pilot control unit designed as an is not constricted An integrated shielded propeller was developed intelligent terminal and having its own data processor and serial and used in power gliders, whose characteristics are reported, and in interface for exchange of data with controller is described P T H the design of a general aviation aircraft, which is described Advantages resulting from the use of the integrated shielded A78-24426 From analog to digital control systems - propeller include extension of the speed range, a reduction in noise Improved performance by means of advanced technology (Von level, and more comfortable cabin design M L analogen zu digitalen Flugfuhrungssystemen-Leistungssteigerung durch erne fortschnttliche Technologic) H Anders and K Weise A78-24435 ff Special problems in the development of the (Messerschmitt Bolkow-Blohm GmbH, Hamburg, West Germany) propulsion system for an over-1he-wing engine configuration (Spezi- Deutsche Gesellschaft fur Luft- und Raumfahrt, Jahrestagung, 10th, elle Probleme bei der Entwicklung der Antnebsanlage fur erne Berlin, West Germany, Sept 13-15, 1977, Paper 77-036 38 p 8 refs Tnebwerksanordnung uber dem Flugel) R Smyth (Veremigte In German (MBB-UH-09-77) Flugtechmsche Werke-Fokker GmbH, Bremen, West Germany) Limitations of present-day analog flight control systems are Deutsche Gesellschaft fur Luft- und Raumfahrt, Jahrestagung, 10th, characterized, and the potential for utilizing digital flight control Berlin, West Germany, Sept 13-15, 1977, Paper 77-046 42 p In systems for improved performance is discussed Prospective advan- German tages of the digital system are thought to include cheaper electronic Problems related to over-the-wmg engine design are discussed, components, the processing of a larger number of computation steps, with special reference to the development of the VFW-Fokker 614, a an increased accuracy, better error detection, fewer line replaceable 40-passenger aircraft with a cruise speed of Mach 0 65 at an altitude limits, lower weight, and increased reliability Cost and the mean of 25,000 ft Engine cycle selection, engine nacelle design, flow time between failures for analog and digital systems are compared nozzle type and pylon configuration are considered Design of the M L intake profile is also considered Digital processing has been applied to the study of the engine performance in nonstationary flow with A78-24427 ff Mission management in the airnort vicinity lateral wind components. JMB (Missionsmanagement im Flughafennahbereich) A Modlmger (Veremigte Flugtechmsche Werke-Fokker GmbH, Bremen, West A78-24436 # Reducing aircraft noise through retrofitting Germany) Deutsche Gesellschaft fur Luft- und Raumfahrt, Jahres- (Senkung des Fluglarms durch Umrustung von Flugzeugen) U tagung, 10th, Berlin, West Germany, Sept 13-15, 1977, Paper Michel, D Bechert, and E Pfizenmaier (Deutsche Forschungs- und 77-037 27 P In German Research supported by the Bundes- Versuchsanstalt fur Luft- und Raumfahrt, Institut fur Turbulenzfor- mimsterium fur Forschung und Technologic schung, Berlin, West Germany) Deutsche Gesellschaft fur Luft- und

190 A78 24460

Raumfahrt, Jahrestagung, 10th, Berlin, West Germany, Sept 13-15, Berlin, West Germany, Sept 13-15, 1977, Paper 77-052 14 p 16 1977, Paper 77-047 16 p 21 refs In German refs In German Retrofitting to reduce aircraft noise in aircraft such as the B727, Consideration is given to different mechanisms of airframe noise 8737, DC-9, and BAC-111 is discussed Data on the effects of aerodynamic noise produced by turbulent flow past aircraft retrofitting on noise emissions and performance are reported, Airframe noise data are analyzed for eight different aircraft (HP 115, re-engming, an option which will not be available for several years, is HS 125, BAC 1-11, VC 10, Libelle, Jet Star, Convair 990 and B-747) also mentioned Since noise reduction may be an expensive proposi- Optimal formulations of semiempirical equations were obtained for a tion, differential landing fees based on aircraft noise emission levels, model accounting for pure boundary layer noise and pure trailing as well as night-time restrictions on noisy aircraft, are suggested The edge noise Normalization of data showed the standard deviation for example of Berlin is cited in urging a role for government m the boundary layer noise model to be negligible Using this model, a retrofitting J M B simple approximation formula was obtained for airframe noise The formula agreed well with experimental data on noise generated on A78-24437 # Recent advances concerning an understanding the F-106B aircraft delta wing and on the Comet magnetic levitation of sound transmission through engine nozzles and jets (Neuere vehicle B J Erkenntmsse zum Schalldurchgang durch Triebwerksdusen und- Strahlen) D Bechert, U Michel, and E Pfizenmaier (Deutsche A78-24443 ff Use of the finite element method in fracture Forschungs und Versuchanstalt fur Luft- und Raumfahrt, Institut fur mechanics (Uber die Anwendung der Finite-Element Methode in der Turbulenzforschung, Berlin, West Germanyl Deutsche Gesellschaft Bruchmechanik) L Schwarmann and J Bauer (Veremigte Flug- fur Luft- und Raumfahrt. Jahrestagung, 10th, Berlin, West Germany, techmsche Werke-Fokker GmbH, Bremen, West Germany) Deutsche Sept 13-15. 1977, Paper 77-048 21 p 12 refs In German Gesellschaft fur Luft- und Raumfahrt, Jahrestagung, 10th, Berlin, Experiments on the interaction between a turbulent jet and pure West Germany, Sept 13-15, 1977, Paper 77-055 26 p 17 refs In tone sound coming from inside the jet nozzle are reported This is a German model representing the sound transmission from sound sources in jet The use of the finite element method for calculating fracture engines through the nozzle and the jet flow into the far field It is mechanics parameters of a planar stringer- or rib-reinforced acircraft shown that pure tone sound at low frequencies is considerably- shell is described Example calculations which take into account the attenuated by the jet flow, whereas it is conserved at higher influence of the reinforcements and of the biaxial and variable frequencies On the other hand, broadband jet noise can be amplified stress-strain state are presented, and the theoretical basis of the considerably by a pure tone excitation Both effects seem not to be method is considered The finite element method is recommended interdependent Knowledge on how they are created and on relevant for complicated structures, when a structure is too complex for parameter dependences allow new considerations for the develop- direct analysis an approximation method, such as the finite element ment of sound attenuators (Author) method, can be used M L

A78-24438 ff Localization and shielding of noise sources A78-24448 ff The endangerment of flight safety due to wind generated by the interaction of free jets with flat surfaces (Lokalisier- shear (Die Gefahrdung der Flugsicherheit durch Scherwind) P ung und Abschirmung der Schallquellen von Freistrahlen, die mit Krauspe (Braunschweig, Technische Universitat, Braunschweig, West Germany) Deutsche Gesellschaft fur Luft- und Raumfahrt, Jahresta- ebenen Flatten mterferieren) E Evertz (Rheimsch-Westfalische Technische Hochschule, Aachen, West Germany) Deutsche Gesell- gung, 10th, Berlin, West Germany, Sept 13-15, 1977, Paper 77-062 23 p 14 refs In German schaft fur Luft- und Raumfahrt, Jahrestagung, 10th, Berlin, West Germany, Sept 13-15, 1977, Paper 77-049 20 p In German Aircraft accidents due to wind shear at Boston (1973), New Interaction of jet flows with the trailing edge flaps of advanced York (1975), and Denver (1975) are cited in discussing possible corrective measures The typical wind shear phenomena registered at STOL aircraft is studied, with emphasis on reduction of the noise generated by the interaction Internal noise (due to fan, compressor, airports is studied, and the dynamic response of aircraft structures to combustion chamber and turbine components), deflector noise, wind shear during the takeoff and landing phases is considered scrubbing noise, noise produced in the turbulent mixing layer, and Adequate characterization of micrometeorological effects along the trailing edge noise are identified A system employing a hot wire airport runways, and the effective use of aircraft trailing edge flaps, probe and a microphone provides data on noise levels as a function spoilers, and direct lift control may provide greater safety during of the length and orientation of the trailing edge element, frequency wind shear conditions JMB analysis of the jet noise is also reported J M B A78-24451 # Flowfield and pressure field of a model propeller (Stromungs- und Druckfeld ernes Modellpropellers) R A78-24439 New methods for flight vibration studies Neubauer and K P Anders (Deutsche Forschungs- und Versuchsan- (Neuere Methoden des Flugschwmgungsversuchs) G Haidl and M stalt fur Luft und Raumfahrt, Abteilung Technische Akustik, Stemmger (Messerschmitt-Bolkow-Blohm GmbH, Ottobrunn, West Braunschweig, West Germany) Deutsche Gesellschaft fur Luft- und Germany) Deutsche Gesellschaft fur Luft- und Raumfahrt, Jahresta- Raumfahrt, Jahrestagung, 10th, Berlin, West Germany, Sept 13-15, gung, 10th, Berlin, West Germany, Sept 13-15, 1977, Paper 77-050 1977, Paper 10 p 10 refs In German 24 p 21 refs In German (MBB-UFE-1350) A schlieren technique is described for visualization of pressure In order to safeguard against flutter the flight vibration gradients and flows in the near field of a reduced-scale propeller characteristics of aircraft should be determined, and a discussion of model Conventional and high-speed photography are used to record procedures for testing and evaluating flight vibration is presented the schlieren images Schlieren films of the model propeller show Measurement and vibration-inducing devices, designed for attach- that the two tip vortices of a two-blade propeller can move along ment to aircraft, are described Analytical methods for processing paths of different radii, and also exhibit temporal fluctuations Such flight vibration data are reported with attention to calculation of behavior in real propellers was verified P T H power spectra and frequency responses, probability of error in fast Fourier transforms, frequency and damping analysis from the A78-24460 ff Six degrees of freedom system for store impulse function, modal analysis, 'Randomdec signature' method, separation studies in ONERA wind-tunnels J Coste (ONERA, and window functions Test results are presented M L Chatillon-sous Bagneux, Hauts-de-Seme. France) (Joint Technical Coordinating Group, Aircraft Stores Compatibility Symposium, 4th, A78-24441 # Airframe noise, the lower noise limit for Eg/in AFB, Fla. Oct 12-14, 1977) ONERA. TP no 1977100, aircraft (Umstromungslarm, die untere Larmgrenze fur Flugzeuge) 1977 13p W F King (Deutsche Forschungs- und Versuchsanstalt fur Luft und The study of airborne store separation can be performed in a Raumfahrt, Institut fur Turbulenzforschung, Berlin, West Germany) wind tunnel by different methods In particular the 'grid' method, Deutsche Gesellschaft fur Luft- und Raumfahrt, Jahrestagung, 10th, where aerodynamic loads are measured on the store placed suc-

191 A78-24461

cessively at discrete locations - grid nodes • in the aircraft A78-24475 # Aircraft electrical equipment (Elektro- aerodynamic field, the trajectory being then calculated by flight oborudovame samoletov) D N Sapiro Moscow, Izdatel'stvo Mashi- mechanics formulas, give fairly good results That kind of testing is nostroenie, 1977 304 p 20 refs In Russian currently carried out in Modane wind-tunnels for any military store Aircraft (including helicopter) electrical equipment is described Until now a sting support system with only one remotely controlled with attention to the general characteristics required in equipment degree of freedom, i e , translation, was used But several manual designed for use in aircraft Attention is directed to automatic operations were needed to modify the other, unmotonzed, pa- control, electrical drive, illumination equipment, and heating equip- rameters of location and attitude Presently a device with six ment Other topics include power, switching, and electromagnetic motorized, remotely controlled, degrees of freedom has been built, devices, primary and secondary electrical sources, and circuit design resulting in a significant time saving for such testing Associated with M L a computer controlled servo system, this device can be used not only with the grid method, but also with the captive trajectory method A78-24548 * Service experience of composite parts on the The mechanical features of the device and the bases for the servo L-1011 and C-130 R H Stone (Lockheed Aircraft Corp , Burbank, control program are described, along with the first calibration results Calif) and W E Harvill (Lockheed-Georgia Co, General Structures in the Modane 6 ft transonic tunnel (Author) Dw , Manetta, Ga ) SAMPE Quarterly, vol 9, Jan 1978, p 34-40 9 refs NASA sponsored research A78-24461 # The ONER A position on the use of feed-back Composite flight service programs are in progress on two control against flutter due to external wing-mounted stores R Dat, aircraft, the L-1011 and C-130 A set of Kevlar-49/epoxy fairings is R Destuynder, and J-J Angelmi (ONERA, Chatillon-sous-Bagneux, being flight tested on three L-1011's and have had no major service Hauts-de-Seme, France) (Joint Technical Coordinating Group, Air- problems after 10,000 hours of service The center wing box craft Stores Compatibility Symposium, 4th, Eg/in AFB, Fla, Oct aluminum skins and hat stiffeners were reinforced with precured 12-14, 1977) ONERA, TP no 1977-101, 1977 21 p 7 refs bonded boron/epoxy strips on three C-130's After almost three Consideration is given to flutter control applicable to wing- years and over 4000 flight hours, these components are continuing to mounted stores, noting that military aircraft carry a high number of perform satisfactorily in service Another flight service component store combinations Equations are derived for determining a flutter on the L-1011 is a graphite/epoxy floor post, which is free of service control law, including those describing the response of a wing in a problems or defects after 10,000 flight hours These components flow to harmonic excitation The selective control of the flutter provide significant verification of the serviceability of all three major mode is discussed with reference to a control law modifying the composite reinforcement types (Author) damping of the unstable mode Nissim's method (1971) is reviewed in terms of providing a control dissipative matrix, and the dissipativ- A78-24585 ;/' Organization of a programmed matrix- ity condition preventing the control matrix from providing active operation system in an airborne digital computer (Orgamzatsna power is found Experiments in damping-out store-induced flutter on programmnoi sistemy matnchnykh operatsii na bortovykh TsVM) wind tunnel models are reviewed SCS V K Tomshm and V M Kharchenko Upravliaiushchie Sistemy i Mashmy, Sept -Oct 1977, p 70 74 In Russian A78-24463 ft A new airfoil family for rotor blades J -J Fixed point procedures for the organization of programmed Thibert (ONERA, Chatillon sous-Bagneux, Hauls de-Seine, France) matrix operation in airborne computers are discussed Scaling and J Gallot (Societe Nationale Industnelle Aerospatiale, Division difficulties are eliminated by the introduction of normalized matrices Helicopteres, Mangnane, Bouches-du-Rh&ne, France) (European and scaling factor for matrices The matrix operation system has the Rotorcraft and Powered Lift Aircraft Forum, 3rd, Aix-en-Provence, following advantages (1) users are completely freed from the need France. Sept 7-9. 1977) ONERA, TP no 1977-113, 1977 22 p 24 to scale matrix operations, (2) the system is of high accuracy and refs enables organization of a flexible computational process, and (3) the The development and characteristics of the new OA 209 programming of matrix operations is performed at the autocode helicopter blade airfoil are described The airfoil, according to level B J steady-flow wind-tunnel experiments and flight tests, has, in comparison with a conventional profile, an increased hft-to-drag ratio in hover, an increase in the flight envelope, a reduced level of vibration, and reduced pitch link loads Airfoil performance in steady airflow was predicted by computer progrdms for viscous transonic airflow Design objects, performance, and anticipated improvements are discussed M L

A78-24468 ,*' Study of a supercritical profile with oscillating control surface in sub- and transonic flows (Etude d'un profit supercntique avec gouverne oscillante en ecoulement subsonique et transsomque) R Grenon and J Thers (ONERA, Chatillon-sous- Bagneux, Hauts-de-Seme, France) (NATO, AGARD, Symposium on Unsteady Aerodynamics, Ottawa, Canada, Sept 26-28, 1977) ONERA, TP no 1977-136,1977 11 p 6 refs In French The paper presents results of unsteady pressure measurements performed on a supercritical profile equipped with a 25 percent- chord trailing edge control surface in harmonic motion, in two- dimensional sub- and transonic flows Important differences appeared between the subcritical regime without shock, and the supercritical regime with shock In both cases, we studied the influence of the 'unsteady' parameters, such as oscillation frequency and amplitude, and that of 'steady' ones, such as mean flap setting and wing angle of attack This study brought to light the importance of viscous and shock-related phenomena, and the necessity to develop calculation methods taking these phenomena into account (Author)

192 N78-15999

of alternative schedules The Logistics Composite Model (LCOM) appeared to have the potential to perform the evaluation, through simulation The authors investigated LCOMs capability to accurately predict the sortie effectiveness of F-15 monthly flying schedules by simulating six actual F-15 monthly flying and maintenance schedules Analysis of the results indicated that LCOM could not effectively evaluate alternative F-15 monthly flying schedules Author (GRA)

N78-15995 Colorado Univ Boulder NUMERICAL SOLUTION FOR SOME PROBLEMS CON- STAR ENTRIES CERNING UNSTEADY MOTION OF AIRFOILS Ph D Thesis Yeou-Kuang Shung 1977 71 p Avail Univ Microfilms Order No 77-24290 N78-15991# Air Force Inst of Tech Wright-Patterson AFB The unsteady behavior of a wing of infinite span moving Ohio School of Systems and Logistics through an inviscid and incompressible fluid is studied by using AN INVESTIGATION INTO THE NATURE OF AIRCRAFT the method of conformal mapping in combination with a numerical SUPPORTABILITY IN THE C1LC ENVIRONMENT MS technique When a small airplane is flying toward a line vortex Thesis left behind by a large aircraft, the lift and moment on the small Gordon S Luna and Robert A Stier Sep 1977 128 p refs airplane caused by the line vortex alone is computed Numencal (AD-A047226 AFIT-LSSR-13-77B) Avail NTIS results have been obtained for various combinations of the speed HC A07/MF A01 CSCL 01/5 and the position of the small airplane relative to the center of This paper deals with the initial development of a generalized the line vortex It is found that the small airplane may experience model representing the Centralized Intermediate Logistics Concept large fluctuations in both lift and moment when traversing through (CILC) The model can handle from 1 to 10 operating locations a strong line vortex Dissert Abstr and many of the logistical variables including demand rates, repair cycle times travel times and base repair rates The N78-15996 Illinois Univ Urbana-Champaign analysis includes a comparison of the traditional maintenance ON SOME STRUCTURE-TURBULENCE INTERACTION system to CILC and a trend analysis of the effects of demand PROBLEMS Ph D Thesis rates base repair rates shipping times repair times and location Shoji Maekawa 1977 117 p strategy on supportabihty Author (GRA) Avail Univ Microfilms Order No 77-26709 The interaction between a turbulent flow and certain types N78-15992# Air Force Inst of Tech Wright-Patterson AFB of structures responding to its excitation was studied The Ohio School of Systems and Logistics turbulence was typical of those associated with a boundary layer AN ANALYSIS OF USER ACCEPTANCE AND PERCEIVED having a cross spectral density indicative of convection and USABILITY OF C-141A JOB GUIDES M S Thesis statistical decay A number of structural models were considered S A Richardson and Thomas E Syster Sep 1977 271 p in the investigation including an unsupported infinite beam and refs a periodically supported infinite beam The results are presented IAD-A047141 AFIT-LSSR-36-77B) Avail NTIS in terms of the spectral densities of the structural response and HC A12/MF A01 CSCL 05/9 the perturbation Reynolds stress in the fluid at the vicinity of The C-141A was the first aircraft to use job guides In the interface It is found that important spectral peaks of the 1976 AFHRL conducted a survey at the two bases which structural response will not appear if decays in the turbulence participated in the development of these |0b guides to determine are neglected in the analysis Dissert Abstr their usability and degree of user acceptance This thesis conducted a similar survey at two ba_ses which did not participate in the N78-15997 Georgia Inst of Tech Atlanta development of the C-141H Job Guide to determine if user AN IMPROVED METHOD OF CALCULATING THE TIP attitudes about job guides was as favorable as found by AFHRL VORTEX GEOMETRY FOR HOVERING ROTORS Also tests were made to determine if there was any difference Ph D Thesis in attitudes between pay grades Behavioral theory suggests that Satish S Samant 1976 73 p workers who participate in planning a change will have less Avail Univ Microfilms Order No 77-25615 resistance to that change and that younger workers resist change Efforts were made to locate the cause of discrepancies in less than older workers It was concluded that technicians at the performance analysis of hovering rotors Accurate specification bases which did not participate in the development of the C-141A of the geometry of the vortex wake particularly in the near Job Guides had a lower acceptance of them, but there was no wake was of primary concern The consistency requirement that difference in perceived usability No significant difference was the velocity in the blades fixed reference system at a point on found between grades for either user acceptance or perceived the a vortex filament must be tangential to the vortex filament usability Although acceptance of the C-141 A Job Guides was referred to the same system was developed in terms of the high actual on-the-job use of them appeared to be quite low apparent velocity components It was shown that the apparent and could eliminate anticipated cost savings as suggested by velocity components calculated from a given vortex system using previous experiments with job guides Author (GRA) the Biot-Savart law do not satisfy these consistency requirements but can be used to calculate the effect of the same vortex system at the blade very accurately The discrepanices in the N78-15993# Air Force Inst of Tech Wright-Patterson AFB induced velocity are therefore thought to be the local effects of Ohio School of Systems and Logistics this small region and are then called the core effect AN EVALUATION OF THE CAPABILITY OF THE LOGISTICS Dissert Abstr COMPOSITE MODEL TO PROJECT THE MONTHLY AIRCRAFT SORTIE EFFECTIVENESS OF AN F-1S WING M S Thesis Charles G Davis and Clifford T Smith Sep 1977 103 p N78-15999'# National Aeronautics and Space Administration refs Lang]ev Research Center Langley Station Va (AD-A047227 AFIT-LSSR-2-77B) Avail NTIS WIND-TUNNEL INVESTIGATION OF AERODYNAMIC PER- HC A06/MF A01 CSCL 01/5 FORMANCE. STEADY AND VIBRATORY LOADS. SURFACE There has been considerable research on computerized TEMPERATURES. AND ACOUSTIC CHARACTER- generation of alternative flying and maintenance schedules in Nov 1976 153 p refs an effort to improve utilization of Air Force resources However (NASA-TN-D-8235 L-10753) Avail NTIS HC A08/MF A01 no technique exists to evaluate the potential sortie effectiveness CSCL 01A

193 N78-16000

Static and wind-on tests were conducted to determine the are represented by a vortex grid arranged on a series of aerodynamic characteristics of and the effects of jet impingement concentrical cylindrical surfaces The analysis of sideslip effects on the wing of a large scale upper surface blown configuration by the subject method is described Numerical considerations powered with an actual turbine engine The wing and flaps were peculiar to the application of these techniques are also discussed instrumented with experimental dual-sensing transducer units The method has been implemented in a digital computer code consisting of a fluctuating pressure gage a vibratory accelerometer A users manual is included along with a complete FORTRAN and a surface mounted alumel thermocouple Noise directivity compilation an executed case and conversion programs for and spectral content measurements were obtained for various transforming input for the NASA wave drag program Author flap configurations and various engine thrust settings to provide baseline noise data for other upper surface blown configura- N78 16003*# Boeing Vertol Co. Philadelphia. Pa tions ARM TWO-DIMENSIONAL WIND TUNNEL TEST OF AN OSCIL- LATING ROTOR AIRFOIL. VOLUME 1 Final Report L U Dadone Dec 1977 163 p refs N78-1600O*# National Aeronautics and Space Administration (Contract NAS1-13795) Langley Research Center Langley Station Va (NASA-CR-2914 D210-11188-1-Vol-1) Avail NTIS LONGITUDINAL AERODYNAMIC CHARACTERISTICS AT HC A08/MF A01 CSCL 01A MACH 0 60TO 2 86 OF A FIGHTER CONFIGURATION WITH A two dimensional wind tunnel test was conducted to obtain STRUT BRACED WING the quasisteady and unsteady characteristics of an advanced airfoil Samuel M Dollyhrgh William J Monta and Giuliana Sangiorgio designed for helicopter rotor applications Differential pressures Dec 1977 149 p refs were measured at 17 locations along the chord of the airfoil (NASA-TP-1102 L-11801) Avail NTIS HC A07/MF A01 model The airfoil motions were sinusoidal forced-pitch oscillations CSCL 01A about the quarter chord at amplitudes varying from 2 5 to 100 An investigation was made to determine the effects on degrees and at frequencies from 23 Hz to 90 Hz The quasisteady longitudinal aerodynamic characteristics of utilizing struts to brace tests were conducted at Mach numbers from 02 to 09 and the wing to allow the wing thickness reduction on the LFAX-8 the oscillatory tests between M = 0 2 and M = 0 7 At quasisteady fighter configuration Structural and load analysis indicated that conditions a limited number of drag measurements were made the maximum airfoil thickness could be reduced from 45 to with a wake-traversing probe Author 3 1 percent with the strut brace concept Wave drag theory indicated that reducing the wing maximum thickness from 4 5 percent to 3 1 percent would yield a significant reduction in N78-16015*# Boeing Commercial Airplane Co Seattle Wash zero-lift wave drag of about 28 percent at the design Mach FEASIBILITY STUDY OF AN INTEGRATED PROGRAM FOR number of 1 60 Strut arrangements designed and tested included AEROSPACE VEHICLE DESIGN (IPAD) VOLUME 5 a single straight strut a single swept strut, and a set of tandem CATALOG OF IPAD TECHNICAL PROGRAM ELEMENTS straight struts In addition a wire of approximately the same Final Report cross sectional area replaced the single straight strut on one W B Gillette ed and J W Southall ed 21 Sep 1973 series of runs The original LFAX-8 with the 4 5-percent-thick 364 p refs wing was retested to serve as a base line for this investigation (Contract NAS1-11441) Author (NASA-CR-132395 D6-60181-5) Avail NTIS HC A16/MF A01 CSCL 01C The catalog is presented of technical program elements which N78-16001*# National Aeronautics and Space Administration are required to support the design activities for a subsonic and Lewis Research Center, Cleveland Ohio supersonic commercial transport Information for each element COLD-AIR PERFORMANCE OF A TIP TURBINE DESIGNED consists of usage and storage information ownership status and TO DRIVE A LIFT FAN 3 EFFECT OF SIMULATED FAN an abstract describing the pumose of the element Author LEAKAGE ON TURBINE PERFORMANCE Jeffrey E Haas (Army R and T Labs) Milton G Kofskey Glen M Hotz. and Samuel M Futral Jr Jan 1978 28 p refs N78-16021# Stevens Inst of Tech Hoboken N J (NASA-TP-1109 E-9331) Avail NTIS HC A03/MF A01 CSCL RESEARCH ON THE FLUTTER OF AXIAL TURBOMACHINE 01A B LADING Performance data were obtained experimentally for a 0 4 F Sisto Nov 1977 46 p refs linear scale version of the LF460 lift fan turbine for a range of (Contract N00014-76-C-0540) scroll inlet total to diffuser exit static pressure ratios at design (AD-A047086 ME-RT-77004) Avail NTIS HC A03/MF A01 equivalent speed with simulated fan leakage air Tests were CSCL 01/3 conducted for full and partial admission operation with three The dynamic stall of an airfoil with leading edge bubble separate combinations of rotor inlet and rotor exit leakage air separation Is analyzed The stall flutter of turbomachine blading Data were compared to the results obtained from previous often involves periodic growth and collapse of such a bubble investigations in which no leakage air was present Results are The mathematical model representing the physical problem is presented in terms of mass flow, torque and efficiency Author presented A flat plate undergoing harmonic oscillations with time dependent point of re-attachment is studied for the perturbed aerodynamic reactions and applications to the stall flutter N78-16002*# Lockheed-California Co Burbank problem Author (GRA) A GENERALIZED VORTEX LATTICE METHOD FOR SUB- SONIC AND SUPERSONIC FLOW APPLICATIONS Luis R Miranda Robert D Elliot and William M Baker Dec N78-16023# Naval Ship Research and Development Center 1977 371 p refs Bethesda Md (Contract NAS1-12972) THEORETICAL ASPECTS OF DROMEDARYFOIL Interim (NASA-CR-2865 LR-28112) Avail NTIS HC A16/MF A01 Report. Jan 1976 - Jan 1977 CSCL 01A Tsze C Tai Nov 1977 39 p refs If the discrete vortex lattice is considered as an approximation (RR02302001) to the surface-distributed vorticity then the concept of the (AD-A047150. DTNSRDC-77-0104) Avail NTIS generalized principal part of an integral yields a residual term to HC A03/MF A01 CSCL 20/4 the vorticity-mduced velocity field The proper incorporation of A new airfoil design (called a dromedaryfoil) has been this term to the velocity field generated by the discrete vortex developed using a single hump on a modified supercritical airfoil lines renders the present vortex lattice method valid for supersonic for limiting the center of pressure excursion and maximizing the flow Special techniques for simulating nonzero thickness lifting drag divergence Mach number Derivation of the hump is based surfaces and fusiform bodies with vortex lattice elements are on isentropic compression in the fore part and incipient separation included Thickness effects of wing-like components are simulated in the rear The former leads to a weakened shock wave and by a double (biplanar) vortex lattice layer, and fusiform bodies the latter to high pressure recovery after the shock The shock

194 N78-16030 will theoretically locate at the peak of the hump to form a fixed N78-16027# Federal Aviation Administration Washington D C pressure pattern under different flight speeds The shock foot TERMINAL AREA FORECAST 1978-1988 will be inclined at a deflection angle of the hump measured Jan 1977 355 p from the normal of the fore hump surface at the peak Theoretical (AD-A046543 FAA-AVP-77-17) Avail NTIS results indicate considerably shorter center-of-pressure travel for HC A16/MF A01 CSCL 01/2 a dromedaryfoil than for a supercritical airfoil with equal wave This report contains forecasts for air carrier and air taxi drag However improper humping would be penalized by increased enplanements air carrier and air taxi aircraft operations itinerant wave drag At high supercritical flows the shock strength would total and instrument aircraft operations and instrument approaches be limited by (M sub 1 sin betalmax = 1 483 Experimental at 894 airports throughout the United States The airports in verification of theoretical predictions is planned Author (GRA) this publication include all those with Federal Aviation Administra- tion air traffic control towers and those with air carrier service The report is intended as an aid for anticipating future manpower and equipment needs at terminal areas Author (GRA) N78-16024$ Aircraft Research and Development Unit Laverton V N (Australia) N78-16028# Transportation Systems Center Cambridge Mass EVALUATION OF SLIMPACK STYLE PARACHUTE IN CT4A AIRLINE DELAY TRENDS. 1974-1975 A STUDY OF BLOCK AIRTRAINER AIRCRAFT TIME DELAYS. GROUND AND AIRBORNE. FOR Nov 1976 31 p refs SCHEDULED AIR CARRIERS Annual Report (AD-A047083 TI-556) Avail NTIS HC A03/MF A01 CSCL Helen M Condell Seymour M Horowitz and Alan S Kaprehan 01/3 Mar 1977 218 p The Slimpak style parachute was being evaluated under (AD-A039483. TSC-FAA-77-6 FAA-EM 77-2) Avail NTIS Technical Investigation 517 for use in place of the standard HC A10/MF A01 CSCL 01/2 Flexible Back parachute which had proven unsatisfactory in Estimates of block airborne and ground delays for route helicopter operations when worn by large crew members Some segments flown by United States domestic scheduled airlines instructors and students of No 1 Flying Training School of rather operating out of twenty large airports are presented in this large build were unable to wear the Flexible Back parachute in document The data were determined from the CAB ER-586 the CT4A Airtramer because of restriction to control column Service Segment data base which provides monthly operational deflection Headquarters Support Command considered that the times both ground and airborne for all route segments receiving Slimpak style parachute might be suitable for use in the Airtramer scheduled air earner service The data in this report are limited by the large crew memebers and ARDU was directed to investigate to the three-hundred and thirty route segments connecting the this possibility Ground and flight trials were conducted using a twenty airports included in the study Average monthly estimates wide range of aircrew sizes Dropping trials were carried out of the ground and airborne components of block delays defined under Technical Investigation 517 The Slimpak model parachute as delays encountered from ramp to ramp on a route segment as tested was found to be unacceptable for use in the Airtramer are presented for the two-year period from 1974-1975 Average by aircrew with a buttock to heel length of less than about monthly estimates of delays for the airborne portion of the segment 1 02 m It was also found to have major deficiencies in design wheel off to wheels on are categorized according to 1 Route and operation of the harness and associated buckles that would segment 2 airline 3 aircraft type and 4 local scheduled arrival render it unsuitable in its present form for use by the RAAF in or departure time Average monthly estimates of delays for the any other aircraft Author (GRAI ground portion of the route segments are categorized according to departure and arrival ground times at the twenty airport locations included in the study These estimates of ground delays N78-16025# Transportation Systems Center Cambridge Mass are further categorized into busy time intervals 0700 - 2259 AIRCRAFT WAKE VORTICES A STATE-OF-THE-ART and dull time intervals 2300 - 0659 Author (GRA) REVIEW OF THE UNITED STATES R AND D PROGRAM Final Report, Oct - Dec 1976 N78-16029# National Aviation facilities ExpenmentaF Center J N Haddock ed and W R Eberle ed Feb 1977 349 p Atlantic City N J refs Prepared in cooperation with Lockheed Missiles and Space SIMULATION TESTS OF FLIGHT TECHNICAL ERROR IN Co Huntsville Ala 2D/3D AREA NAVIGATION (RNAV) USING A MULTIPLE (AD-A042442 TSC-FAA-77-4 FAA-RD-77-23) Avail NTIS WAYPOINT RNAV SYSTEM WITH AND WITHOUT A FLIGHT HC A15/MF A01 DIRECTOR SYSTEM Final Report. Nov 1975 - Jan 1977 A summary of the current state of-the-art understanding of Donald Eldredge Warren G Crook and William R Crimbnng the aircraft wake vortex phenomenon is presented and the results Oct 1977 101 p refs of the United States program to minimize the restrictions caused (AD-A047246 FAA-NA-77-10) Avail NTIS by aircraft wake vortices in the terminal environment are included HC A06/MF A01 CSCL 17/7 The vortex phenomenon vortex avoidance systems and vortex Six pilots participated in a series of flight simulation tests alleviation techniques were also discussed Author (GRA) employing solo pilot techniques which were conducted in order to measure total system crosstrack (TSCT) and flight (echnical error using a multiple waypomt storage 2D/3D area navigation N78-16026*|~ Boeing Vertol Co. Philadelphia Pa (RNAV) system The tests were designed to assess pilot RESEARCH REQUIREMENTS TO IMPROVE SAFETY OF performance as a function of the interexpenmental variables (1) CIVIL HELICOPTERS 2D RNAV mode versus 3D RNAV mode (2) flight director versus Kenneth T Waters Nov 1977 77 p refs no flight director (3) insertion of an impromptu waypomt into a (Contract NAS1-13624) previously entered flight plan and (4) different route structures (NASA-CR-145620) Avail NTIS HC A05/MF A01 CSCL Performance was measured on the variables horizontal track- 01C ing, vertical tracking airspeed control and procedural perform- Helicopter and fixed-wing accident data were reviewed and ance Author major accident causal factors were established The impact of accidents on insurance rates was examined and the differences N78-16030# National Aviation Facilities Experimental Center. in fixed-wing and helicopter accident costs discussed The state Atlantic City N J of the art in civil helicopter safety was compared to military INTERMITTENT POSITIVE CONTROL PHASE 1 OPERA- helicopters Goals were established based on incorporation of TIONAL TEST AND EVALUATION Interim Report. Jul - known technology and achievable improvements that require Sep 1976 development as well as administrative-type changes such as John W Goodwin Oct 1977 19 p refs the impact of improved operational planning, training and human (AD-A047249 FAA-NA-77-12) Avail NTIS factors effects Specific R and D recommendations are provided HC A02/MF A01 CSCL 17/7 with an estimation of the payoffs timing and development In testing this interface the IPC algorithm was resident in costs Author the Diqital Simulation Facility which simulated the operation of

195 N78-16031

a discrete address beacon system The test series was operation- of today the all-DABS environment of tomorrow and the ally oriented and did not consider such factors as program size intervening transition period The ground and airborne equipments loading factors or processing time The results of the tests reveal required are add-ons to the ground beacon and the airborne that the IPC controller alerts, consistency of commands readability DABS units A two-way data link separate from, but compatible of displayed information and method of displaying information in format with the DABS data link provides the SS-CAS-Equipped to the controllers were, acceptable The issuance of negative aircraft with important site data A tracker capable of reading commands to aircraft presents a problem to the controllers in reliable tracks through ATCRBS synchronous garble is employed that negative phraseology is not utilized in the air traffic control DABS replies arrive garble-free at the SS-CAS aircraft and are system The alerting methods of IPC and conflict alert are similar simple to track An active mode and multi-site usage capability but because of the critical timing of the IPC alert jt was felt X are available for performance enhancement in identified special that a distinctly different alert for IPC should be utilized Author situations This report fully describes the SS-CAS concept as it \ \ \ functions in the all-ATCRBS. all-DABS and transition environ- N78-16031# Mitre Corp McLean Va ments Author (GRA) INITIAL COLLISION AVOIDANCE ALGORITHMS FOR THE BEACON-BASED COLLISION AVOIDANCE SYSTEM J Clark and A McFarland Apr 1977 96 p refs (Contract DOT-FA69NS-162) N78-16037$ Transportation Systems Center. Cambridge, Mass (AD-A047254 MTR-7532 FAA-RD-77-163) Avail NTIS AIRPORT SURFACE TRAFFIC CONTROL VISUAL GROUND HC A05/MF A01 CSCL 17/7 AIDS ENGINEERING AND DEVELOPMENT PLAN Interim A set of baseline collision avoidance algorithms are described Report. Jun 1975 - Oct 1976 which can be used as a point of departure for the development F D MacKenzie Jan 1977 68 p refs (AD-A038153 TSC-FAA-76-26 FAA-RD-77-161 Avail NTIS of final algorithms for the beacon-based collision avoidance system The algorithms were structured to permit great flexibility HC A04/MF A01 CSCL 01/5 in an experimental environment, and incorporate a number of The plan described in this document supports the overall program at the Transportation Systems Center to define, design selectable options in the collision avoidance logic and in the display output One option permits the selection of either a develop and evaluate systems that meet the requirements of passive mode logic or an active mode logic When the passive airport surface traffic control This plan is part of documentation supporting one aspect of the program, visual ground aids mode is selected other options allow horizontal positive or negative commands to be used In addition the display of positive development There are twenty-four concerns with the present visual ground aids The concerns deal with the ability of the or negative commands can be selected or suppressed and limit present system and its components to support taxiing operations vertical rate commands can be selected for display in- in the lower visibility environment found during Category III dependently of positive or negative commands Two types of intruder position data can also be selected for display The logic conditions This report describes an engineering and development can drive three types of cockpit displays Author plan which will identify solutions for the concerns create the specifications for improved visual ground aids and lay the ground work for application in future Category Ml operations The N78-16032# Mitre Corp McLean va METREK Div management of the development process leading to major ASSESSMENT OF THE PERFORMANCE OF AN ACTIVE improvements in the present system is described The plan ATCRBS MODE FOR BEACON COLLISION AVOIDANCE includes a schedule budget, milestones and evaluation criteria N A Spencer Paul M Ebert and Leonard T Moses Dec Author (GRA) 1977 132 p refs (Contract DOT-FA69NS-162) N78-16038$ Transportation Systems Center. Cambridge, Mass (AD-A047670 MTR-7645 FAA-RD-77-151) Avail NTIS AIRPORT SURFACE TRAFFIC CONTROL TAGS PLANNING HC A07/MF A01 CSCL 01/2 ALTERNATIVES AND COST/BENEFIT ANALYSIS Final The active air traffic control radar beacon system mode of Report. Dec 1975 - Mar 1976 the beacon collision avoidance system (BCAS) was tested in a Paul S Rempfer Jan 1977 51 p refs National Aviation Facilities Experiment Center (NAFEC) airborne (AD-A037790, TSC-FAA-76-23, FAA-RD-77-9) Avail NTIS test bed After conducting many flights for purposes of the system HC A04/MF A01 CSCL 17/7 shakedown design refinement and the setting of parameters a The findings of a cost/benefit analysis of the deployment of series of detailed data collection flights was run The results of a new airport ground surveillance system TAGS (Tower Automated approximately 100 one-on-one aircraft encounters were presented Ground Surveillance) are presented TAGS will provide a plan in which the ability of BCAS to give a proper maneuver command view display of aircraft on the airports taxiways and runways was examined then results of one and one-quarter hours of like ground surveillance radar (ASDE) but unlike ASDE. TAGS data on targets-of-opportunity in the environment of the will perform in heavy precipitation and automatically acquire and Washington D C TCA flights with a controlled target in the display aircraft flight identity The findings indicate that a TAGS airspace near NAFEC were examined to explore the effects of deployment of between four and nine systems is cost/beneficial antenna coverage A comparison was made between the results The development plan system costs analysis Approach and obtained in Washington those from NAFEC flights and those sensitivity analysis supporting the findings are provided from simulated scenarios were fed into the operating processor Author (GRA) Author

N78-16035$ Stanford Telecommunications Inc McLean Va N78-16O40 Aeronautical Research Labs Melbourne (Australia) THE SINGLE-SITE COLLISION AVOIDANCE SYSTEM STABILITY OF HELICOPTER SLUNG LOADS (SS-CAS1 N Matheson Aug 1976 59 p refs L Schuchman and R Orr 16 Sep 1977 151 p refs Sponsored (ARL/AERO-Note-364) Copyright Avail Issuing Activity in part by FAA Recent developments and data available concerning the (Contract F04701-75-C-0239) operation of helicopters with slung loads are reviewed In (AD-A045977 FAA-EM-77-8) Avail NTIS HC A08/MF A01 particular slung load aerodynamic instabilities vertical bounce CSCL 17/7 and sling leg flapping are considered Methods for reducing SS-CAS is a unique beacon collision avoidance system which these instabilities and procedures for extending the operating works in conjunction with the current and next generation air limits of a helicopter with different types of slung loads are traffic control surveillance systems (ATCRBS and DABS) In its discussed Author passive mode SS-CAS provides three dimensional positions of both user and target aircraft using beacon replies from only one N78-16041 Arizona State Univ. Tempe ground-based DABS or ATCRBS interrogator Full collision SENSITIVITY ANALYSIS OF OPTIMAL FLIGHT TRAJECTO- avoidance service is provided in both the all-ATCRBS environment RIES Ph D Thesis

196 N78-16047

Matthew Allison Nichols 1977 166 p William D Mark Dec 1977 138 p refs Avail Univ Microfilms Order No 77-25887 (Contract NAS1-14413) Aircraft performance sensitivity to variations in aerodynamic (NASA-CR-2913 Rept-3496) Avail NTIS HC A07/MF A01 and atmospheric conditions was analyzed The energy state CSCL 01C approximation was used to reduce the complexity of the aircraft Mathematical expressions were derived for the exceedance equations of motion permitting the use of optimizing functional rates and probability density functions of aircraft response variables determined from variations! techniques The minimum time and using a turbulence model that consists of a low frequency minimum fuel trajectories were determined for the supersonic component plus a variance modulated Gaussian turbulence F-4 aircraft Having determined the performance under nominal component The functional form of experimentally observed conditions variations in aerodynamic terms and atmospheric concave exceedance curves was predicted theoretically the conditions were introduced along the optimal trajectory It was strength of the concave contribution being governed by the found that aircraft flight time and fuel consumption are sensitive coefficient of variation of the time fluctuating variance of the to variations in aircraft thrust, drag coefficients and weight turbulence Differences in the functional forms of response Furthermore, a hot day atmosphere increased ftlight time and exeedance curves and probability densities also were shown to fuel consumption while a cold day atmosphere reduced flight depend primarily on this same coefficient of variation Criteria time and fuel consumption Dissert Abstr were established for the validity of the local stationary assumption that is required in the derivations of the exceedance curves and N78-16042*# National Aeronautics and Space Administration probability density functions These criteria are shown to depend Langley Research Center, Langley Station Va on the relative time scale of the fluctuations in the variance GEMPAK AN ARBITRARY AIRCRAFT GEOMETRY the fluctuations in the turbulence itself and on the nominal GENERATOR duration of the relevant aircraft impulse response function Metrics Sharon H Stack. Clyde L W Edwards, and William J Small that can be generated from turbulence recordings for testing Dec 1977 167 p refs the validity of the local stationary assumption were developed (NASA-TP-1022 L-11666) Avail NTIS HC A08/MF A01 Author CSCL01C A computer program. GEMPAK has been developed to aid in the generation of detailed configuration geometry The program N78-16045*# Gates Learjet Corp Wichita Kans was written to allow the user as much flexibility as possible in CONCEPTUAL DESIGN OF SINGLE TURBOFAN ENGINE his choices of configurations and the detail of description desired POWERED LIGHT AIRCRAFT and at the same time keep input requirements and program F Samuel Snyder, C Gene Voorhees Allyn M Hemnch and turnaround and cost to a minimum The program consists of Donald N Baisden Mar 1977 174 p refs routines that generate fuselage and planar-surface (wmglike) (Contract NAS2-9242) geometry and a routine that will determine the true intersection (NASA-CR-151972) Avail NTIS HC A08/MF A01 CSCL of all components with the fuselage This paper describes the 01C methods by which the various geometries are generated and The conceptual design of a four place single turbofan provides input description with sample input and output Also engine powered light aircraft was accomplished utilizing contem- included are descriptions of the primary program variables and porary light aircraft conventional design techniques as a means functions performed by the various routines The FORTRAN of evaluating the NASA-Ames General Aviation Synthesis Program program GEMPAK has been used extensively in conjunction with (GASP) as a preliminary design tool In certain areas disagreement mterfaces to several aerodynamic and plotting computer or exclusion were found to exist between the results of the programs and has proven to be an effective aid in the preliminary conventional design and GASP processes Detail discussion ot design phase of aircraft configurations Author these points along with the associated contemporary design methodology are presented Author

N78-16046*# Old Dominion Univ Norfolk Va School of N78-16043*# Boeing Commercial Airplane Co Seattle Wash Engineering STUDY OF METALLIC STRUCTURAL DESIGN CONCEPTS ANALYSIS OF SPREAD MULTI-JET VTOL AIRCRAFT IN FOR AN ARROW WING SUPERSONIC CRUISE CONFIG- HOVER Final Technical Report URATION Final Report, Tasks 1 and 2 Leroy F Albang and A Sidney Roberts Dec 1974 89 p refs M J Turner and D L Grande Dec 1977 147 p refs (Contract NAS1-11707) (Contract NAS1-12287) (NASA-CR-155582, TR-74-T8) Avail NTIS HC A05/MF A01 (NASA-CR-2743. D6-42438-3) Avail NTIS HC A07/MF A01 CSCL 01C CSCL 01C An investigation of vertical takeoff and landing aircraft lift A structural design study was made to assess the relative losses in hover was conducted to evaluate a method for a simplified merits of various metallic structural concepts and materials for test technique Three flat plate models were tested to determine an advanced supersonic aircraft cruising at Mach 2 7 Preliminary their usefulness in predicting hover characteristics by comparing studies were made to ensure compliance of the configuration results between plate and three-dimensional models Data with general design criteria integrate the propulsion system with obtained for the plate models were correlated to three-dimensional the airframe select structural concepts and materials, and define results by the application of a geometrical equivalent height an efficient structural arrangement An advanced computerized correction factor The correlation of plate and tunnel models structural design system was used in conjunction with a relatively indicated that lift losses in ground effect were essentially large complex finite element model for detailed analysis and independent of the efflux characteristics for the engine simula- sizing of structural members to satisfy strength and flutter criteria tors Author A baseline aircraft design was developed for assessment of current technology Criteria analysis methods and results are presented The effect on design methods of using the computerized N78-16047# Air Force Aero Propulsion Lab Wright-Patterson structural design system was appraised, and recommendations AFB Ohio are presented concerning further development of design tools QUIET PROPELLER/ROTOR CONCEPT EVALUATION Final development of materials and structural concepts and research Technical Report, 1 Feb 1971 - 31 Oct 1976 on basic technology Author Paul A Shahady. Craig A Lyon, Matthew H Chopin Mark S Ewmg and Robert M McGregor Oct 1977 185 p refs (AD-A047297. AFAPL-TR-77-56) Avail NTIS HC A09/MF A01 CSCL 01/3 N78-16044*# Bolt Beranek, and Newman. Inc Cambridge This report describes an exploratory development program Mass to experimentally evaluate the noise characteristics of several CHARACTERIZATION OF NONGAUSSIAN ATMOSPHERIC quiet propeller configurations so determine the noise reduction TURBULENCE FOR PREDICTION OF AIRCRAFT RESPONSE potential of various new designs Variables investigated include STATISTICS Final Report number of blades blade-to-hub phasing angles and blade length

197 N78 16O48

Performance and acoustic tests were conducted on modified different classes of airports non-hierarchical groups consist of UH-10 helicopter tail rotor blades in a specially designed hub avionics equipment which give an aircraft additional capability The hub allowed the spacing between each blade to be but which are not required equipment according to FAA independently varied so that the effects of modulated blade spacing regulations Once the framework was developed the GA fleet could be studied The configurations tested included a 9 33 ft as represented by the 1974 Aircraft Statistical Master File was diameter six-bladed baseline rotor the same rotor with 6% and distributed among the capability groups and its characteristics 10% modulated blade spacing a six-bladed rotor with leading were studied In addition individual capability groups were edge rakes a two-bladed rotor and several rotor configurations analyzed to discover subgroups of aircraft with homogeneous with unequal blade lengths on the hub Author (GRA) characteristics This report presents the methodologies used in the analyses statistical tables and other results Author (GRA) N78 16O48# RAND Corp Santa Monica Calif A CRITIQUE OF AIRCRAFT AIRFRAME COST MODELS Interim Report N78-16051 *# \National Aeronautics and Space Mamimstration J P Large and K M S Gillespie Sep 1977 63 p refs Washington D C (Contract F49620-77-C-0023) INVESTIGATION OF THE JET-WAKE FLOW OF A HIGHLY (AD-A047181 R-2194-AF) Avail NTIS HC A04/MF A01 LOADED CENTRIFUGAL COMPRESSOR IMPELLER Doc- CSCL 01/3 toral Dissertation This document examines a sample of seven aircraft airframe Dietrich Eckardt Jan 1978 194 p refs Transl into ENGLISH cost models The intent is to determine whether the model output from Untersuchung der Strahl/Totwasserstromung hinter emem is reasonable over a broad range of inputs, what limitations Hochbelasteten Radialverdichterlaufrad (West-Germany) 1977 should be noted and where one model might be preferable to p 1-227 Transl by Kanner (Leo) Associates Redwood City the others The critique shows that all the models have some Ohf Original Doc Prep by Rhein Westfael Technical School deficiencies and all should be used with caution The more recent Aachei_ models appear to be better than the older ones which may be (Contra'ct "NASw-2790) taken as a sign of progress, but it is plain that more progress (NASA-TM-75232) Avail NTIS HC A09/MF A01 CSCL21E is needed Some of the lessons learned in this review may be Investigations aimed at developing a better understanding helpful in pointing out how the next generation of aircraft airframe of the complex flow field in high performance centrifugal cost models could be improved Author compressors were performed Newly developed measuring techniques for unsteady static and total pressures as well as N78-16049# Boeing Aerospace Co. Seattle, Wash Military flow directions and a digital data analysis system for fluctuating Airplane Development signals were thoroughly tested The loss-affected mixing process SPECIFICATIONS FOR IDAMST SOFTWARE Final Technical of the distorted impeller discharge flow was investigated in detail, Report. Apr - Jun 1976 in the absolute and relative system, at impeller tip speeds up to David G Tubb Jul 1977 130 p refs 380 m/s A theoretical analysis proved good coincidence of the (Contract F33615-76-C-1099) test results with the DEAN-SENOO theory which was extended (AD-A047163 AFAL-TR-76-208-Vol-1) Avail NTIS to compressible flows Author HC A07/MF A01 CSCL 09/2 The objective of this piogram was to define the operational flight program and operational test program for an Integrated N78-16052*# Fiber Science Inc Gardena Calif Digital Avionics System for the Medium STOL (IDAMST) airplane FILAMENT-WINDING FABRICATION OF QCSEE CONFIG- This effort is part of an Air Force Avionic Laboratory Program URATION FAN BLADES to specify a candidate avionics design based on DAIS technology Sam Yao Jan 1978 22 p The approach involved the development of software requirements (Contract NAS3-20099) derived from the system analysis of the hardware baseline and (NASA-CR-135332) Avail NTIS HC A02/MF A01 CSCL the operational analysis of the AMST mission The software 21E requirements were developed into a specific IDAMST software The design and fabrication of twelve NASA-QCSEE type design The design is described in terms of functional architectural composite fan blades utilizing wet filament winding fabrication and configurational characteristics The design documents consist techniques is described All composite fibers were continuous of four Computer Program Development Specifications type B5 and attached to the root end All components were formed per MIL-STD-490 and MIL-STD-483 The IDAMST software bonded and co-cured in one molding process Advanced fiber design was based on DAIS architecture and adapted as required materials used in the blade fabrication were Thornel-300 Carbolon to meet the IDAMST requirements The DAIS architecture proved Z-2-1 and Carbolon Z-3 graphite in an epoxy resin matrix to be flexible allowing the design to be extended in IDAMST Author without major change The IDAMST system defined satisfies the functional and operational requirements of the AMST The N78-16053*# National Aeronautics and Space Administration design consists of a dual redundant processor with a reprogram- Lewis Research Center Cleveland Ohio mable backup processor Author (GRA) COLD-AIR PERFORMANCE OF FREE-POWER TURBINE DESIGNED FOR 112 KILOWATT AUTOMOTIVE GAS- TURBINE ENGINE 1 DESIGN STATOR-VANE-CHORD N78-16050# Transportation Systems Center Cambridge Mass SETTING ANGLE OF 35 DEC GENERAL AVIATION AVIONICS STATISTICS 1974 Annual Milton G Kofskey and William J Nusbaum Jan 1978 23 p Report. CY 1974 refs Judith C Schwenk ed Aug 1977 116 p refs (NASA-TP-1007 CONS/1011-12 E-8964) Avail NTIS (AD-A045209 TSC-FAA-77-1 1 FAA-MS-77-2) Avail NTIS HC A02/MF A01 CSCL 21 E HC A06/MF A01 CSCL 09/3 A cold air extpenmental investigation of a free power turbine The primary objectives of this study were to (1) provide a designed for a 112-kW automotive gas-turbine was made over framework for viewing the general aviation (GA) aircraft fleet a range of speeds from 0 to 130 percent of design equivalent which would relate airborne avionics equipment to the capability speeds and over a range of pressure ratio from 1 11 to 2 45 for an aircraft to perform in the National Airspace System and Results are presented in terms of equivalent power torque mass (2) within this framework to portray the types of aircraft flow and efficiency for the design power point setting of the common to the GA fleet in terms of descriptive information on variable stator Author the aircraft To provide the framework capability groups of avionics equipment were designed and translated into aircraft capability to perform certain functions in the airspace system Two types N78-16054*# Pratt and Whitney Aircraft Group tast Hartrord of groups evolved hierarchical groups consist of avionics Conn Commercial Products Div equipment meeting FAA requirements for flying in different AN ANALYTICAL STUDY OF THERMAL BARRIER COATED airspace segments in different conditions and for landing at FIRST STAGE BLADES IN A JT9D ENGINE

198 N78-16063

William R Sevcik and Barry L Stoner Jan 1978 33 p refs performance shift during operation of the FB-111A aircraft Details (Contract NAS3-21033) of the test conducted at Pease AFB during September 1974 (NASA-CR-135360 PWA-5590) Avail NTIS are given along with analysis of the data by P/WA GD/FW. HC A03/MF A01 CSCL 21 E and Hq SAC/LGME Measurement of ambient temperature Steady state and transient heat transfer and structural instrument uncertainty in the trim procedure, and assumption of calculations were completed to determine the coating and base constant inlet operation for simplification were found to be the alloy temperatures and strains Results indicate potential for prime causes of the apparent performance or trim shift increased turbine life using thin durable thermal barrier coatings Recommendations for improvement are given Author (GRA) on turbine airfoils due to a significant reduction in blade average and maximum temperatures and alloy strain range An intepreta- N78-16059# Bolt Beranek, and Newman Inc Canoga Park. tion of the analytical results is compared to the experimental Calif engine test data Author PHYSICAL ANALYSIS OF THE IMPULSIVE ASPECTS OF HELICOPTER NOISE Final Report N78-16055*# National Aeronautics and Space Administration William J Galloway Apr 1977 394 p refs Lewis Research Center Cleveland Ohio (Contract WI-77-3683-1) A REVIEW OF NASA'S PROPULSION PROGRAMS FOR (AD-A039715. BBN-3425. FAA-EQ-77-8) Avail NTIS AVIATION HC A17/MF A01 CSCL 01/3 Warner L Stewart Harry W Johnson and Richard J Weber An evaluation is made of several helicopter flyover noise 1978 21 p refs Presented at the 16th Aerospace Sci Meeting calculation schemes intended to describe signal impulsive Huntsville Ala 16-18 Jan sponsored by AIAA character These schemes were proposed by ICAO member (NASA-TM-73831) Avail NTIS HC A02/MF A01 CSCL21A organizations Data are presented for various recorded flyovers A review of five NASA engine-oriented propulsion programs and for simulations of helicopter flyovers Author (GRA) of major importance to civil aviation are presented and discussed Included are programs directed at exploring propulsion system N78-16O61 Stanford Umv , Calif concepts for 11) energy conservation subsonic aircraft (improved UNSTEADY AERODYNAMIC MODELING AND ACTIVE cc.lent turbofans advanced turbofans and advanced turboprops) AEROELASTIC CONTROL Ph D Thesis (2) supersonic cruise aircraft (variable cycle engines) (3) general John Will,am Edwards 1977 209 p aviation aircraft (improved reciprocating engines and small gas Avail Umv Microfilms Order No 77-25659 turbines) (4) powered lift aircraft (advanced turbofans) and (5) Unsteady aerodynamic modeling techniques are developed advanced rotorcraft Author and applied to the study of active control of elastic vehicles The problem of active control of a super-critical flutter mode N/B-16056# Purdue Univ Lafayette Ind poses a definite design goal—stability and is treated in detail PROJECT SQUID Semiannual Progress Report. 1 Apr - The transfer functions relating the arbitrary airfoil motions to 30 Sep 1977 the airloads are derived from the Laplace transforms of the T C Adamson. F Browand, Edgar P Bruce Franklin Carta, and linearized airload expressions for incompressible two-dimensional A Dean 1 Oct 1977 100 p refs Prepared by MIT flow The transfer function relating the motions to the circulatory Cambridge part of these loads is recognized as the Theodorsen function (Contract N00014-75-C-1143 Proi SQUID) extended to complex values of reduced frequency, and is termed (AD-A047076) Avail NTIS HC A05/MF A01 CSCL 20/4 the generalized Theodorsen function A brief critique of previous Progress on 20 research programs comprising Project SQUID attempts to generalize the Theodorsen function is given Inversion are presented The research programs fall into the areas of of the Laplace transforms yields exact transient airloads and Aerodynamics and Turbomachinery, Combustion and Chemical airfoils motions Exact root loci of aero-elastic modes are Kinetics Measurements and Turbulence Project SQUID is a calculated providing quantitative information regarding subcntical cooperative program of basic research related to jet propulsion and supercritical flutter conditions Dissert Abstr GRA

N78-16057# Air Force Inst of Tech Wright-Patterson AFB N78-16O62*# National Aeronautics and Space Administration Ohio Ames Research Center. Moffett Field Calif A METHODOLOGY FOR ESTIMATING THE ECONOMIC AERODYNAMIC CHARACTERISTICS OF AN F-8 AIRCRAFT BENEFITS OF AN AIRCRAFT ENGINE WARRANTY CONFIGURATION WITH A VARIABLE CAMBER WING AT M S Thesis MACH NUMBERS FROM 1 S TO 2 0 Martin P Dooley and Richard E Kells Sep 1977 135 p refs Frederick W Boltz Dec 1977 70 p (AD-A047282. AFIT-LSSR-10-77B) Avail NTIS (NASA-TM-73271, A-7141) Avail NTIS HC A04/MF A01 HC A07/MF A01 CSCL 14/1 CSCL 01C Aircraft engine warranties are used extensively in the A 0 1 -scale model of an F-8 aircraft was tested over a commercial airlines industry If the Department of Defense hopes range of Mach numbers from 1 5 to 2 0 Reynolds number of to use warranties as a method of reducing engine life cycle 412 million was based on wing mean-aerodynamic chord for costs the costs and benefits of each warranty must be carefully angles of attack varying from -2 deg to +12 deg The model analyzed The methodology developed in this study provides was equipped with an advanced-technology-conformal-variable- framework to assist analysts in estimating the economic benefits camber wing (ATCVCW) having simple hinge flaps Data were of an engine warranty A test application of the methodology also obtained for the model equipped with the basic F-8 wing details the benefits of a hypothetical DOD engine warranty, and and conventional flaps Model variables included aileron and wing includes a sensitivity analysis of the key variables The study trailing edge deflections and horizontal tail incidence The ATCVCW concludes that the basic method can be used to estimate the configuration produced slight improvements in lift-curve slope economic benefits of a wide range of engine and equipment drag and static longitudinal stability over that of the basic F-8 warranties Author (GRA) wing configuration Flap effectiveness was essentially the same for both wings Author

N/»-16Ob8# straieyic Air Command, urtutt AFB Nebr Aircrart Engineering Div N78-16O63*# National Aeronautics and Space Administration TF-30-P-7 INSTALLED TRIM CORRECTION Engineering Ames Research Center Moffett Field Calif Report. Aug 1973 - Jan 1977 STUDY OF THE APPLICATION OF AN IMPLICIT MODEL- James L Pettigrew 14 Jan 1977 70 p refs FOLLOWING FLIGHT CONTROLLER TO LIFT-FAN VTOL (AD-A047023. SAC/LGME-ER-P-206) Avail NTIS AIRCRAFT HC A05/MF A01 CSCL 21/5 Vernon K Mernck Nov 1977 180 p refs This report summarizes the findings from engineering tests (NASA-TP-1040 A-6712) Avail NTIS HCA09/MFA01 CSCL conducted to determine causes of observed TF30-P-7 engine QIC

199 N78-16064

An implicit model-following flight controller is proposed This N78-16067# SRI International Corp Menlo Park Calif All controller is relatively simple in concept it provides an input/ Weather Landing Systems output relationship that is approximately that of any selected PILOTED FLIGHT SIMULATOR STUDY OF LOW-LEVEL second order system, it provides good gust alleviation and it is WIND SHEAR. PHASE 2 Interim Report, Aug 1976 - Mar self-trimming The flight controller was applied to all axes of a 1977 comprehensive mathematical model of a lift-fan V/STOL transport W B Gartner D W Ellis W H Foy M G Keenan A C Power management controls and displays were designed to match McTee and W 0 Nice Mar 1977 189 p refs the various modes of control provided by the flight controller A (AD-A047251 FAA-RD-77-157) Avail NTIS piloted simulation was performed using a six degree of freedom HC A09/MF A01 CSCL 01/3 simulator The fixed-operating-point handling qualities throughout Task 2 of the All-Weather Landing Systems project is the powered lift flight envelope received pilot ratings of 3-1/2 concerned with piloted flight simulation tests of various techniques or better Approaches and vertical landings in IFR zero-zero designed to aid the pilot to detect and cope with low level conditions received pilot ratings varying from 2-1/2 to 4 depending wind shear on approach and landing The operational situation on the type of approach and weather conditions Author of a DC-10 aircraft landing in Category 1 visibility with ILS guidance was simulated Wind corresponding to inversion-layer frontal thunderstorm and no-shear conditions were simulated to N78-16064*| Colorado Univ Boulder provide test profiles The baseline aiding concept was the DESIGN OF NONINTERACTING FLIGHT CONTROL conventional DC-10 manual approach management The aiding SYSTEMS IN THE PRESENCE OF LARGE PARAMETER concepts tested were based on ground speed displays (first VARIATIONS Final Report. 1 Jul 1975 - 30 Nov 1977 experiment) flight path angle (second), and modified (acceleration- Frank S Barnes Nov 1977 86 p refs augmented) flight director (third experiment) Author (Grant NsG-1213) (NASA-CR-155589) Avail NTIS HC A05/MF A01 CSCL 01C N78-16068$ Naval Civil Engineering Lab, Port Hueneme, Calif The effects of system parameter variations on the over-all EXPERIMENTAL RELATIONSHIPS BETWEEN MODULI FOR system stability were considered Results from the application SOIL LAYERS BENEATH CONCRETE PAVEMENTS of numerical minimization to reduce system coupling are given Final Report, Jun 1975 - Jan 1976 and some future research directions are outlined Author J B Forrest P S Sprmgston M G Katona, and J Rollins Jun 1977 245 p refs (Contract DOT-FA74WAI-487) (AD-A046239/0 FAA-RD-76-206) Avail NTIS HC A11/MF A01 CSCL 01/5 N78-16065$ Dynamic Controls Inc. Dayton Ohio Two subgrades and four rigid pavement test sections were RESEARCH AND DEVELOPMENT OF AIRCRAFT CONTROL constructed and instrumented to recover experimental information ACTUATION SYSTEMS THE DEVELOPMENT OF A DIRECT of soil/rigid pavement behavior static loadings Pavement DRIVE FLY-BY-WIRE FLIGHT CONTROL SYSTEM AND deflections and pavement/soil strain data were recorded for EVALUATION OF A FORCE SHARING FLY-BY-WIRE incremental static loads applied to a 30 inch diameter steel ACTUATOR Final Report. Feb 1975 - Jun 1977 plate Tests were conducted for comparison of experimentally Gavin D Jenney Sep 1977 216 p collected data with Westergaard and elastic layer analyses of (Contract F33615-75-C-3068) the test sections to investigate whether a consistent mathematical (AD-A047283, AFFDL-TR-77-91) Avail NTIS relationship exists between the two methods of analysis To HC A10/MF A01 CSCL 01/4 this end material characterizations were carried out for the This report describes the design and test evaluation of a component materials in the four different pavement sections and direct drive fly-by-wire redundant control system Also included analytically predicted and experimentally obtained response data in the report is the evaluation testing of a fly-by-wire tandem were compared Author actuator mechanization developed by Parker-Hannifin Aerospace Hydraulics Division Irvine California The direct drive system is N78-16069# Naval Postgraduate School, Monterey. Calif based on using moving coil force motors to position a hydraulic EVALUATION OF AND OPERATIONAL PROCEDURES FOR control valve without hydraulic amplification The system is A HELICOPTER SIMULATION SYSTEM UTILIZING AN designed as a single fail operate system which will accept one INTEGRATED ELECTRONIC INSTRUMENT DISPLAY input or component failure and continue to operate with M S Thesis acceptable performance The test results verified that the failure William Woodrow Fetzer Jr Jun 1977 89 p refs modes and performance met the design goals The system (AD-A047166) Avail NTIS HC A05/MF A01 CSCL 01/4 incorporates component dispersion techniques to allow single This report discusses the evaluation and documentation of hit survivability The direct drive mechanization offers adequate an integrated electronic instrument display designed to investigate performance with minimum complexity as a fly-by-wire control stability and control of a helicopter during precision hover system The Parker-Hannifin actuator mechanization is a two operations The equations of motion developed from the Kaman fail operate configuration using an integrated secondary actuator SH-2F Seaspnte helicopter were implemented by a hybrid with both force and position summing The test results document computer system and displayed by a graphics processor A the operational characteristics of the design Author (GRA) complete procedural checklist including troubleshooting methods, is included in this report This helicopter simulation system can be used for further research in the development of optimal heads-up display configurations as well as analyses of instability caused by pilot induced oscillations in the hover flight regime N78-16O66~# Douglas A i re ran Co, Inc Long Beach Calif Author (GRA) EXPANSION OF FLIGHT SIMULATOR CAPABILITY FOR STUDY AND SOLUTION OF AIRCRAFT DIRECTIONAL N78-16070# Air Force Inst of Tech Wright-Patterson AFB. CONTROL PROBLEMS ON RUNWAYS, APPENDIXES Ohio School of Systems and Logistics J A McGowan 20 Jan 1978 224 p refs AN ASSESSMENT OF RELEVANT DECISION MAKING (Contract NAS1-13981) FACTORS FOR ORGANIC VERSUS CONTRACT MAINTE- (NASA-CR-145281) Avail NTIS HC A10/MF A01 CSCL NANCE OPTIONS ON USAF FLIGHT SIMULATORS 14B M S Thesis The models used to implement the DC-9-10 aircraft simulation Ronald J Arceneaux and George E Farsshman, Jr Sep 1977 for the Runway Direction Control study are presented The study 137 p refs was done on the Douglas Aircraft six-degree-of-freedom motion (AD-A047136 AFIT-LSSR-7-77B) Avail NTIS simulator Documentation of the models was in algebraic form, HC A07/MF A01 CSCL 05/1 to the extent possible Effort was directed toward presenting Since the maintenance on flight simulators is reportably what was actually done rather than general forms Author manpower intensive, the use of contract maintenance is often

200 N78-16245 suggested A taxonomy of relevant decision maning factors was installation of an alternate model support system using a not available for the maintenance managers use when evaluating centerplate mount was accomplished An aerodynamic evaluation the alternatives of contracting for maintenance or maintaining for comparing the two model mounting concepts was performed an organic capability This research effort has identified some via experiments with a single calibration wing Additionally relevant decision making factors for a maintenance manager to these experiments were the first operational exercise of a recently consider when addressing the issue of contract maintenance versus developed microprocessor data acquisition system Author (GRA) organic maintenance at the organizational and intermediate level The data were obtained from open-end interviews on which an analysis was performed utilizing a technique of behavioral research N78-16074# Federal Aviation Administration. Washington. D C called semantic content analysis The data analysis allowed for a determination of the relevant decision making factors and the Office of Aviation System Plans subsequent recommendations on the development of a contract REMOTENESS-COMPENSATION METHODOLOGY FOR BENEFIT/COST ESTABLISHMENT AND DISCONTINUANCE maintenance decision tree network Basically this decision tree would allow a manager to evaluate the options of contract CRITERIA Final Report maintenance versus organic maintenance making a determination Jan 1977 55 p of which is optimal for the given situation The factors identi- (AD-A043836. FAA-ASP-76-7) Avail NTIS HC A04/MF A01 fied by this research are considered to be cost drivers of the CSCL 01/5 applicable maintenance option Author (GRA) This report develops a procedure for adjusting the benefit/cost (B/C) ratios by which proposals for FAA terminal facilities m remote locations are evaluated The procedure is applicable to N78-16071# Naval Postgraduate School Monterey. Calif the types of installations for which B/C analyses, based on AN EVALUATION OF THE FIDELITY OF MOTION SIMULA- nationwide average data are incorporated in Airway Planning TORS USING A MODEL OF HUMAN DYNAMIC ORIENTA- Standard Number One (FAA Order 7031 2B) Without such an TION M S Thesis adjustment, proposals for facilities in Alaska and other such Richard G Fuller Sep 1977 94 p refs locations could not realistically be compared with those for IAD-A047120) Avail NTIS HC A05/MF A01 CSCL 06/16 facilities in the contiguous 48 states (CONUS) The compensatory A deterministic simulation using a model of human dynamic methodology first adjusts construction and installation costs orientation was written to optimize the parameters of the motion according to a geographically differentiated index Staff housing base control system for a six-degree-of-freedom flight simulator cost is subtracted Exceptional site-preparation and other cost An experiment requiring pilots to rate different levels of motion elements are not discarded but their cost is made equivalent to fidelity during a basic flight task provided a data base for validation the cost of doing the same work at a corresponding CONUS of the simulation Ratings between subjects for linear, rotational site Next for facilities to serve remote communities shown to and combined motion cues were inconsistent due in part to be exceptionally reliant on air transportation, the ascribed the subjects lack of experience in the F-15 aircraft and proficiency benefits are adjusted upward This benefit enhancement is in high performance aircraft The coefficient of concordance among proportional to the communities aviation-dependency as subjects for the three ratings were 4483 4835 and 5914 determined by the model contained in this report but it is not respectively Comparison of simulation results with experimental permitted to more than double intrinsic benefits The benefit- data yielded positive correlations as high as 5138 Response of enhancement premium is earned by a relatively few sites where the simulation to changing wash-out filter parameters was large numbers of citizens are without alternative transportation investigated and found to be adaptable to experimental optimiza- links to the outside world for extended periods Author (GRA) tion methods Author iGRA) N78-16075# Federal Aviation Administration Washington. D C N78-16072# Calspan Corp Buffalo N Y Office of Aviation System Plans WIND TUNNEL MODEL STUDY OF THE HOT EXHAUST ESTABLISHMENT OF NEW MAJOR PUBLIC AIRPORTS IN PLUME FROM THE COMPRESSOR RESEARCH FACILITY THE UNITED STATES AT WRIGHT-PATTERSON AIR FORCE BASE. OHIO Final Aug 1977 140 p Report. May 1976 - Jun 1977 (AD-A046462, FAA-ASP-77-3) Avail NTIS HC A07/MF A01 Gary R Ludwig Oct 1977 59 p refs CSCL 01/5 (Contract F33615-76-C-2092) This study was performed in response to Section 26(2) of (AD-A047205 CALSPAN-XE-5933-A-101 AFAPL-TR-77-58) the Airport and Airway Development Act Amendments of 1976 Avail NTIS HC A04/MF A01 CSCL 13/2 (Public Law 94-353) which directed the Secretary of Transporta- This report presents the results of a wind tunnel model tion to conduct a study on the establishment of a new major study to determine temperatures at various locations generated public airports in the United States including (a) identifying by the hot exhaust air from the Compressor Research Facility potential locations (b) evaluating such locations and (c) (CRF) which is being built at Wright-Patterson Air Force Base investigating alternative methods of financing the land acquisition Ohio The study was designed to provide data at the inlet to and development costs necessary for such establishment The the CRF and at other nearby locations where pedestrians report assesses needs for major new airports in the United States ouilding ventilation systems and vegetation might be affected through the year 2000 Potential airport locations the general The test program which was conducted in the Calspan size requirements of new airports financing, and airport Atmospheric Simulation Facility included flow visualization studies development issues and problems are also analyzed under a and quantitative concentration measurements of a tracer gas variety of future conditions The potential need for new major from which full-scale temperatures could be calculated The airports is highly sensitive to the future forecasted activity extent concentration measurements were performed for a number of of accommodation of general aviation effectiveness of the wind speeds at each of twelve different wind directions Two upgraded third generation air traffic control system in increasing exhaust flows and two exhaust stack configurations were capacity and peak spreading, in that order Author (GRA) studied Author (GRA)

N78-16073# Naval Research Lab Washington D C DESIGN STUDY OF A CENTERPLATE MOUNT FOR WIND N78-16245$ Transportation Systems Center Cambridge, Mass TUNNEL MODELS M S Thesis PRELIMINARY LIMITED SURVEILLANCE RADAR (LSR) Robert Wayne Russell Jun 1977 114 p refs COST/BENEFIT ANALYSIS Final Report. Dec 1976 - Apr (AD-A047204) Avail NTIS HC A06/MF A01 CSCL 14/2 1977 A three-strut wind-tunnel model support system was being Paul S Rempfer Oct 1977 53 p refs used with an electrical balance m the 3 5 by 50 foot Department (AD-A046829 TSC-FAA-77-16) Avail NTIS of Aeronautics low-speed wind tunnel The traditional method HC A04/MF A01 CSCL 17/9 of image systems and alternate inverted mounting for the This report presents the findings of a cost/benefit analysis evaluation of aerodynamic tares was considered impractical for of the deployment of a new Limited Surveillance Radar (LSR) implementation in the small sized tunnel The design and An LSR is an inexpensive single channel short-range (about

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20 miles) primary radar for use at approach control facilities some 36,000 values m a sequence of maximum and minimum which cannot economically justify an Airport Surveillance loads The sequence of loads was generated from a set of matrices Radar/Radar Beacon System (ASR/RBS) An LSR can also be representing the bivanate distributions of load for three characteris- used in tower cabs to aid in VFR operation where a BRITE tic flight missions and from other statistical data concerning display is not feasible due to coverage limitations dictated by flight duration, aircraft configuration, and ground loads by obstructions or distance from the parent radar facility The study means of a computer program written in FORTRAN This program is preliminary in that it is brief and uses rough estimates and may be adapted to output the load sequence in a form appropriate assumptions for both benefits and costs Its purpose is to give to a particular fatigue testing system, i e punched tape, magnetic a gross estimate of the current deployment potential of the tape, or direct machine output Author LSR and to aid in decisions regarding further system analysis development and testing Author (GRA) N78-16741 Texas Umv. Austin A TANDEM-QUEUE ALGORITHM FOR EVALUATING OVERALL AIRPORT CAPACITY Ph.O Thesis N78-16372fjl Naval Postgraduate School. Monterey. Calif Chang-Ho Park 1977 190 p A STUDY OF PULL-THROUGH FAILURES OF MECHAN- Avail Umv Microfilms Order No 77-23011 ICALLY FASTENED JOINTS M S Thesis Development is given for an analytical model of an airport Robert N Freedman Sep 1977 81 p refs system that can be used to evaluate overall airport capacity (AD-A047142) Avail NTIS HC A05/MF A01 CSCL 13/5 Capacity is defined as the maximum flow-rate that can be imposed The relationship between the bending moment and the on an airport without violating user-specified, level-of-service through-plane shear force in the vicinity of a mechanical fastener criteria for airport components A deterministic queueing at failure was determined Experiments were conducted on 4-mch algorithm is presented The main thrust of the approach is to wide flat plate aluminum and graphite-epoxy composite specimens tie individual component models together to relate the input to that modeled portions of a wing skin along a spar and along a one component and the output to one component and the rib The composite specimens were either 8-ply or 16-ply balanced output from preceding components The overall algorithm is layups and were simply supported at two opposing edges and intended for estimating component level of service measures free along the other two edges The fasteners were pulled normal These measures are then evaluated by the user of the model to the plates, and the maximum force at failure was measured Dissert Abstr for specimen lengths varying from two to six inches between supports Two analyses were made, one for small elastic deflections of a thin orthotropic plate and another for a beam in the elastic range A mesh generator for a finite element model of the plate around the fastener was also developed for the N78-16816# Naval Electronics Lab Center San Diego Calif computer program AOINA GRA A 7 ALOFT ECONOMIC ANALYSIS AND EMI-EMP TEST RESULTS R A Greenwell and G M Holma In AGARD Opt Fibres N78-16376jj( Army Test and Evaluation Command, Aberdeen Integrated Optics and Their Mil Appl Oct 1977 13 p refs Proving Ground, Md Avail NTIS HC A24/MF A01 ARRIVAL INSPECTIONS/PRE-OPERATIONAL INSPEC- Cost projections for three performance-equivalent cable TIONS (AVIATION MATERIEL) Final Report alternatives coaxial twisted-shielded pair and fibre optic were Roy L Miller 31 Aug 1977 22 p refs Supersedes TOP-1-3-505 developed These cost projections were generated by an approach (AD-A047260, TOP-7-3-503 TOP-1-3-505 Avail NTIS which utilizes two techniques one which computes very specific costs of research and development (R&D) investment, and HC A02/MF A01 CSCL 01/3 operation and support (O&S) for the data transmission links, A method is described for evaluation of test item complete- and the other which computes total weapon systems cost of ness conditions, and operabihty upon receipt for testing This R&O investments and O&S resulting from the inclusion of the report identifies the facilities and equipment required It provides field-operation systems The results clearly indicated definite procedures for documents arrival, receiving packaging, mainten- economic benefits with fiber optics Tests were also performed ance test package, item inventory safety preoperational and to determine EMI susceptibility and EMP effects on fiber-optic technical inspections This is applicable to aviation materiel and wire interconnects for the A-7 navigation and weapon delivery Author (GRA) subsystem (NWDS) These tests were performed in the laboratory N78-16391# National Aeronautical Establishment Ottawa and on the aircraft Results from the EMI and EMP tests have (Ontario) shown that the A-7 ALOFT fiber-optic subsystem is less THE DISSECTION OF AN AIRCRAFT LOADS SPECTRUM susceptible to EMI and greatly reduces electromagnetic induction PRODUCED BY PEAK-COUNTING ACCELEROMETERS from an induced transient pulse Author A V Rugiemus 16 Nov 1977 24 p refs (LTR-ST-951. ICAF-978) Avail NTIS HC A02/MF A01 Wing fatigue damage to aircraft was examined in regard to measurements made by peak-counting accelerometers Major causes of damage were defined as repetitive stresses caused by N78-16849jjf Standard Telecommunication Labs Ltd, Harlow ground loads, air loads and the ground-air-ground cycle These (England) phases of the aircraft loads environment were discussed in detail AN OPTICAL FIBRE. MULTI-TERMINAL DATA SYSTEM FOR Recommendations were made on the procedure for converting AIRCRAFT accelerometer data into loads spectra B L P J G Farnngton and M Chown In AGARD Opt Fibres Integrated Optics and Their Mil Appl Oct 1977 12 p refs Sponsored by Ministry of Defense N78-16392# National Aeronautical Establishment Ottawa Avail NTIS HC A24/MF A01 (Ontario) As a result of a study on the potential of optical fiber MODIFICATIONS TO FALSTAFF THAT WERE REQUIRED multitermmal data systems for avionics a design approach was FOR OPERATION ON A 16 K POP Be MINICOMPUTER chosen which is expected to be a suitable basis for a wide Rolf Hangartner 15 Feb 1977 19 p refs range of applications This is a time division multiplexing system, (LTR-ST-899. ICAF-977) Avail NTIS HC A02/MF A01 which has features of being highly immune to problems of optical The FALSTAFF (fighter aircraft loading standard for fatigue loss and multipath effects in optical highways having redundant evaluation) is a computer program that utilizes a Markov chain paths and of avoiding the need for any master terminal This method to generate a simulation of a service load history for a system approach is tailored to characteristics of optical fibers typical fighter aircraft This service load history consisted of 200 and should lead to good integrity and ruggedness A breadboard flights of varying length and seventy and was characterized by model of a terminal was demonstrated Author

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N78-16988 Virginia Polytechnic Inst and State Umv Blacksburg A computer program was developed to solve the low speed THE EFFECT OF WHITCOMB WINGLETS AND OTHER flow around airfoils with highly separated flow The flow model WINGTIP MODIFICATIONS ON WAKE VORTICES includes all of the major physical features in the separated region PhD Thesis Flow visualization tests were made to substantiate to the validity Henry Frederick Faery 1977 175 p of the model The computation involves the matching of the Avail Umv Microfilms Order No 77-26887 potential flow, boundary layer and flows in the separated regions Wind tunnel experiments were conducted on six wingtip Heads entramment theory was used for boundary layer configurations to determine their wake vortex characteristics The calculations and Korst's jet mixing analysis was used in the trailing wingtip vortex was probed by a 1/8 inch diameter five separated regions A free stagnation point aft of the airfoil and hole yawhead pressure probe The vortex tangential and axial a standing vortex in the separated region were modelled and velocity profiles are compared at five and twenty chordlengths computed The separation location and pressure were found downstream The Whitcomb wmglet and the upper winglet iteratively without a priori specification A GAIWI-1 17% thick configuration both produce two distinct vortices of the same airfoil at three angles of attack and two Reynolds numbers rotation The maximum tangential velocity in each vortex is was used for the analysis Dissert Abstr about 64 percent less than that produced by a conventional wingtip configuration The lift and drag characteristics of the N78-16996 Georgia Inst of Tech . Atlanta wingtip configurations are compared The aerodynamic force A NUMERICAL STUDY OF INCOMPRESSIBLE VISCOUS effects of the wing on the winglet and the winglet on the wing FLOW AROUND AIRFOILS Ph D Thesis The downwash distribution on the wing both with and without Sarangan Sampath 1977 215 p wmglets and the effect of different winglet dihedral angles on Avail Umv Microfilms Order No 77-29219 the wing downwash pattern are discussed Dissert Abstr An mtegro-differential formulation for the numerical solution of the two-dimensional incompressible Navier-Stokes equations is developed and applied to the study of dependent incompressible N78-16992 Washington Umv Seattle viscous flow past a 9% thick symmetrical airfoil This formulation UNSTEADY HOVERING WAKE PARAMETERS IDENTIFIED utilizes vorticity and stream function as dependent variables in FROM DYNAMIC MODEL TESTS Ph D Thesis the governing equations and has the capability of confining the Samuel Tribble Crews 1977 123 p computations to the region of non-negligible vorticity thus reducing Avail Umv Microfilms Order No 77-28339 computer time requirements for the study of external viscous The development of a four bladed model rotor that can be flow problems and enables the exact boundary condition on excited with a simple eccentric mechanism in progressing and velocity to be satisfied truly at infinity Based on the integral regressing modes with either harmonic or transient inputs was representation for stream function, a method for the determination reported Parameter identification methods were applied to the of vorticity on the solid surface is also presented With this problem of extracting parameters for linear perturbation models method the physical process of vorticity generation on the solid including rotor dynamic inflow effects from the measured blade surface is correctly simulated and the principle of conservation flapping responses to transient pitch-stirring excitations These of total vorticity is satisfied Dissert Abstr perturbation models were then used to predict blade flapping response to other pitch-stirring transient inputs and rotor wake and blade flapping responses to harmonic inputs The viability N78 16998*# Boeing Vertol Co ."Philadelphia Pa and utility of using parameter identification methods for extracting TWO-DIMENSIONAL WIND TUNNEL TEST OF AN OSCIL- the perturbation models from transients are demonstrated through LATING ROTOR AIRFOIL. VOLUME 2 Final Report these combined analytical and experimental studies L U Dadone 1977 310 p Dissert Abstr (Contract NASt-13795) (NASA-CR-2915 D-210-11188-2) Avail NTIS HC A14/MF A01 CSCL01A For abstract, see N78-16003 N78-16994 Georgia Inst of Tech Atlanta DRAG ON AN OSCILLATING AIRFOIL IN A FLUCTUATING FREE STREAM Ph.D Thesis Sesi Bhushan Rao Kottapalli 1977 161 p N78-16999*# Boeing Commercial Airplane Co. Seattle, Wash Avail Umv Microfilms Order No 77-28579 THE PRACTICAL APPLICATION OF A FINITE DIFFERENCE The unsteady skin friction drag of an oscillating airfoil exposed METHOD FOR ANALYZING TRANSONIC FLOW OVER to a fluctuating free stream speed was investigated The OSCILLATING AIRFOILS AND WINGS Final Report introduction of fluctuations in the free stream alters the skin Warren H Weathenll James D Sebastian, and E Edwards Ehlers friction drag considerably by causing significant fluctuations in Feb 1978 88 p refs the drag There is a considerable difference between the drag (Contract NAS1-14204) behaviors of an airfoil at constant incidence and one undergoing (NASA-CR-2933 D6-44419) Avail NTIS HC A05/MF A01 oscillations about a mean angle of attack both subjected to CSCL 01A identical fluctuating free streams For an airfoil undergoing Separating the velocity potential into steady and unsteady oscillations about a mean angle of attack in a fluctuating free parts and linearizing the resulting unsteady equations for small stream the phase (with respect to the free stream) and amplitude disturbances was performed The steady velocity potential was of the drag fluctuations are strongly dependent on the phase obtained first from the well known nonlinear equation for steady difference between the free stream fluctuations and airfoil transonic flow The unsteady velocity potential was then obtained oscillations Depending on the values of the phase difference from a linear differential equation in complex form with spatially between free stream fluctuations and airfoil oscillations, reduced varying coefficients Since sinusoidal motion is assumed, the frequency and amplitude of free stream fluctuations the drag unsteady equation is independent of time The results of an can either lead or lag the free stream Dissert Abstr investigation into the relaxation-solution-mstabihty problem was discussed Concepts examined include variations in outer boundary conditions, a coordinate transformation so that the boundary condition at infinity may be applied to the outer boundaries of the finite diffprencn repion and overlapping subregions The general conclusion was that only a full direct solution in which all unknowns are obtained at the same time will avoid the solution N78-16996 Kansas Umv , Lawrence instabilities of relaxation An analysis of the one-dimensional form AN ANALYTICAL MODEL FOR THE STUDY OF HIGHLY of the unsteady transonic equation was studied to evaluate errors SEPARATED FLOW ON LOW SPEED AIRFOILS between exact and finite difference solutions Pressure distributions PhD Thesis were presented for a low-aspect-ratio clipped delta wing at Mach Sharad Narayanrao Naik 1977 100 p number of 0 9 and for a moderate-aspect-ratio rectangular wing Avail Umv Microfilms Order No 77-28897 at a Mach number of 0875 . Author

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N78-170OO*# National Aeronautics and Space Administration N78-17006# Deutsche Forschungs- und Versuchsanstalt fuer Ames Research Center Moffett Field Calif Luft- und Raumfahrt. Goettmgen (West Germany) Inst fuer DYNAMIC STALL EXPERIMENTS ON THE NACA 0012 Aeroelastik AIRFOIL SIGNIFICANCE OF STRUCTURAL NONUNEARITIES FROM Kenneth W McAlister Lawrence W Carr, and William J THE STRUCTURAL DYNAMICS AND AEROELASTICITY McCroskey Jan 1978 166 p refs POINT OF VIEW [DIE BEDEUTUNG STRUKTURELLEft (NASA-TP-1100, A-7096) Avail NTIS HCA08/MFA01 CSCL NICHTLINEARITAETEN AUS DER SIGHT DER STRUKTUR- 01A DYNAMIK UND AEROELASTIK] The flow over a NACA 0012 airfoil undergoing large E Breitbach In its Contrib to Steady and Unsteady Aerodyn oscillations in pitch was experimentally studied at a Reynolds 10 Aug 1977 p 7-19 refs In GERMAN number of 2 5 million and over a range of frequencies and amplitudes Hot-wire probes and surface-pressure transducers were Avail NTIS HC A13/MF A01, DFVLR Cologne DM 107.30 used to clarify the role of the laminar separation bubble, to deline- The effects of structure-dependent nonlmeanties on the ate the growth and shedding of the stall vortex and to quantify the dynamic behavior of aircraft structures were investigated, and resultant aerodynamic loads In addition to the pressure their significance for flutter stability analysis and for solution of distributions and normal force and pitching moment data that general dynamic response problems considered Some measure- have often been obtained in previous investigations, estimates ment and analytical compuation problems resulting from structural of the unsteady drag force during dynamic stall have been derived nonlmeanties, and methods for resolving them, are discussed from the surface pressure measurements Special characteristics Physical relations are explained using an example of rudder of the pressure response, which are symptomatic of the occurrence mechanism nonlmeanties in manually controlled aircraft ESA and relative severity of moment stall, have also been examined Author N78-17006| Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt, Goettmgen (West Germany) Inst fuer N78-17O02*# Kansas Umv Center for Research. Inc Lawrence Aeroelastik Flight Research Lab THE STALL PROBLEM [ZU DEM PROBLEM DES STALL] MINIMUM INDUCED DRAG CONFIGURATIONS WITH JET P Bublitz In its Contrib to Steady and Unsteady Aerodyn INTERACTION 10 Aug 1977 p 21-32 refs In GERMAN Jenn Louh Pao and C Edward Ian Feb 1978 166 p refs (Grant NsG-1139) Avail NTIS HC A13/MF A01 DFVLR Cologne DM 107.30 (NASA-CR-155929 CRINC-FRL-281-2) Avail NTIS An extensive literature study concerning the analysis of the HC A08/MF A01 CSCL 01A complicated phenomena occurring at aerodynamic stalling is A theoretical method is presented for determining the reported The findings of this study show that the potential theory optimum camber shape and twist distribution for the minimum method of analysis indicates the correct tendency, but that the induced drag in the wing-alone case without prescribing the separation phenomenon and the vortex formation at large angles span loading shape The same method was applied to find the need further exploration using different methods ESA corresponding minimum induced drag configuration with the upper-surface-blowing jet Lan's quasi-vortex-lattice method and his wing-jet interaction theory were used Comparison of the N78-17O07# Deutsche Forschungs- und Versuchsanstalt fuer predicted results with another theoretical method shows good Luft- und Raumfahrt, Goettmgen (West Germany) Inst fuer agreement for configurations without the flowing jet More Aeroelastik applicable experimental data with blowing jets are needed to UNSTEADY AERODYNAMIC FORCES ON HARMONICALLY establish the accuracy of the theory Author OSCILLATING POINTED CIRCULAR CONICAL SHELLS WITH SMALL APERTURE ANGLE [INSTATIONAERE N78-17003I Lockheed Missiles and Space Co, Palo Alto. Calif LUFTKRAEFTE AN HARMONISCH SCHWINGENDEN OUTLINE OF AEROELASTIC PHENOMENA SPITZEN KREISKEGELSCHALEN MIT KLEINEM OEF- A S Volmir [1978] 10 p Transl into ENGLISH from the FNUNGSWINKEL] book "Obolochki v Potoke Zhidkosti i Gaza Zadachi Aerouprugo- H Foersching and K-L Chao In its Contrib to Steady and sti' Moscow. Nauka Press, 1976 p 70-81 Unsteady Aerodyn 10 Aug 1977 p 33-48 refs In GERMAN Avail NTIS HC A02/MF A01. National Translation Center John Crerar Library Chicago Illinois 60616 Avail NTIS HC A13/MF A01 DFVLR Cologne DM 107.30 Aeroelastic processes were examined in regard to their effect The analytical relations for the calculations were derived from of deformation on aircraft wings empennage fuselage and control the slender body theory Numerical calculations were carried out organs A classification is provided of aeroelastic phenomena, for some typical examples and results compared with those of and the concepts of divergence classical flutter panel flutter, the piston theory ESA stalling flutter aeolian vibrations galloping, buffeting, shaking, and washing are differentiated Diagrams denoting aeroelasticity. aerothermoelectricity and aeroautoelasticity illustrate factors of aaroelastic strain B LP N78-17008jjl Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt, Goettmgen (West Germany) Inst fuer N78-17004jjf Deutsche Forschungs- und Versuchsanstalt tuer Aeroelastik Luft- und Raumfahrt. Goettmgen (West Germany) Inst fuer THE INTERFERENCE PROBLEM OF THE OSCILLATING Stroemungsmechanik FUSELAGE NEAR GROUND [DAS INTERFERENZPMOBLEM CONTRIBUTIONS TO STEADY AND UNSTEADY AERODY- DES SCHWINGENDEN RUMPFES IN BODENNAEHE] NAMICS W Geissler In its Contrib to Steady and Unsteady Aerodyn F W Riegels, ed and O Lawaczeck. ed 10 Aug 1977 10 Aug 1977 p 49-60 refs In GERMAN 282 p refs Partly in ENGLISH and partly in GERMAN. ENGLISH summary Avail NTIS HC A13/MF A01 DFVLR Cologne DM 107.30 (DLR-FB-77-34) Avail NTIS HCA13/MFA01. DFVLR Cologne A numerical method is described for calculation of the steady DM 107.30 and unsteady pressure distributions on an axisymmetric body Topics discussed are missile aerodynamics, flow separation near ground The method operates according to the singularity on wings and cascades and its control, transonic similarity for method with a continuous surface coverage of harmonically real gases in cryogenic wind tunnel models, unsteady forces pulsating sources and sinks The ground effect is accounted for and pressure distributions, acoustic problems in gas turbine power by the mirror principle, the distance to ground may be selected plants performance of sailing boats, a hybrid wind tunnel concept, freely A stationary angle of attack (measured against the rotation water jets emerging in vacuum (Spacelab). and neutron sources axis) and several oscillation modes can be taken into consideration for fusion reactor materials tests Results are partly compared with measurements ESA

204 N78-17O34

N78-17012# Deutsche Forschungs- und Versuchsanstalt fuer Dec 1977 100 p refs Luft- und Raumfahrt Goettingen (West Germany) Inst fuer (AD-A047921 AEDC-TR-77-73) Avail NTIS Stroemungsmechanik HC A05/MF A01 CSCL 20/4 EFFECT OF SEPARATION BUBBLES ON THE LIFT OF WING An experimental investigation of the effects of free-stream PROFILES [UEBER DEN EINFLUSS VON ABLOESEBLASEN disturbances on the development of a turbulent boundary layer AUF DEN AUFTRIEB VON TRAQFLUEGELPROFILEN] is described The data obtained at a free-stream Mach number K Jacob In its Contnb to Steady and Unsteady Aerodyn of 0 5 indicated (1) compared to the baseline acoustic 10 Aug 1977 p 111-123 refs In GERMAN disturbances of 133 db acoustic disturbances of up to 150 db did not significantly alter the turbulent boundary-layer skin friction, Avail NTIS HC A13/MF A01. DFVLR Cologne DM 10730 displacement thickness or momentum thickness and (2) compared The problem of high lift behavior of wing profiles as a to the baseline vortical disturbances of 0 5 percent of the function of profile shape and Reynolds number is dealt with free-stream velocity vortical disturbances of one percent of the The case of the combined occurrence of trailing edge separation free-stream velocity considerably altered the boundary-layer skin and a short laminar turbulent separation bubble was examined, friction displacement thickness and momentum thickness as and a method developed for overall flow calculation Empirical well as their growth rates Author (GRA) criteria and relationships were used for approximative consideration of the bubble Maximum lift calculations earned out for two profiles are in good agreement with measurements ESA N78-17028$ Nielsen Engineering and Research Inc Mountain View Calif FURTHER STUDIES OF AERODYNAMIC LOADS AT SPIN N78-17020# Deutsche Forschungs- und Versuchsanstalt fuer ENTRY Annual Report. 1 May 1976 - 1 May 1977 Luft- und Raumfahrt Goettingen (West Germany) Inst fuer Selden B Spangler and Michael R Mendenhall 30 Jun 1977 Aeroelastik 161 p refs UNSTEADY PRESSURE DISTRIBUTION MEASUREMENTS (Contract N00014-74-C-0344, NR Proj 212-225 AT TWO TRAPEZOIDAL WINGS WITH UNIT ASPECT RATIO RF41411801) [INSTATIONAERE DRUCKVERTEILUNGSMESSUNGEN AN (AD-A047952 NEAR-TR-141 ONR-CR212-225-3 AR-3) Avail ZWEI TRAPEZFLUEGELN DER STRECKUNG EINS] NTIS HC A08/MF A01 CSCL 20/4 E Schmidt In its Contnb to Steady and Unsteady Aerodyn As part of a continuing investigation of the aerodynamic 10 Aug 1977 p 227-242 refs In GERMAN loads on a fighter-bomber aircraft at spin departure, a coordinated analytical and experimental program was undertaken on vortex Avail NTIS HC A13/MF A01. DFVLR Cologne DM 107.30 shedding from noncircular nose shapes The asymmetric loads Systematic unsteady pressure distribution measurements were induced by nose vortex shedding at zero and nonzero sideslip carried out on two sharp-edged tapered wings with unit aspect are a primary cause for adverse handling qualities at high angles ratio and tapenng lambda = 1/8 and 1/2 (symmetric-circular of attack A theoretical analysis for vortex shedding from profile, reference wing depth 1 m) A harmonic longitudinal low noncircular nose shapes at combined angles of attack and sideslip amplitude motion at frequencies from 2 5 to 9 4 Hz was was developed Boundary layer separation is predicted in order superimposed for angles of attack from 0 to 18 deg The flow to determine the rate of shedding of vorticity Comparisons with velocity was 60 m/sec maximum Some characteristic plots are separation data on two dimensional cylinders and with measured presented which show considerable angle of attack effects upon loads and flow field velocities in the wake for inclined ogive- the unsteady pressure distribution of slender wings The cylinders give reasonable agreement Tests were conducted in measurements agree with potential theory panel method the V/STOL tunnel at NASA Langley Research Center and the calculations for zero angle of attack ESA Nielsen Engineering - Research water tunnel on a fighter model and typical fighter nose shapes GRA

N78-17025# Grumman Aerospace Corp Bethpage NY Research Dept N78-17029$ European Space Agency Pans (France) INVESTIGATION OF VTOL UPWASH FLOWS FORMED BY A NUMERICAL METHOD FOR CALCULATING THE TWO IMPINGING JETS UNSTEADY AERODYNAMIC PRESSURE DISTRIBUTION Richard C Jenkins and William G Hill Jr Nov 1977 87 p ON HARMONICALLY OSCILLATING WINGS WITH CON- refs TROL SURFACES IN SUBSONIC FLOW THEORY AND (AD-A047805 RE-548) Avail NTIS HC A05/MF A01 CSCL RESULTS FOR COMPRESSIBLE FLOW. PART 2 20/4 Wolfgang Geissler Nov 1977 52 p refs Transl into ENGLISH This report presents results of an experimental investigation of 'Em numensches Verfahren zur Berechnung der mstationaeren of the complex flows that occur under a VTOL vehicle operating aerodyn Druckverteilung der harmomsch schwmgenden Tragf- near the ground The effects of geometric and operating laeche mit Ruder in Unterschallstroemung Theone u Ergeb fuer parameters on the upwash flow produced by ground impingement kompressible Stroemung, Teil 2 DFVLR Goettingen West Ger of two parallel subsonic jets have been modeled This flow has Report DLR-FB-77-15 22 Apr 1977 Original report in GERMAN been subdivided into separate modular elements |et impinge- previously announced as N78-14015 Original German report ment wall jet behavior, stagnation line formation and upwash available from DFVLR Cologne DM 25 90 flow field properties Models have been developed and evaluated (ESA-TT-430 DLR-FB-77-15) Avail NTIS HC A04/MF A01 for each of these elements These models can be used in A numerical method to calculate the unsteady pressure and numerical computation methods that have been developed to force distributions on harmonically oscillating three-dimensional predict such ground effects as suckdown and upwash lift on wings with control surfaces in subsonic flow is presented This VTOL aircraft Parameters included in this investigation were jet panel-method is based on the velocity potential and has the velocity, distance from the ground separation distance between advantage that local unsteady lift and moment coefficients jets, relative jet strength impingement angle and nozzle necessary for flutter investigations can be determined in a simple diameter Properties of the upwash were determined by local and sufficient way The numerical method for compressible flow flow measurements above the ground and by ground plane is described in detail and numerous results and comparisons measurements of surface pressure and oil flow patterns GRA with other mothnds and with experimental data are presented Author (ESA)

N78-17026$ ARO Inc Arnold Air Force Station Tenn N78-17034$ Electromagnetic Compatibility Analysis Center. EFFECTS OF ACOUSTIC AND VORTICAL DISTURBANCES Annapolis Md ON THE TURBULENT BOUNDARY LAYER AT FREE- AUTOMATED UHF FREQUENCY ASSIGNMENT SYSTEM STREAM MACH NUMBER 05 Final Report. 1 Jul 1974 FOR FAA AIR TRAFFIC CONTROL COMMUNICATIONS 30 Jun 1976 Final Report

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Thomas Hensler and John Morrow Jun 1977 94 p Prepared range of input phase variations Included also is an analytical in cooperation with IIT Research Inst Annapolis evaluation on the basis of error probability of an algorithm for (Contract DOT-FA70WAI-175) automatic time synchronization of the receiver to the OMEGA (AD-A047847, FAA-RD-77-96 ECAC-PR-77-012) Avail NTIS broadcast format The use of actual OMEGA phase data and HC A05/MF A01 CSCL 17/7 published propagation prediction corrections to determine phase An automated LIHF Frequency Assignment System (UHF-FAS) velocity estimates was discussed Author was developed as a means of providing frequency assignment plans for FAA Air Traffic Control (ATC) UHF communications facilities The UHF-FAS consists of a series of computer programs N78-17041*# National Aeronautics and Space Administration and can be used to investigate the advantages of different Lewis Research Center, Cleveland Ohio frequency assignment strategies (including partial and complete PRELIMINARY STUDY OF PROPULSION SYSTEMS AND assignments), detect assignments that do not meet the FAA AIRPLANE WING PARAMETERS FOR A US NAVY SUB- criterion provide statistical analyses, and plot ATC service SONIC V/STOL AIRCRAFT volumes Author C L Zola L H Fishbach. and J L Allen Feb 1978 42 p refs N78-17035# Lincoln Lab. Mass Inst of Tech , Lexington (NASA-TM-73652, E-9519) Avail NTIS HC A03/MF A01 PROPOSED TECHNICAL CHARACTERISTICS FOR THE CSCL 01C DISCRETE ADDRESS BEACON SYSTEM (DABS) Two V/STOL propulsion concepts were evaluated in a J D Welch and P H Robeck 30 Sep 1977 63 p common aircraft configuration One propulsion system consists (Contracts DOT-FA72WAI-261 F19628-76-C-0002. FAA Pro| of cross coupled turboshaft engines driving variable pitch fans 034-241-012) The other system is a gas coupled combination of turbojet gas (AD-A048246 ATC-71 FAA-RD-77-143) Avail NTIS generators and tip turbine fixed pitch fans Evaluations were HC A04/MF A01 CSCL 17/7 made of endurance at low altitude low speed loiter with equal A detailed performance specification for the DABS transpon- takeoff fuel loads Effects of propulsion system sizing bypass der is provided including specifications on transponder receiver ratio and aircraft wing planform parameters were investigated and compared Shaft driven propulsion systems appear to result sensitivity and performance in interference Specifications for a in better overall performance although at higher installed weight proposed digital datalmk interface are included and message and than gas systems Author control fields associated with experimental transponder data applications are defined Guidance material on the performance of an optional transponder antenna diversity scheme is pre- N78-17O42*# National Aeronautics and Space Administration sented Author Washington D C AEROSPATIALE IS READY TO DEVELOP A CONVERTI- PLANE WITH TETHERING ROTORS Jacques Monsset Aug 1977 11 p Transl into ENGLISH N78-17036jjf Lincoln Lab, Mass Inst of Tech Lexington from Air et Cosmos (France) no 662 12 Mar 1977 p 19-22 DEVELOPMENT OF A DISCRETE ADDRESS BEACON Translation was announced as A77-26913 Transl by Transeman- SYSTEM Quarterly Technical Summary. 1 Jul - 30 Sep tics Inc Washington D C 1977 (Contract NASw-2792) 1 Oct 1977 23 p (NASA-TM-75038) Avail NTIS HC A02/MF A01 CSCL01C (Contracts DOT-FA72WAI-261 F19628-76-C-0002, FAA Proj Information on the recent study of the convertiplane is 034-241-012) (AD-A048247. FAA-RD-77-159 QTS-23) Avail NTIS reported The convertiplane was designed to replace the HC A02/MF A01 CSCL 17/7 conventional helicopter Its speed is much faster than that of Analytical studies, laboratory and flight experiments, and the helicopter, it uses less fuel, and can carry up to five passengers software developments supporting the concept feasibility and The discovery of the convertiplane was brought about because performance definition phase of the FAA DABS Program are the helicopter is handicapped by its slow speed and can carry described Topics considered include antenna pattern measure- only a few passengers Author ments on the first of two candidate L-band monopulse antennas (modified hogtrough) design effort on the Calibration and N78 17043# Lockheed Missiles and Space Co Palo Alto Calif Performance Monitor Equipment slated for prototype sensor SUPERELEMENT METHOD OF DESIGNING A HELICOPTER evaluation and the initial stage of validating the performance of FUSELAGE Aircraft Reply and Interference Environment Simulator as 0 M Aksenov and Z I Burman [1978] 6 p refs Transl interfaced with the DABS sensor at DABSEF J M S into ENGLISH from Izv Vyssh Ucheb Zaved Aviats Tekh (USSR) no 2, 1977 p 12-17 Avail NTIS HC A02/MF A01, National Translation Center John Crerar Library, Chicago. Illinois 60616 N78-17037*# Research Triangle Inst Research Triangle Park A method of helicopter fuselage design based on separated N C fuselage substructures known as superelements is developed INVESTIGATION OF NEW TECHNIQUES FOR AIRCRAFT for full-scale fuselages The theory and general algorithm utilizing NAVIGATION USING THE OMEGA NAVIGATION the method of forces are presented B L P Ernest G Baxa Jr Feb 1978 238 p refs (Contract NAS1-14005) (NASA-CR-145303 RTI-4378-1152-F) Avail NTIS N78-17044jjl McDonnell Aircraft Co St Louis. Mo HC A11/MF A01 CSCL 17G STRESS HISTORY SIMULATION VOLUME 2 A USERS An OMEGA navigation receiver with a microprocessor as MANUAL FOR A COMPUTER PROGRAM TO MODIFY the computational component was investigated A version of STRESS HISTORY SIMULATIONS Final Report. May the INTEL 4004 microprocessor macroassembler suitable for use 1975 - Jul 1976 on the CDC-6600 system and development of a FORTRAN IV H T Young F R Foster, and H D Dill Mar 1977 133 p simulator program for the microprocessor was developed refs Supporting studies included development and evaluation of (Contract F33615-75-C-3112) navigation algorithms to generate relative position information (AD-A042785 AFFDL-TR-76-113-Vol-2) Avail NTIS from OMEGA VLF phase measurements Simulation studies were HC A07/MF A01 CSCL 01/3 used to evaluate assumptions made in developing a navigation This report presents a description of a computer program to equation in OMEGA Line of Position (LOP) coordinates In- combine and modify stress history simulations generated by a cluded in the navigation algorithms was a procedure for calculating companion computer program described in Volume I Input random a position in latitude/longitude given an OMEGA LOP fix stress history data sets are combined and modified to create Implementation of a digital phase locked loop (DPLL) was stress spectra variations Each variation is characterized by its evaluated on the basic of phase response characteristics over a mission mix a mission mix consists of a particular order of

206 N78-17050

mission types (Air-to-Air Air-to-Ground and Instrumentation and objectives were met, although several areas of possible improve- Navigation) An example problem is included which demonstrates ment to the model are indicated and discussed Author (GRA) the program output a sequential list of peaks and valleys of the flight by flight spectrum and a summary table of the coupling of the peaks and valleys Both of the computer programs were N78-17048# Advisory Group for Aerospace Research and used in a study of load sequence effects on crack growth Development. Paris (France) summarized in AFFDL-TR-76-112 Effects of Fighter Attack APPLICATIONS OF STRUCTURAL OPTIMIZATION FOR Spectrum on Crack Growth Author (GRA) STRENGTH AND AEROELASTIC DESIGN REQUIRE- MENTS N78-17045# Naval Air Development Center Warmmster Pa Warner Lansing (Grumman Aerospace Corp Bethpage N Y) Aircraft and Crew Systems Technology Directorate Edwin Lerner and Ronald F Taylor (AFFDL) Jan 1978 25 p STATISTICAL REVIEW OF COUNTING ACCELEROMETER refs Presented at the 45th Struct and Mater Panel Meeting. DATA FOR NAVY AND MARINE FLEET AIRCRAFT FROM Voss Norway Sep 1977 1 JANUARY 1962 TO 30 JUNE 1977 Semiannual Summary (AGARD-R-664 ISBN-92-835-1269-3) Avail NTIS Report HC A02/MF A01 Alan M Kaniss 1 Nov 1977 157 p Supersedes report dated The need to design airframe components of minimum weight 1 May 1977 while taking into account both strength and aeroelastic require- (AD-A047857) Avail NTIS HCA08/MFA01 ments has been recognized for some time An historical review CbCL 01, 4 is presented of optimization technology development and a state This report is a specialized summary of normal acceleration of the art survey of methods in use by the U S industry that data recorded by counting accelerometers Data are separated indicate considerable progress was made in automating this aspect by calendar time and mission category Only data reported in of the airframe design process It is concluded that algorithms the counting accelerometer program are included Author (GRA) for addressing strength and flutter are now sufficiently developed for practical use at all levels of design and for addressing other aeroelastic design objectives in the preliminary design stage It N78-17O46# Army Aeromedical Research Lab Fort Pucker is recommended that airframe designers utilize these methods Ala more extensively in future aircraft development programs TOXICOLOGIC GAS EVALUATION OF THE UTILITY Additional effort is needed to extend some of the finite element TACTICAL TRANSPORT AIRCRAFT SYSTEM (UH 60) resizing techniques so that static aeroelastic design objectives Final Report can be treated as effectively as flutter-speed requirements and Richard L Schumaker and Gary D Pollard Jul 1977 13 p additional computer software development is always desirable refs to upgrade analysis and data management capabilities Author (AD-A047801 USAARL-77 18) Avail NTIS HC A02/MF A01 CSCL 01/3 N78-17049# Advisory Group for Aerospace Research and The accumulation of toxic gases in US Army combat and Development Pans (France) combat support aircraft presents a significant hazard for the aircrew in addition to the combat forces and aeromedical evacuation TECHNICAL EVALUATION REPORT ON THE FLIGHT MECHANICS PANEL SYMPOSIUM ON ROTORCRAFT patients being transported The US Army Aeromedical Research DESIGN Laboratory is conducting an on-going evaluation of the cockpit and cabin environment of current and future helicopter and fixed H R Velkoff (Ohio State Umv Columbus) Jan 1978 14 p refs Symp held at NASA Ames Research Center Moffett Field wing aircraft Toxic product accumulation evaluation during actual Calif 16-19 May 1977 flight with weapons firing presents a difficult technicologic challenge This study of toxic gases due to aircraft engine (AGARD-AR-114 ISBN-92-835-1273-1) Avail NTIS HC A02/MF A01 operation and weapons firing demonstrates adequate ventilation The status of rotorcraft design and development the possible for the compounds carbon monoxide nitrogen dioxide, nitric oxide, divergence of the development pattern of military and civil sulfur dioxide and hydrogen cyanide Single samples of hydrogen sulfide demonstrate instantaneous toxic levels Biochemical and helicopters and the possibihtes for greater coordination in the analytical techniques are being refined to further evaluate on-line development of futurp rotarv winq aircraft arp considered Specific in-flight hydrogen sulfide levels in US Army aircraft under actual topics discussed include (1) military requirements and new military combat conditions Author (GRA) rotorcraft 12) civil operations and new civil helicopters (3) rotary wing aircraft research vehicles (4) wind tunnel and flight research (5) common ground for milita- and civil cooperation N78-17O47# Air Force Inst of Tech Wright-Patterson AFB in the development of rotary wing aircraft and (6) coordination Ohio School of Engineering of military and civil requirements and specifications It is A DISCRETE-EVENT DIGITAL SIMULATION MODEL OF THE recommended to seek out ways to maximize common mission F-16 FIRE CONTROL COMPUTER OPERATIONAL FLIGHT and design features to reduce overlapping costs and increase PROGRAM USING SIMSCRIPT 2 5 M.S Thesis production . J M S L R Hanson Dec 1977 108 p refs (AD-A048164 AFIT/GE/MA/77-1) Avail NTIS HC A06/MF A01 CSCL 09/2 N78-170~6b*# "Santa Clara Umv Calif Dept of blectncal In support of a request from the Air Force Avionics Laboratory Engineering and Computer Science a model of the F-16 Fire Control Computer (FCC) Operational AIRCRAFT ATTITUDE MEASUREMENT USING A VECTOR Flight Program (OFP) was developed The initial specification MAGNETOMETER required that this model allow for possible changes to the rate R Peitila and W R Dunn Jr 1 Dec 1977 170 p refs of accomplishment of various OFP mode-dependent tasks The (Grant NGR-05-017-031) reconfiguration of the input and output tasks and the processing (NASA-CR-155565) Avail NTIS HC A08/MF A01 CSCL reserve were of particular interest In order to determine the 01D most useful approach, the various computer system modeling The feasibility of a vector magnetometer system was relationships are first reviewed Based on the author s background investigated by developing a technique to determine attitude the real world system and the modeling goals a discrete event given magnetic field components Sample calculations are then queue level simulation using SIMSCRIPT 2 5 is selected as the made using the earth s magnetic field data acquired during actual desired approach The basic features of the F-16 FCC and the flight conditions Results of these calculations are compared OFP are discussed and a description of the task movement in graphically with measured attitude data acquired simultaneously the system is provided This description is used to detail the with the magnetic data The role and possible implementation various rate groups and their member tasks The model is verified of various reference angles are discussed along with other pertinent by comparison against data derived from an actual system run considerations Finally it is concluded that the earth s magnetic and a statistical analysis provided by the OFP manufacturer field as measured by modern vector magnetometers can play a The verification process showed that all the original design significant role in attitude control systems Author

207 N78-1705M

N78 17051*# Santa Clara Univ Calif Oept of Electrical noise propagation and also permited reduced nozzle exhaust Engineering and Computer Science velocity for reduced shear noise In another embodiment, airflow EVALUATION OF STOL NAVIGATION AVIONICS Final was increased by means of a fan blade pitch change or speed Technical Report increase while the fan nozzle area was increased yielding both W R Dunn Jr 1 Dec 1977 276 p refs a net reduction in engine thrust and noise (Grant NGR-05-017-031) Official Gazette of the U S Patent Office (NASA-CR-155566) Avail NTIS HC A13/MF A01 CSCL 01D N78-17067*jjl National Aeronautics and Space Administration Research projects including work on a vector magnetometer Langley Research Center, Langley Station, Va for aircraft attitude measurement are summarized The earth s INTERNAL PERFORMANCE PREDICTIONS FOR LANGLEY electric field phenomena was investigated in its application to SCRAMJET ENGINE MODULE aircraft control and navigation Research on electronic aircraft S Z Pmckney Jan 1978 81 p refs cabin noise suppression is reviewed and strapdown mertial (NASA-TM-X-74038) Avail NTIS HC A05/MF A01 CSCL reference unit technical support is outlined B L P 21E A one dimensional theoretical method for the prediction of the internal performance of a scramiet engine is presented The N78-17053*# National Aeronautics and Space Administration, effects of changes in vehicle forebody flow parameters and Washington D C characteristics on predicted thrust for the scramjet engine were EXPERIMENTAL TESTING OF FLIGHT CONTROL HEAD UP evaluated using this method and results are presented A DISPLAYS theoretical evaluation of the effects of changes in the scramjet M Berjal Jan 1978 15 p Transl into ENGLISH of Experimenta- engine s internal parameters is also presented Theoretical internal tion de Dispositifs de Pilotage Tete Haute" Rept Vol 2 Editions performance predictions in terms of thrust coefficient and specific Chiron Electron and Civil Aviation Intern Conf (Pans) 1972 impulse are provided for the scramjet engine for free stream p 1033-1046 Translation was announced as A73-32508 Transl Mach numbers of 5 6 and 7 free stream dynamic pressure of by Kanner (Leo) Associates, Redwood City. Calif 23.940 N/sq m forebody surface angles of 4 6 deg to 14 6 deg (Contract NASw-2790) and fuel equivalence ratio of 1 0 Author (NASA-TM-75205) Avail NTIS HC A02/MF A01 CSCL01D Experiments and tests with 4 generations of head up displays N78-17058*l Pratt and Whitney Aircraft West Palm Beach was reported The CV 191. based on fighter aircraft gunsights Fla Government Products Div was replaced by the CV 193 with several improvements The ANALYTICAL STUDY OF THERMAL BARRIER COATED CV 193 V incorporates the velocity vector reference mark FIRST-STAGE BLADES IN AN F100 ENGINE Progress eliminates much other data clusters the rest in a small area of Report. 1 Sep 1977 - 31 Jan 1978 the visual field and is seen together with the outside landscape D E Andress Feb 1978 27 p The CV 91 presents only velocity vector and total angle of descent (Contract NAS3-21032) data, used when runway and horizon are visible TC 121 displays (NASA-CR-135359 FR-9609) Avail NTIS HC A03/MF A01 an outline of the runway and can be used in visual and CSCL 21E instrument approaches Author Heat transfer and stress analyses were performed on two sections of a thermal barrier coated (TBC) F100 1st-stage turbine blade Results of the analyses indicate that the TBC on the N78-17064 Tennessee Univ , Knoxville leading edges of both sections experience the highest elastic AN ANALYSIS OF THE INFLUENCE OF SOME EXTERNAL strain ranges and these occur during transient engine operation DISTURBANCES ON THE AERODYNAMIC STABILITY OF Further study is recommended to determine the effects of TURBINE ENGINE AXIAL FLOW FANS AND COMPRES- plastic deformation (creep) and creep-fatigue interaction on coating SORS PhD Thesis life Author William F Kimzey 1977 287 p Avail Univ Microfilms Order No 77-27675 N78-17059*# National Aeronautics and Space Administration The development of a one-dimensional, time-dependent Lewis Research Center. Cleveland Ohio mathematical compressor model for analysis of planar disturbances CERAMICS IN GAS TURBINE POWDER AND PROCESS and an extension of the model to a three-dimensional form for CHARACTERIZATION analysis of distortion was accomplished Compressor stage force Sunil Dutta 1977 16 p refs Presented at the Conf on and shaft work were determined from empirical stage characteris- Composites and Advanced Maters Cocoa Beach Fla 17-19 Jan tics with corrections made for unsteady cascade airfoil aerodynam- 1977, Sponsored by Am Ceramic Soc ics Example problems solved using the one-dimensional analysis (NASA-TM-73875 E-9475) Avail NTIS HC A02/MF A01 include determination of the steady-state state stability limit CSCL 21E with undisturbed flow instability caused by oscillating planar Some of the intrinsic properties of various forms of Si3N4 inflow and dynamic response of a compressor to oscillating and SiC are listed and limitations of such materials availability entry pressure Example problems solved using the distortion are pointed out The essential features/parameters to characterize model include stability limit line reduction caused by a combined a batch of powder are discussed including the standard techniques radial and circumferential pressure distortion and pure pressure for such characterization In process characterization parameters and temperature circumferential distortion effects Dissert Abstr in sintering reaction sintering and hot pressing processes are discussed including the factors responsible for strength limitations N78-17055* National Aeronautics and Space Administration in ceramic bodies Significant improvements in material properties Lewis Research Center Cleveland Ohio can be achieved by reducing or eliminating the strength limiting VARIABLE THRUST NOZZLE FOR QUIET TURBOFAN factors with consistent powder and process characterization ENGINE AND METHOD OF OPERATING SAME Patent along with process control Author Arthur P Adamson inventor (to NASA) (GE Cincinnati Ohio) N78-17060*]j' National Aeronautics and Space Administration Issued 17 Jan 1978 7 p Filed 29 May 1975 Sponsored by Lewis Research Center Cleveland Ohio NASA GENERAL AVIATION ENERGY-CONSERVATION RE- (NASA-Case-LEW-12317 -1 US-Patent-4 068.469. SEARCH PROGRAMS AT NASA-LEWIS RESEARCH CEN- US-Patent-Appl-SN-581750 US-Patent-Class-60-204 TER . _ . _ US-Patent-Class-60-226R. US-Patent-Class-60-271) Avail US Edward A Willis 1977 26 p refs Presented at the Cont on Patent Office CSCL 21E Energy Conserv m Gen Aviation Kalamazoo Mich 10-11 Oct An improved method of operating a gas turbine engine is 1977 sponsored by Western Michigan Univ presented wherein engine-generated noise is maintained at a (NASA-TM-73884) Avail NTIS HC A03/MF A01 CSCL 21E reduced level during reduced thrust operation Fan speed was The major thrust of NASA s nonturbine general aviation engine maintained at a constant level while fan nozzle area was increased programs is directed toward (1) reduced specific fuel consumption This maintained high inlet Mach numbers for reduced forward (2) improved fuel tolerance and (3) emission reduction Current

208 N78-17067 and planned future programs in such areas as lean operation, N78-17064*# Pratt and Whitney Aircraft Group East Hartford improved fuel management advanced cooling techniques and Conn Commercial Products Div advanced engine concepts are described These are expected to METHOD OF FAN SOUND MODE STRUCTURE DETERMI- lay the technology base by the mid to latter 1980s, for engines NATION Final Report whose total fuel costs are as much as 30% lower than today's G F Pickett. T G Sofrm and R W Wells Aug 1977 160 p conventional engines Author refs (Contract NAS3-20047) (NASA-CR-135293 PWA-5554-3) Avail NTIS N78-17061*# Raman Aeronautics Research and Engineering, HC A08/MF A01 CSCL 21E Inc Palo Alto Calif A method for the determination of fan sound mode structure AN ANALYSIS OF THE ROTOR BLADE STRESSES OF THE in the Inlet of turbofan engines using in-duct acoustic pressure THREE STAGE COMPRESSOR OF THE AMES RESEARCH measurements is presented The method is based on the CENTER 11- BY 11-FOOT TRANSONIC WIND TUNNEL Final simultaneous solution of a set of equations whose unknowns Report are modal amplitude and phase A computer program for the Jules B Dods Jr Nov 1977 147 p refs solution of the equation set was developed An additional computer (Contract NAS2-9112) program was developed which calculates microphone locations (NASA-CR-152083) Avail NTIS HC A07/MF A01 CSCL the use of which results in an equation set that does not give 21E rise to numerical instabilities In addition to the development of The static and dynamic rotor blade stresses of the three a method for determination of coherent modal structure stage compressor were measured Data are presented in terms experimental and analytical approaches are developed for the of total blade stress for the complete operational range of determination of the amplitude frequency spectrum of randomly compressor speeds and tunnel total pressures Modal frequen- generated sound models for use in narrow annulus ducts Two cies and variations with tunnel conditions were measured Phase approaches are defined one based on the use of cross-spectral angles and coherences between various gage combinations are techniques and the other based on the use of an array of also presented Recommendations for improvements are given microphones Author for future rotor blade experimental investigations Author N78-17065'# Pratt and Whitney Aircraft Group East Hartford N78-17O62*# Boemg Co Seattle Wash Conn Commercial Products Div LOW SPEED TEST OF A HIGH-BYPASS-RATIO PROPUL- METHOD OF FAN SOUND MODE STRUCTURE DETERMI- SION SYSTEM WITH AN ASYMMETRIC INLET DESIGNED NATION COMPUTER PROGRAM USER'S MANUAL FOR A TILT-NACELLE V/STOL AIRPLANE MICROPHONE LOCATION PROGRAM J Syberg Jan 1978 115 p refs G f Pickett. R A Wells and R A Love Aug 1977 72 p (Contract NAS2-9640) refs (Contract NAS3-20047) (NASA-CR-152072 D-180-22888-1) Avail NTIS HC A06/MF A01 CSCL 21 E (NASA-CR-135294. PWA-5554-4) Avail NTIS A large scale model of a lift/cruise fan inlet designed for a HC A04/MF A01 CSCL 21E A computer users manual describing the operation and the tilt nacelle V/STOL airplane was tested with a high bypass ratio turbofan Testing was conducted at low freestream velocities essential features of the microphone location program is presented with inlet angles of attack ranging from 0 deg to 120 deg The The Microphone Location Program determines microphone operating limits for the nacelle were found to be related to inlet locations that ensure accurate and stable results from the equation boundary layer sepa'ation Small separations originating in the system used to calculate modal structures As part of the inlet diffuser cause little or no performance degradation However, computational procedure for the Microphone Location Program, a first-order measure of the stability of the equation system at sufficiently severe freestream conditions the separation changes was indicated by a matrix conditioning number Author abruptly to a lip separation This change is associated with a significant reduction in nacelle net thrust as well as a sharp increase in fan blade vibratory stresses Consequently the onset N78-17066*# Pratt and Whitney Aircraft Group East Hartford of lip separation is regarded as the nacelle operating limit The Conn Commercial Products Div test verified that the asymmetric inlet design will provide high METHOD OF FAN SOUND MODE STRUCTURE DETERMI- performance and stable operation at the design forward speed NATION COMPUTER PROGRAM USER'S MANUAL and angle of attack conditions At some of these however, MODAL CALCULATION PROGRAM operation near the lower end of the design inlet airflow range G F Pickett R A Wells and R A Love Aug 1977 74 p is not feasible due to the occurrence of lip separation Author refs (Contract NAS3-20047) N78-17063*# Cincinnati Umv Ohio Dept of Aerospace (NASA-CR-135295 PWA-5554-5) Avail NTIS Engineering HC A04/MF A01 CSCL 21E OPTIMIZATION STUDY FOR HIGH SPEED RADIAL A computer user s manual describing the operation and the TURBINE WITH SPECIAL REFERENCE TO DESIGN essential features of the Modal Calculation Program is presented VARIABLES The modal Calculation Program calculates the amplitude and I Khalil and W Tabakoff Oct 1977 67 p refs Prepared in phase of modal structures by means of acoustic pressure cooperation with Army Air Mobility Research and Development measurements obtained from microphones placed at selected Lab Moffett Field Calif locations within the fan inlet duct In addition the Modal (Contract NAS2-7850) Calculation Program also calculates the first-order errors in the (NASA-CR-152094) Avail NTIS HC A04/MF A01 CSCL modal coefficients that are due to tolerances in microphone 21E location coordinates and inaccuracies in the acoustic pressure Numerical results of a theoretical investigation are presented measurements Author to provide information about the effect of variation of the different design and operating parameters on radial inflow turbine N78-17067# Air Force Inst of Tech Wright-Patterson AFB performance The effects of variations in the mass flow rate Ohio School of Systems and Logistics rotor tip Mach number inlet flow angles number of rotor blades DEVELOPMENT OF COST ESTIMATING RELATIONSHIPS =ind huh to shroud radius ratio nn the internal fluid dynamics FOR AIRCRAFT JET CORE-ENGINE OVERHAUL COSTS of turbine rotors, were investigated A procedure to estimate the M S Thesis flow deviation angles at the turbine exit is also presented and Robert A Bregiio Jr Sep 1977 160 p refs used to examine the influence of the operating conditions and (AD-A047667. AFIT-LSSR-31-77B) Avail NTIS the rotor geometrical configuration on these deviations The HC A08/MF A01 CSCL 21/5 significance of the results obtained is discussed with respect to Cost estimation is a wide open area within the Department improved turbine performance Author of Defense and accurate cost estimating models are a valuable

209 N78-17068

tool in the life cycle costing of a weapon system This research N78-17071| Royal Aircraft Establishment. Farnborough effort utilized multiple linear regression analysis to develop (England) parametric cost models or cost estimating relationships (CERs) INFLUENCE OF GUST MODELLING ON THE IDENTIFICA- for jet engine depot overhaul costs Both engine operating TION OF THE DERIVATIVES OF THE LONGITUDINAL parameters e g turbine inlet temperature, RPM, etc . and engine MOTION OF AN AIRCRAFT physical characteristics, e g , length, weight etc were considered Gerd Schulz Oct 1977 34 p refs Transl into ENGLISH as probable cost drivers Extensive analysis was performed to from report DLR-FB 76-63 (West Germany), 1976, DFVLR, determine the reliability of the data base The major finding of Oberpfaffenhofen 34 p this study was that models can be developed with acceptable (RAE- Lib-Trans-1944, BR61071) Avail NTIS explanatory power with respect to variation in the data base, HC A03/MF A01 using data of questionable reliability Thus a model developed The influence of stochastic modelling of horizontal and vertical should not be accepted on the basis of explanatory power alone gusts on the maximum likelihood identification of derivatives of but should be tested further to determine its utility as a cost the longitudinal motion of the HFB-320 aircraft was investigated estimator Author (GRA) Several different modellings of the power spectral densities of the gusts were considered It was shown that the outputs are more influenced than the estimates of the derivatives The best N78-17O68# ARO, Inc , Arnold Air Force Station. Tenn curve fit occurred for modelling of the power spectral densities OPTICAL MEASUREMENTS OF NO AND NO SUB 2 IN of the gust by a first order Gauss-Markov process Author THE EXHAUST OF AN F101-GE 100 ENGINE AT SIMU- LATED ALTITUDES Final Report. 12 Jan 1975 - 1 Apr 1977 J D Few AEDC Dec 1977 26 p refs (AD-A047882 ARO-ETF-TR-77-42 AEDC-TR-77-75) Avail NTIS HC A03/MF A01 CSCL 21/2 N78-17072# United Technologies Corp Stratford, Conn Measurements of nitric oxide (NO) and nitrogen dioxide (N02) Sikorsky Aircraft Div concentrations were made in the exhaust of an F101-GE-100 PRELIMINARY DESIGN STUDY OF AN INTEGRATED TAIL engine using ultraviolet (UV) spectral absorption techniques The ROTOR SERVO POWER MODULE Final Report measurements were made at a station 102 cm downstream of Joseph R Maciolek and Karl Walhscheck Sep 1977 165 p the engine nozzle exit The NO measurements were made at refs two engine power settings, intermediate and maximum afterburn- (Contract DAAJ02-76-C-0056) ing the N02 measurement was made only at intermediate power (AD-A047678, SER-50798, USAAMRDL-TR-77-20) Avail The Ime-of-sight absorption measurements through the axisym- NTIS HC A08/MF A01 CSCL 01/3 metnc exhaust stream were converted to local values of concentra- The purpose of the work performed was to determine the tion via an iterative radial inversion computation These in situ feasibility of generating the hydraulic power required to control measurements are compared to NO sub x concentrator! values the tail rotor pitch of a utility helicopter by locating tail-rotor- obtained by conventional probe sampling techniques using a driven hydraulic supply systems within the tail rotor servo This chemilummescent analyzer Author (GRA) relocation of the hydraulic supply system would eliminate the weight, the cost and the excessive vulnerability of the long hydraulic lines in conventional servo systems Using the YUH-60 as a design subject, a preliminary design of an integrated servo N78-17O69# Avco Lycommg Oiv, Stratford Conn power module with electrical (fly-by-wire) inputs was performed ADVANCED SCAVENGE SYSTEMS FOR AN INTEGRATED This study confirms the advantages of generating the hydraulic ENGINE INLET PARTICLE SEPARATOR Final Report, power at the tail rotor gearbox When combined with a 21 Mar 1975 - 21 Mar 1977 fly-by-wire controller the weight saving for a UTTAS design Michael J Zoccoli Sep 1977 200 p refs would be the order of 10 Ibs Compared with the current (Contract DAAJ02-75-C-0026) conventional system, the MTBF of the system would increase (AD-A047872 LYC-77-26. USAAMRDL-TR-77-26) Avail by a 7 to 1 factor Production cost savings could be almost NTIS HC A09/MF A01 CSCL 21/5 $2000 per aircraft GRA In designing a device which scavenges the gas turbine engine integral particle separator, the fundamental problem is one of providing primarily a durable design that is practical in other important aspects which include, but is not limited to power consumption cost physical size and noise An advanced scavenge system for an integrated engine inlet protection system was N78-17073# Air Force Inst of Tech, Wright-Patterson AFB. developed to demonstrate a 50-hour operational capability at a Ohio specified minimum performance level in the severe erosion AIRCRAFT COMPENSATOR DESIGN METHODS environment typical of conditions at the exit from the engine MS Thews particle separator Several alternative configurations were studied, Tom Lance Riggs. Jr Jun 1977 133 p refs two were selected for detailed design and experimental evalua- (AD-A047814, AFIT-CI-77-15) Avail NTIS HC A07/MF A01 tion GRA CSCL 20/4 In this paper methods using linear analysis are presented for the design of longitudinal flight compensators The compensa- N78-17070*# National Aeronautics and Space Administration tors employ state feedback to force the aircraft to respond in Langley Research Center Langley Station Va the desired manner The design process involves analysis of the FILTERING TECHNIQUE BASED ON HIGH-FREQUENCY uncompensated aircraft, construction of a model which has the PLANT MODELING FOR HIGH-GAIN CONTROL Patent desired response, and two algorithms for designing the compensa- Application tor A method is presented for contriving the desired model Frank R Niesson and John F Garren Jr inventors (to NASA) from handling qualities performance criteria The method is Filed 8 Dec 1977 14 p straightforward and results in the exact desired short period (NASA-Case-LAR-12215-1. US-Patent-Appl-SN-858762) Avail response however, the phugoid (long period) response is less NTIS HC A02/MF A01 CSCL 01C predictable The compensator design algorithms are easily An aircraft control system which utilized feedback motion implemented into computer programs The algorithms require a sensors to generate a control signal to control the aircraft is minimum of human/computer interaction and solutions are illustrated The use of a complementary filter permitted a assured for controllable systems Compensators for two aircraft substantial increase in frequency bandwidth due to the simulta- are designed to show the techniques oresented In both examples neous reduction in noise amplification and control limit cycle the compensated system response is exactly the same as the tendencies NASA model response Author (GRA)

210 N78-17080

N78-1707*# Advisory Group for Aerospace Research and N78-17078$ Stanford Research Inst Menlo Park Calif Development. Paris (France) PILOTED FLIGHT SIMULATOR STUDY OF LOW-LEVEL AN INTRODUCTION TO THE PROBLEM OF DYNAMIC WIND SHEAR. PHASE 1 Interim Report. Jun 1975 - Jul. STRUCTURAL DAMPING 1976 Paolo Santini (Rome Univ), Antonio Castellani (Rome Umv) Walter B Gartner and A Charles McTee May 1977 72 p and Alfonso Nappi (Rome Univ ) Jan 1978 24 p refs Presented refs at the 45th Struct and Mater Panel Meeting Voss. Norway. (Contract DOT-FA75WA-3650. SRI Pro| 4364) Sep 1977 (AD-A047985. FAA-RD-77-166) Avail NTIS (AGARD-R-663. ISBN-92-835-1268-5) Avail NTIS HC A04/MF A01 CSCL 01/4 HC A02/MF A01 A piloted flight simulation was conducted to evaluate the Major topics in the area of dynamic damping are described need for improved cockpit displays and procedures for aiding A list of typical problems where damping is of primary importance airline pilots in anticipating and coping with the effects of low-level is provided Typical structural components are considered and a wind shear Pilot and aircraft response to the shear encounter brief account on the effect of materials is given Mathematical under 'baseline conditions was determined using existing models and intermodal coupling are also examined and the cockpit displays and approach management procedures, and the extreme difficulty of obtaining reasonably accurate information improvement that might be realized from various ways of from them is emphasized Possible philosophies of ground tests augmenting the information available to the pilot for wind-shear and flight tests are discussed Author detection and flight control was evaluated The results indicate that pilots would not be able to successfully cope with the N78-17076$ Advisory Group for Aerospace Research and more severe frontal and thunderstorm shears using existing flight Development, Pans (France) instruments and procedures All of the aiding concepts evaluated TECHNICAL EVALUATION REPORT ON THE AVIONICS provided some useful information for alerting the pilot to a PANEL/GUIDANCE AND CONTROL PANEL JOINT SYM- potential shear and for indicating the effects of the shear during POSIUM ON AVIONICS/GUIDANCE AND CONTROL FOR the encounter However pilot preferences were strongly in favor REMOTELY PILOTED VEHICLES (RPV«) of a display of ground speed integrated with the airspeed Morns A Ostgaard Dec 1977 14 p Symp held at Florence, indicator Author 3-6 Oct 1976 (AGARD-AR-113 ISBN-92-835-1264-2) Avail NTIS HC A02/MF A01 N78-17079jjl Naval Air Propulsion Test Center, Trenton NJ A symposium was held to examine the state-of-the-art in Propulsion Technology and Praiect Engineering Dept the field of avionics and guidance control related to the problems EVALUATION OF THE EXTENDED USE OF FERROCENE of remotely piloted vehicles Some of the following topics were FOR TEST CELL SMOKE ABATEMENT ENGINE AND discussed (1) Electro-optical sensors and their adverse weather ENVIRONMENTAL TEST RESULTS Interim Report capability limitations (2) Experimental testing of various types Anthony F Klarman Oct 1977 126 p refs of sensors (3) Sensor requirements for medium range surveillance (AD-A047659. NAPTC-PE-110) Avail NTIS and target acquisition systems and (4) Data processing data HC A07/MF A01 CSCL 21/4 display systems B B Results of a test program to evaluate the feasibility of utilizing the smoke suppressant fuel additive, ferrocene during post overhaul performance checks of gas turbine engines at Naval Air Rework Facilities (NARFs) and other lower level mainte- N78-17076$ Advisory Group for Aerospace Research and nance test facilities to reduce test cell exhaust smoke plumes to. Development Paris (France) environmentally acceptable levels are presented This test program EFFECTS OF STRUCTURAL NON-LINEARITIES ON AIR- was conducted on the following gas turbine engines J52-P-6B. CRAFT VIBRATION AND FLUTTER J57-P-10, J79-GE-8D, TF30-P-6C and TF41-A-2A E Breitbach (Aerodynamische Versuchsanstalt Goettingen. West Author (GRA) Ger) Jan 1978 17 p refs Presented at the 45th Struct and Mater Panel Meeting. Voss Norway Sep 1977 (AGARD-R-665 ISBN-92-835-1270-7) Avail NTIS HC A02/MF A01 N78-17080$ Vehicle Systems Development Corp . Upland, Calif The physical sources of various types of nonlmeanties were HELICOPTER GROUND MOBILITY SYSTEM (HGMS) examined and their influence on the different parts of the flutter CONCEPT FORMULATION AND SELECTION Final Technical clearance process was investigated Methods which permit Report. 29 Jun. 1976 - 20 Jun 1977 quantitative solutions of nonlinear aeroelastic problems were also R W Forsyth and J P Forsyth Sep 1977 94 p refs surveyed Author (Contract DAAJ02-76-C-0037 DA Proj 1F2-62209-AH-76) (AD-A047507, USAAMRDL-TH-77-35) Avail NTIS HC A05/MF A01 CSCL 01/3 The first task resulted in the definition of some 30 ground N78-17077# Dunlay (William J . Jr) Bala Cynwyd. Pa mobility system concepts, including wheeled and tracked, AIRPORT IMPROVEMENT TASK FORCE DELAY STUDY frame-type transporters, auxiliary wheel systems all-wheel-dnve DELAY MODEL VALIDATION PLAN Final Report. 26 Jul. - prime movers and two-element, articulated mover systems 18 Aug 1977 designed for load transfer from the helicopter In Task 2 the William J Dunlay Jr Washington FAA Aug 1977 55 p contractor developed evaluation criteria and conducted a refs preliminary analysis of the suitability of the various concepts for (FAA Order W1-77-2412-1) the mission of providing local ground mobility for the AAH and (AD-A048112 FAA-EM-77-17) Avail NTIS UTTAS helicopters in unimproved terrain The third task involved HC A04/MF A01 CSCL 01/5 the preparation of prototype design layouts of the selected concept, A validation plan was oresented for an airside simulation a four-wheeled two-element articulated prime mover, with model The plan stresses basic principles of validation and inherent provisions for offloading the tail wheel of the helicopter for weight problems associated with comparing simulation model delay transfer and controls for a walking operator With tractive effort estimates with observable real-world data A methodology was provided by this, the flotation required for the helicopter is achieved proposed that consists of three major steps (1) evaluation of by temporarily attaching tracks on the main landing gear of the helicopter Additionally under Task 3, the contractor prepared model logic inputs, and outputs (2) comparison of model the system specification for the HGMS The program effort was estimates with collected data and (3) a sensitivity analysis of concluded with Task 4 which involved the development of a the delay simulation model A Model Validation Group established concept design and preliminary layout drawings for the adapter to oversee the validation process, was described Suggestions were given on sources of data on airside operations for model unit enabling use of the HGMS with skid-equipped helicopters inputs and for comparisons with model estimates Author GRA

211 N78-17082

N78-17082f Apph-Mation Inc . Orlando. Fla N78-17339*# McDonnell Aircraft Co. St Louis, Mo INSTRUCTOR PILOTS ROLE IN SIMULATION TRAINING. EVALUATION OF A LARGE CAPACITY HEAT PUMP PHASE 2 Final Report. Mar 1976 - May 1977 CONCEPT FOR ACTIVE COOLING OF HYPERSONIC John P Charles Aug 1977 59 p refs AIRCRAFT STRUCTURE (Contract N61339-76-C-0034) L L Pagel and R L Herring Feb 1978 47 p refs (AD-A047919 NAVTRAEQUIPC-76-C-0034-1) Avail NTIS (Contract NAS1-14981) HC A04/MF A01 CSCL 05/9 (NASA-CR-145301) Avail NTIS HC A03/MF A01 CSCL Analyses of Instructor Pilot functions in training pilots using 20D simulation were performed The functions were based on the Results of engineering analyses assessing the conceptual review of current simulation training conducted in the Phase I feasibility of a large capacity heat pump for enhancing active study NAVTRAEQUIPCEN 75-C-0093-1 (AD-A023 546) cooling of hypersonic aircraft structure are presented A unique Feasible allocations of functions were made and modular heat pump arrangement which permits cooling the structure of implementation concepts developed x\ . GRA a Mach 6 transport to aluminum temperatures without the aid \ of thermal shielding is described The selected concept is N78-17084| Naval Weapons SuppbruCenter -Crane, Ind compatible with the use of conventional refrigerants, with Freon AN EXAMINATION OF SELECTED DIGITAL FLIGHT R-11 selected as the preferred refrigerant Condenser tempera- GENERATORS Final Report. May 1974 - Dec 1975 tures were limited to levels compatible with the use of conventional O K Sanders and N L Papke Nov 1977 49 p refs Sponsored refrigerants by incorporating a unique multipass condenser design, by Joint Tech Coordinating Group for Aircraft Survivabihty which extracts mechanical energy from the hydrogen fuel, prior (AD-A047845, JTCG/AS-77-S-001) Avail NTIS to each subsequent pass through the condenser Results show HC A03/MF A01 CSCL 09/2 that it is technically feasible to use a large capacity heat pump This report describes the findings of an investigative analysis in lieu of external shielding Additional analyses are required to of four flightpath generation computer models The four models optimally apply this concept Author (FAIR PASS FLYGEN BLUE MAX and MCEP) are commonly used in the aircraft survivabihty/vulnerability community The first three are primarily fixed-wing models, white MCEP is exclusively N78-17390*# Stem Seal Co. Philadelphia. Pa a rotary-wing flightpath generator All four models were acquired FEASIBILITY STUDY OF NEGATIVE LIFT CIRCUMFEREN- installed tested and analyzed at NWSC (Naval Weapons Support TIAL TYPE SEAL FOR HELICOPTER TRANSMISSIONS Center), Crane, IN Criteria such as capabilities limitations ease E N Goldnng Oct 1977 38 p and economy of use and compatibility with attrition models (Contract NAS3-20598) were considered in the evaluations Author (GRA) (NASA-CR-135302) Avail NTIS HC A03/MF A01 CSCL 11A A new seal concept the negative lift circumferential type seal, was evaluated under simulated helicopter transmission conditions The bore of the circumferential seal contains step type geometry which produces a negative lift that urges the N78-17229*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio sealing segments towards the shaft surface The seal size was a 2 5 inch bore and the test speeds were 7000 and 14,250 rpm ALTERNATIVE AIRCRAFT FUELS J P Longwell (MIT Cambridge) and J Grobman Jun 1977 During the 300 hour test at typical transmission seal pressure 22 p refs Proposed for presentation at 23d Ann Intern Gas (to 2 psig) the leakage was within acceptable limits and generally less than 0 1 cc/hour during the last 150 hours of testing The Turbine Conf, London, Engl, 9-13 Apr 1978 sponsored by wear to the carbon segments during the 300 hours was Am Soc of Mechan Engineers (NASA-TM-73836) Avail NTIS HC A02/MF A01 CSCL 210 negligible Author The efficient utilization of fossil fuels by future jet aircraft may necessitate the broadening of current aviation turbine fuel specifications The most significant changes in specifications would N78-17398# Air Force Flight Dynamics Lab Wright-Patterson be an increased aromatics content and a higher final boiling AFB Ohio point in order to minimize refinery energy consumption and costs INCLUDING FLEET USAGE VARIABILITY IN RELIABILITY These changes would increase the freezing point and might lower ANALYSES FOR BOTH SAFETY AND ECONOMIC LIMIT the thermal stability of the fuel and could cause increased pollutant Final Report. Sep 1976 - Mar 1977 emissions, increased combustor liner temperatures, and poorer Robert L Neulieb Aug 1977 21 p refs ignition characteristics The effects that broadened specification (AD-A047714. AFFDL-TR-77-77) Avail NTIS fuels may have on present-day jet aircraft and engine components HC A02/MF A01 CSCL 14/4 and the technology required to use fuels with broadened Reliability tools have been developed which are capable of specifications are discussed Author determining the probability of failing a given aircraft or the first aircraft in a fleet as a function of time, loading and inspections These methods developed for the entire fleet can easily be extended to include variations in usage across the fleet and to N78-17292 Kansas Univ Lawrence address the concept of economic life Author (GRA) AN INVESTIGATION OF LIGHTNING DAMAGE TO NON- METALLIC COMPOSITE AIRCRAFT MATERIALS AND N78-17558*! National Aeronautics and Space Administration ASSOCIATED PROTECTIVE SYSTEMS Ph D Thesis Lewis Research Center, Cleveland Ohio Steven Ames Lorenz 1977 140 p AUTOMATED METEOROLOGICAL DATA FROM COM- Avail Univ Microfilms Order No 77-29190 MERCIAL AIRCRAFT VIA SATELLITE PRESENT EXPERI- The inherent dangers of operating aircraft equipped with ENCE AND FUTURE IMPLICATIONS nonmetallic components within the natural lightning environment Robert Steinberg 1978 7 p refs Presented at Intern Conf are described A philosophy for simulating the natural lightning on Maritime and Aeron Satellite Commun and Navigation. current waveform is presented and a circuit to produce simulated London. 7-10 Mar 1978 sponsored by Institution of Elec Eng waveforms is proposed A chronicle of the design construction (NASA-TM-73750 E-9323) Avail NTIS HC A02/MF A01 and operation of a simulation facility based on this circuit is CSCL 04B presented with emphasis on design and operational safety aspects A low-cost communications system to provide meteorological A test program using boron/epoxy and graphite/epoxy material data from commercial aircraft, m neat real-time on a fully specimens is outlined Possible applications and modifications automated basis has been developed The complete system for this type of facility are suggested that are commensurate including the low profile antenna and all installation hardware with the future uses of nonmetallic composite materials in aircraft weighs 34 kg The prototype system was installed on a B-747 structures Dissert Abstr aircraft and provided meteorological data (wind angle and velocity.

212 N78-17943

temperature, altitude and position as a function of time) on a grouping of indexes helps locate specific publications by author fully automated basis The results were exceptional This (including contractor authors), contractor organization, contract concept is expected to have important implications for operational number, and report number Author meteorology and airline route forecasting Author N78-17931*# Summerfield Associates Santa Monica Calif N78-17598# World Meteorological Organization Geneva DETERMINATION OF THE FLIGHT EQUIPMENT MAINTE- (Switzerland) NANCE COSTS OF COMMUTER AIRLINES A DIGITAL CONTINUOUSLY UPDATED TWO MINUTE Nov 1977 37 p refs MEAN WINDSPEED INDICATOR FOR USE AT AIRPORTS (NASA Order A-36079-BITS)) G Venugopal and G P Srivastava In its Inst and Methods of (NASA-CR-152069) Avail NTIS HC A03/MF A01 CSCL Observation 1977 p 91-96 refs 05C Labor and materials costs associated with maintaining and Avail NTIS HCA12/MFA01 operating 12 commuter airlines carrying an average of from 42 A digital average wmdspeed measuring equipment tor use to 1 100 passengers daily in a variety of aircraft types were at airports based on the measurement of the total wind run for studied to determine the total direct maintenance cost per flight 2 minute periods continuously updated every 10 seconds is hour for the airframe, engine and avionics and other instru- described The quipment consists of a photoelectric cup anemome- ments The distribution of maintenance costs are analyzed for ter for sensing the wind a computer for computing the mean two carriers one using turboprop aircraft and the other using wmdspeed a programmer to control the computer operations piston engine aircraft A R H and a seven segment numeric indicator to display the information ESA N78-17943# Defense Systems Management School, Fort Belvoir, Va THE PROBLEM OF TECHNOLOGY TRANSFER REAL OR N78-17600# World Meteorological Organization Geneva IMAGINED (Switzerland) Warrer^W Cook May 1977 52 p refs A CURRENT WEATHER INFORMATION DISPLAY SYSTEM FOR USE AT AIRPORTS (AD-A042961I Avail NTIS HC A04/MF A01 CSCL 05/1 G Venugopal and G P Srivastava In its Instr and Methods of This study project report provides an analysis of the process by Observation 1977 p 100-104 which the Air Force transfers or transitions technology from less than major system advanced development projects performed in Avail NTIS HC A12/MF A01 Air Force laboratories to use in operational systems An A description is given of the current weather display system examination of the DoD and Military Departments policies, in use at Indian airports The system consists of conventional procedures and technology base management techniques lead sensors for wind direction, wind speed dew point and air to a description of the factors that tend to camouflage or provide temperature The system electronics comprise an analog roadblocks to the transition process These factors are placed multiplexer, and A/D converter a storage and senahzer unit as into Communications/Motivation Groups and are evaluated for well as the display and power supply ESA their impact on the process Conclusions are reached concerning the Air Force laboratory organizational structure, use of off-the- shelf hardware, contractor independent research and development, N78-17916*# Gellman Research Associates Inc Jenkintown and contract procedures Recommendations discuss documenta- Pa tion, changes in organizational structure, and modification of THE ROLE OF ENGINEERING IN THE FLIGHT EQUIPMENT procurement and contracting procedures Author (GRA) PURCHASING PROCESS Final Report Dec 1977 85 p (Contract NASw-3075) (NASA-CR- 156839) Avail NTIS HC A05/MF A01 CSCL 05A The role of the airline engineering department in the flight equipment acquisition process is examined The data for the study was collected from six airlines The principal findings of the study include (1) engineering activities permeate, but do not dominate the airline flight equipment decision process (2) The principal criterion for the flight equipment acquisition decision is return on investment (3) The principal sources of information for the airline engineering departments in the monitoring process are the manufacturers of equipment Subsidiary information sources include NASA publications and conferences among others and (4) The engineering department is the principal communication channel for technical information Author

N78-17921*+ National Aeronautics and Space Administration Lewis Research Center. Cleveland. Ohio BIBLIOGRAPHY OF LEWIS RESEARCH CENTER TECHNI- CAL CONTRIBUTIONS ANNOUNCED IN 1976 Dec 1977 192 p (NASA-TM-73860. E-9449) Avail NTIS HC A09 CSCL 05B Abstracts of Lewis authored publications and publications resulting from Lewis managed contracts which were announced in the 1976 issues of STAR (Scientific and Technical Aerospace Reports) and IAA (International Aerospace Abstracts) are presented Research reports, journal articles, conference presentations, patents and patent applications, and these are included The arrangement is by NASA subject category Citations indicate report literature (identified by their N-numbers) and the journal and conference presentations (identified by their A-numbers) A

2J3 SUBJECT INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography ISuppl.96) MAY 1978 Typical Subject Index Listing

TAPOBIZBBS Bethod of fan sound mode structure determination -Liquid hydrogen flash vaporizer --- for [BASA-CB-135293] 878-170611 fuel systems ACOOSTIC EBOEAGATIOB f EASA-CASE-LAB-121S9-1 1 S78-11260 Boise transmission into a light aircraft [AIAA EAPEE 78-197] A78-20739 An experimental study of sound diffraction at an airfoil trailing edge REPORT TITLE A78-232M7 NUMBER The location of the ground focus line produced by a supersonic aircraft A78-23Q57 ACOOSTIC IBOPBBIIES The title is used to provide a description of the subject matter When the title is Rind-tunnel investigation of aerodynamic insufficiently descriptive of the document content a title extension is added performance, steady and vibratory leads, surface separated from the title by three hyphens The NASA or AIAA accession number temperatures, and acoustic characteristics of a is included in each entry to assist the user in locating the abstract in the abstract large-scale twin-engine upper-surface blcvn section of this supplement If applicable a report number is also included as an jet-flap configuration [HASA-1H-D-8235] H78-15999 aid in identifying the document ACTOAIOBS Electromechanical flight control actuation [SAE PAPEB 77100"] A78-23838 Research and development of aircraft control actuation systems. The development of a direct drive fly-by-wire flight control system and 1-7 AIBCB1FT evaluation of a force sharing fly-by-mre actuator A-7 ALOFT economic analysis and EBI-EBP test results [AD-A0117283] B78-16065 H78-16816 ADAPTIVE COBIBOI ABLATIVE BOSS COSES Sensor failure detection using analytical redundancy Influence of nosetip shape on boundary layer A78-23862 transition in arc heated jets ADDITIVES [AIAA PAPEB 78-235] A78-20759 Evaluation of the extended use of ferrocene for ABSIB»CTS test cell smoke abatement engine and Bibliography of Lewis Research Center technical environmental test results contributions announced in 1976 [AD-AOt7659] F78-17079 [BASA-TB-73860] U78-17921 ADHESIVE B01DI1G AC GEHEBATOBS Spectrum crack growth in adhesively bonded structure Power conditioning systems for high-power, [ASBE TAPES 77-IIA/BAT-7] A78-23372 airborne, pulsed applications Development of random fatigue data for adhesively A78-23qi2 bonded and veldbonded structures subjected to ACCELEBATIOI (PBISICS) dynamic excitation aircraft structures Characteristics of the jet acceleration cf a flow [ASHE PAPEB 77-BA/BAT-1] A78-23373 to hypersonic speeds AEBOACOOSTICS A78-20953 On some singular acoustic signatures observed in ACCEISBOBBTBES the cockpit of a twin engined jet aircraft The dissection of an aircraft loads spectrum [AIAA SAFES 78-212] A78-20765 produced by peak-ccunting acceleroaeters Semiempirical theory of the generation of discrete [LTB-ST-951] R78-16391 tones ty a supersonic nnderexpanded jet flowing Statistical review of counting accelerometer data over an obstacle for Navy and Hanne fleet aircraft frci 1 A78-21133 January 1962 to 30 June 1977 Becent advances concerning an understanding of [AD-A017857] B78-170H5 sound transmission through engine nozzles and jets iCCBPIABIIITI (DSIB FAPBB 77-008] A78-20137 An analysis of user acceptance and perceived localization and shielding of noise sources usability cf C-1U1A job guides generated by the interaction of free jets with tAD-AOimOl] H78-15992 flat surfaces Evaluation of slimpack style parachute in CT4A [DGLB PAPEB 77-OB9] A78-21Q38 airtrainer aircraft AEBODIBAIIC EBAKBS [AD-A047083] S78-16021 A study of the influence of slits on the A CCO Bid effectiveness of King mechanization and controls An evaluation of the fidelity of notion sinulators in separated flow using a model of hnnan dynanic orientation A78-226II7 tAD-AO«7120] H78-16071 ABBODIIABIC CHABACTEBISTICS ACOOSTIC FATIGUE Computational transonic airfoil design in free air Fatigue crack growth in a pressure-fuselage panel and a wind tunnel A78-226Q9 [AIAA EAPEE 78-103] A78-20685 Development of randoa fatigue data for adhesively Transonic wing analysis using advanced bonded and veldbcnded structures subjected to computational methods dynamic excitation aircraft structures [AIAA PAPEB 78-105] A78-20686 tASBE EAPEB 77-SA/HAT-1] A78-23373 Some applications of a test track for aerodynamic ACODSTIC BBASOBEBEBTS testing Two point correlations cf jet noise [AIAA FAEEB 78-167] A78-20719 A78-23219 EBP noise suppression and aerodynamic penalties Physical analysis of the iipnlsive aspects of Externally Blown Flaps helicopter ncise [AIAA FAPEB 78-2UO] A78-20763 [AD-A039715] H78-16059

A-1 AEBODYH4BIC COKPPICIBSTS SOBJECT IHDEX

Calculation of the flow past a fuselage of The effect of Rhitcomb winglets and other wingtip arbitrary configuration at Ion velocities modifications on wake vortices 478-208115 B78-16988 Approximate method of calculating the lifting Two-dimensional wind tunnel test of an oscillating force and the longitndinal moment of an airfoil rotor airfoil, volume 2 tabulated test results section at low velocities vith allowance for [BASA-CB-2915] B78-16998 viscosity AEBODIBABIC COBtFICIEHTS A78-20849 normal-force and pitching-moment coefficients of Calculation of the flow cf a rarefied gas past a wing-body combinations at very high angles of plate of infinite span attack A78-20857 [4144 EAEEB 78-63] 478-20664 The basic characteristics of the variation of An aerodynamic analysis of several hypersonic aerodynamic parameters in the transition region research airplane concepts from a = 0.2 to 6.0 at hypersonic flew velocities [AIAA IAEEE 78-150] A78-20706 478-20900 Effect of a conical break of delta-wings on the B pproxinate wind-tunnel simulation of the dynamics aerodynamic characteristics of a system conpcsed cf a body with a trailing 478-21084 cable Two-dimensional separated wake modeling and its A78-20902 use to predict maximum section lift coefficient The effect of blnnting the leading edge of a delta [AIAA E4EEE 78-156] 478-22590 wing on its aerodynamic characteristics during AEBODIHAHIC COBFIGOBATIOBS supersonic flight Influence of nosetip shape on boundary layer A78-20920 transition in arc heated jets Supersonic flov near a thin trapezoidal wing [4144 E4PEB 78-235] 478-20759 478-20921 Solving the problem of numerical construction of a Ose of the polynomial nethod to calculate the model of similar rigidity to the initial parameters of the stabilized maneuver of an structure as a problem of gnadratic programming elastic aircraft 478-208611 478-20930 Rearrangement of the flow between a pair of Effect of the thickness cf profile and trailing bodies, one of which is situated in the other's edge on the flow field and the aerodynamic wake, in supersonic flow characteristics of a low-aspect-ratio delta wing 478-20913 at It = 3 Flow visualization in the region of intersection 478-20949 of aerodynamic surfaces Effect of a conical break cf delta-wings en the 478-20951 aerodynamic characteristics Nearly wedge-shaped antisymmetric wing in 478-210814 supersonic flow Hypersonic flov past a conical wing with detached 478-22080 shock wave at the leading edges Aerodynamic optimization and analysis as part of 478-22078 the computer-aided design process Calculation of nonlinear aerodynamic [AIAA IAPEE 78-97] 478-22572 characteristics of wing cf complex planform Analysis and calculation of plane skew symmetric allowing fcr nose vortex sheet contours of second-order smoothness for 978-22359 channel surface design An interaction solution algorithm for viscous 478-22636 aerodynamic performance prediction Determination of the longitudinal lines cf an [AI4A PAPEB 78-153] 478-22589 aircraft fuselage by the special-contour method Modeling the influence of the ground effect on the 478-22610 aerodynamic characteristics of a wing by means Contributions to steady and unsteady aerodynamics of a flat screen of finite dimensions [DIB-FE-77-34] N78-17004 ^ A78-22634 AEBODTSAHIC DBAG Uniformly precise conforual mapping of the An investigation of strut-wall intersection losses exterior cf a circle cnto the exterior of a wing [AIAA EAEEE 78-205] A78-20743 section The significance of wing end configuration in A78-22612 airfoil design for civil aviation aircraft A study of the influence of slits on the [DGLB EAEEB 77-030] A78-24421 effectiveness of wing mechanization and controls The integrated shielded propeller as a drive in separated flow system for general aviation aircraft A78-22647 [DGLB E4PEB 77-01(5] 478-24431 Special areas of gas dynamics: Sonic, hypersonic, Theoretical aspects of droiedaryfoil lifting surfaces, wave propagation German book [AD-A047150] B78-16023 478-22937 AEBODIHAHIC FQBCES Why the flexible wing. II for glider design Normal-force and pitching-moment coefficients of A78-23058 wing-body combinations at very high angles of Successive-approximation calculation of a steady attack subsonic gas flow about an airfoil lattice [4I4A EAPEE 78-63] 478-20661 A78-24085 Effect of blade loading and thickness on the The effect of angle of attack on the aercdamping aerodynamics of oscillating cascades of wing-profile vibrations [AI44 E4PEE 78-227] 478-20756 478-24252 Perturbing forces in the hydrodynamic interaction Design of a transonically profiled wing of thin-blade cascades in a potential flew [DGIB E4EES 77-026] 478-24417 478-21219 A new airfoil family for rctor blades Contributions to steady and unsteady aerodynamics [08EBA, TP HC. 1977-113] 478-24463 [DLB-FE-77-34] 578-17001 Wind-tunnel investigaticn of aerodynamic Unsteady aerodynamic forces on harmonically performance, steady and vibratory leads, surface oscillating pointed circular conical shells with temperatures, and acoustic characteristics of a small aperture angle large-scale twin-engine upper-surface blown S78-17C07 jet-flap configuration ABBODHARIC HEATIIG [N4S4-TN-D-8235] H78-15999 Aerodynamic heating to the hypersonic research Longitudinal aerodynamic characteristics at Bach aircraft, X-24C 0.60 to 2.86 of a fighter configuration with [AIAA EAPEB 78-37] A78-20617 strut braced wing Bational parameters of reinforced panels operating [NASA-TE-1102] B78-16000 under conditions of unsteady heating Aerodynamic characteristics of an P-8 aircraft A78-2C681 configuration with a variable camber wing at Economical method for calculating unsteady Bach numbers from 1.5 to 2.0 conducted in temperature fields in thin-walled aircraft the fmes 9 by 7 foot supersonic wind tunnel structures [HASA-TH-73271] H78-16062 A78-20903

A-2 SOBJECI IHDEI AIB FLOB

AEBODJBABIC IITIBFBBE8CE JBBOELAS1ICITY Experimental observations cf vail interference at Solving the problem of numerical constrncticn of a transonic speeds model of similar rigidity to the initial [AIAA PAPEB 78-1C1] A78-20716 structure as a problem of guadratic programming Experimental investigation of support interference A78-20661 on an ogive cylinder at bigh incidence Taking into account the effect of elasticity of [AIAA PAPEB 78-165] A78-20717 the structure on the longitudinal short-period Contributions to stead; and unsteady aerodynamics motion of an aircraft [DLR-FE-77-31] N78-17001 A78-20e82 The interference prcblen of the oscillating Use of the polynomial method to calculate the fnselage near grcund parameters of the stabilized maneuver of an H78-17008 elastic aircraft AEBODYBABIC ICAES A78-20930 Turbulent boundary layer en a moving surface Bational arrangement of the structural and A78-20850 load-bearing elements of the ving with allowance Dse of a fast Fourier transformation and the Honte for certain aerodynamic requirements Carlo nethcd to calculate repeatitility cf load A78-20981 and fatigue damage of aircraft structural ihy the flexible wing. II for glider design elements under vibration excited by external A78-23058 stationary random loads Unsteady aerodynamic modeling and active B78-20932 aeroelastic control Rational arrangement of the structural and S78-16061 load-bearing elements of the ving with allowance Outline of aeroelastic phenomena for certain aerodynamic reguirements S78-17003 A78-20981 Significance of structural nonlinearities from the Hind-tunnel investigation of aerodynamic structural dynamics and aeroelasticity point of performance, steady affd vibratory leads, surface view temperatures, and acoustic characteristics of a K78-17005 large-scale twin-engine upper-surface blown Applications of structural optimization for jet-flap configuration strength and aeroelastic design requirements fNASA-TS-D-8235] H78-15999 [AGABD-B-66U] B78-17018 Two-dimensional wind tunnel test of an oscillating AEBOBAUTICAI EB6IHEEBIBG rotor airfcil, volume 2 tabulated test results The role of engineering in the flight equipment [NASA-CB-2915] B78-16998 purchasing process Dynamic stall experiments en the HACA 0012 airfoil [SASA-CB-156839] B78-17915 fNASA-TP-1100] B78-17000 AEROSOLS Farther studies of aerodynamic loads at spin entry Fire detection devices for aircraft cabins [AD-A017952] B78-17C28 A78-22900 AEBODYBABIC HOISE AEROSPACE EBGIBEEBIBG Measurements of noise produced by flow past Aerospatiale is ready to develop a convertiplane lifting surfaces with tethering rotors [AIAA PAPEE 78-239] A78-20762 [HASA-TB-75038] H78-17012 EEF noise suppression and aerodynamic penalties AEROSPACE BEDICIBE Externally Elown Flaps Toxicologic gas evaluation of the utility tactical [AIAA PAPEE 78-210] A78-20763 transport aircraft system (DH-60) Airframe noise, the lower noise limit for aircraft [AD-A017801] H78-17016 [DGLR PAPEF 77-052] A78-21111 ABBOSEACE TECHNOLOGY TBABSFEB AEBODTBABIC STABILHT Hhere aerospace can serve afresh - Paths to energy Application of the finite element methcd to the independence stability analysis of triangular plates in A78-23120 supersonic flov AEBOSPACE 7EBICLES A78-20866 Feasibility study of an Integrated Program for Stability of helicopter slung loads Aerospace vehicle Design (IPAD). Volume 5: [AEL/AEBO-BOTE-361] H78-16010 Catalog of IPAD technical program elements Evaluation of and operational procedures for a [HASA-CB-132395] H78-16015 helicopter simulation system utilizing an ABBOTBEBBOD1BABICS integrated electronic instrument display Calculation of the three-dinensional supersonic [AD-AOU7166] B78-16069 viscous heat-conducting gas flow past blunted An analysis of the influence cf seme external bodies disturbances en the aerodynamic stability of A78-21096 turbine engine axial flow fans and compressors SB-60 BELICOPTEB N78-1705U YAH-61 advanced attack helicopter design tradeoffs AEBODTBABIC STAL1I1G [SAE PAPEB 770950] A78-23801 The prediction of two-dimensicnal airfoil stall AIB BBEiTBIlG EBGIBES progression Trends and research opportunities in airbreathing [AIAA PAPEE 78-155] A78-20709 propulsion Numerical solution for airfoils near stall in [AIJA FAPEB 78-

A-3 AIB IBTAKBS SUBJECT IHDEI

MB IBTAKES AIBCBAFT Calculation of the near flow characteristics at Automated OBF freguency assignment system for FAA the inlet to the air intake located under a air traffic control communications delta wing [AD-A017817] B78-1703II A76-20895 AIBCB1FT SCCIDEBTS AI6 LAUBCHIBG The endangerment of flight safety due to wind shear An aerodynamic analysis of several hypersonic [DGLB PAPEB 77-062] A78-21118 research airplane concepts from B = 0.2 to 6.0 AIBCBAFT JHTENBAS [AIAA EAEEB 78-150] A78-20706 EBP response of aircraft antennas AIB BAVIGATIOB A78-21992 Testing a modern strike aircraft navigation systen Broad-band analysis of VLF/LF aircraft wire antennas A78-22852 J78-21995 Navigation procedure - Present systems and AIBCBAFT EBAKES developnent trends Hear studies on aircraft brake materials [DGLB PAPIE 77-018] A78-21111 478-231133 Investigation of new techniques for aircraft AIBCBAFT CCBHDBICATIOB navigation using the oaega navigation Navigation procedure - Present systems and [BASA-CB-115303] B78-17037 development trends AIB P011DT10B [DGLB EAFEB 77-018] A78-21111 Preliminary QCSEE program - Test results Quiet An optical fibre, malti-terminal data system for Clean Short-haul Experimental Engine aircraft [SAE PAEEB 771008] A78-23810 B78-168U9 AIB QUALITY AIBCBAFT COBEABTBEBTS Hind tunnel nodel study of the hot exhaust plume The experimental determination of the parameters from the Compressor Fesearch Facility at of a mathematical model of an aircraft passenger Bright-Patterson Air Force Ease, Ohio compartment as a control plant with respect to [AD-A017205] B78-16072 air temperature AIB TBAFFIC COBTBOI A78-22652 Mission management in the airport vicinity AIBCBAFT COBFIGDB4TIOBS digital flight control for terminal maneuvering EEF noise suppression and aerodynamic penalties area Externally Blown Flaps fDGLB PAFEF 77-037] A78-21127 [AIAA PAPES 78-210] A78-20763 Terminal area forecast 1976-1S88 Computational transonic flow about realistic [AD-A016513] B78-16027 aircraft configurations firline delay trends, 1971-1975. A stady of block [AIAA EAPEB 78-101] A78-22576 tine delays, ground and airborne, for scheduled Configuration development of a supersonic cruise air carriers strike-fighter [AD-A039183] B78-16028 [AIAA EAPES 78-118] A78-22587 Intermittent positive control. Phase 1: Impact of engine cycle parameters on 7/STOL Type A Operational test and evaluation configuration and commonality [AD-A017218] N78-16030 [SAE PAEEB 77C980] A78-23821 Assessment of the performance of an active ATCBBS Sensitivity studies for several high performance node for beacon collision avoidance VSTOL concepts [AD-A017670] B78-16032 [SAE PAEEB 770982] A78-23822 The Single-Site Collision Avoidance System (SS-CAS) Binimum induced drag configurations with jet [AD-40115977] B78-16035 interaction Airport surface traffic control visual ground aids [BASA-CB-1S5929] B78-17002 engineering and development plan AIBCBAFT COBSTBOCTIOB BATEBIAIS [AD-A038153] B78-16037 Fatigue of ABg6B sheet with Sprut 5H and YAK Airport surface traffic control TAGS planning coatings in the linear and plane states of alternatives and cost/benefit analysis stress under high-freguency loads [AD-A03779C] B78-16038 S78-22108 Automated DBF freguency assignment system for FAA Fracture analysis of aerospace metals air traffic control communications 178-22721 [AD-A0178U7] B78-17031 Airworthiness criteria for aluminum alloy covering Proposed technical characteristics for the with uniform corrosion damage Discrete Address Eeaccn System (DABS) 878-22737 [AD-A018216] B78-17C35 Service experience of composite parts on the Development of a discrete address teacon system L-1011 and C-130 testing monopulse beacon antennas A78-21518 [AD-AOU8217] B78-17036 An investigation of lightning damage to AIB TBANSPOBTiTIOB nonmetallic composite aircraft materials and Fuels outlook I - Transportation and the D.S. associated protective systems petroleum resource, an aviation perspective B78-17292 [AIAA PAEEf 78-357] A78-21032 AIBCBAFT COBTBOL Remoteness-compensation methodology for Bobustness of linear guadratic state feedback benefit/cost establishment and discontinuance designs in the presence of system uncertainty criteria application to Augmentor ding Jet STCL [AD-A013836] 1178-16071 Besearch Aircraft flare control autopilot design AIBBOBBE EQDIEBBBT ' A78-23917 Airborne navigation systems Integrated flight control system for future 478-22317 transport aircraft Power conditioning systems for high-power, [DGLB EAEEE 77-035] A78-2112S airborne, pulsed applications From analog to digital control systems - Improved 478-23112 performance by means of advanced technology Concorde AIDS - Powerplant applications used for commercial aircraft Airborne Integrated Data Systems [DG1B EAFEB 77-036] A78-21126 [SAE PAPEB 7709951 A78-23831 Filtering technique based on high-freguency plant General aviaticn avionics statistics: 19714 modeling for high-gain control [AD-A015209] B78-16050 [BASA-CASE-LAB-12215-1] B78-17070 A-7 ALOFT economic analysis and EHI-EBP test results Technical evaluation report on the Avionics B78-16816 Eanel/Gnidance and Control Panel Joint Symposium AIBBOBHE/SPACEEOHBE CCBEDTEBS on Avionics/Guidance and Control for Bemctely Condition monitoring experience on CF6 engines Piloted Vehicles (BPVs) [SAF EAEFB 770991] A78-23830 [AGABD-AB-113] B78-17075 Organization of a programmed matrix-operation AIBCBAFT DBSIGB system in an airborne digital computer Aerodynamic heating to the hypersonic research A78-21585 aircraft, X-21C [AIAA PAPEE 78-37] 478-20617 SUBJECT IJDBX AIBCB1FT FOEIS

Relating take off gross weight and mission A review of BASA's propulsion programs for civil requirements for gecietricallj optimized aircraft aviation [AIAA PAPEB 78-98] 178-206811 [AIAA SAPEE 78-H3J A78-206S1 Transonic ving analysis using advanced Electrical fluctuations in turbulent computational acthods electrogasdynamic flows [AIAA PAPEB 78-105] A78-20686 A78-2236"! Calculation of tbe flov past a fuselage of Analysis of the determination of arbitrary configuration at low velocities acceptance-inspection parameters for gas-turbine A78-208H5 engines Solving tbe prcblen of numerical construction of a A78-22630 nodel of similar rigidity to tbe initial Toward scranjet aircraft progress in engine structure as a problem of quadratic programing development A78-20861 A78-23121 Ose of a fast Fonrier transformation and tbe Route A clutch for V/ST01 Carlo method to calculate cepeatibility of load [SAE PAPEB 770989] A78-23826 and fatigue damage of aircraft structural Hodalar engine maintenance concept considerations eleoents under vibration excited by external for aircraft turbine engines stationary random loads [SAE EAEEB 770991] A78-23827 178-20932 Gas path analysis applied to pre and post overhaul Aerodynamic optimization and analysis as part of testing of JT9D tnrbofan engine the computer-aided design process [SAE EAEEB 770993] A78-23829 [AIAA PAPEE 78-97) A78-22572 Condition monitoring experience on CF6 engines Distributed load aircraft concepts [SAE FAEEB 77099(1] A78-23830 [AIAA PAPEB 78-100] A78-22573 Concorde AIDS - Eowerplant applications Beal flow limitations in supersonic airplane design Airborne Integrated Data Systems [AIJA PAPIB 78-107] A78-22586 [SAE EAEBB 770995] A78-23831 Configaration development cf a supersonic cruise Hinimnm-time acceleration of aircraft turbofan strike-fighter engines [AIAA PAPEB 78-1G8] A78-22587 A78-23892 Arrow wings for supersonic cruise aircraft Failure state detection of aircraft engine output [A1AA PAEEB 78-151) A78-22588 sensors Oeterainaticn of the longitudinal lines cf an 878-23906 aircraft fuselage by the special-contour method Engine development toward lower energy consumption A78-22640 and reduced environmental impact The weight of fuel tanks in aircraft [AIAA EAEBB 78-307]' A78-21I008 A78-22818 Conversion of an automotive engine for aircraft Shy the flexible wing. 11 for glider design application A78-23058 [AIAA PAPEB 78-309] A78-21I010 The impact of emerging technologies on tactical Special problems in the development of the V/STOL airplane design and utility propulsion system for an over-the-wing engine [SAE PAPEB 770985] A78-23821 configuration Flight on 0.33 horsepower - The Gossamer Condor [DGIB SAPEE 77-OU6] A78-2IIH35 [AIAA PAPEE 78-308] A78-21C09 An analytical study of thermal barrier coated The challenge cf advanced fuel-corservative first stage blades in a JT9D engine aircraft - s manufacturer's view [UASA-CB-135360] N78-16051 [AIAA EAEEB 78-362] 878-21C3"! A methodology for estimating the economic benefits Future development of commercial aircraft: of an aircraft engine warranty Technological challenge - Economic constraints [AD-80H7282] H78-16C57 [DGIB PAPEE 77-005] A78-2U102 Analytical study of thermal barrier coated Problems of supersonic transport first-stage blades in an F100 engine [DGIB PSEEB 77-007] J78-21101I [HASA-CB-135359] B78-17058 Design of a transonically profiled wing General aviation energy-conservation research [DGIB PAPEE 77-026] A78-2UU17 pro9rams at BASA-Lewis Besearch Center Profile design for an advanced-technology airfoil [HASi-TH-73880] B78-17060 for general aviation aircraft AIBCBAFT BQCIPHEHI [DGLB PAPEB 77-027] A78-21118 An evaluation of weight optimization of aircraft Aircraft performance improvement through radioelectronic egnipment retrofitting of winglets A78-226I16 [DGIB PAPEE 77-031] A78-21U22 Constant speed generating systems for aircraft The integrated shielded propeller as a drive electric power supply system for general aviation aircraft [SAE PAPEB 771001] A78-23835 [DGIB PAEEB 77-015) A78-21Q3

A-5 AIBCBSPT BiZABDS SOBJBCT IHDEI

AIBCBAFT BAZ1BDS Hew methods for tlight vibration studies using \n analysis of the aircraft trailing vortex system Fourier analysis TMAS PAEES 78-312] A78-21013 [DG1B PAPEB 77-050] A78-21139 The Lou-level Hind Shear Slert Program AIBCBAFT BOISE A78-21316 Noise transmission into a light aircraft Hake turbulence - Gone with the wind airport [AIAi PAPEE 78-197] A78-20739 advisory system for aircraft generated vortices Advanced goiet propulsion for general aviation 478-211317 [DG1E EAPEB 77-011] A78-21133 A severe dcwnslcpe windstorm and aircraft Becent advances concerning an understanding of turbulence event induced by a mountain wave sound transmission through engine nozzles and jets 878-211356 [DGIB PAPEB 77-048] A78-21137 AIBCBAFT BTDBAQLIC SISTERS Airframe noise, the lover noise limit for aircraft Flight testing an 8000 psi Lightweight Hydraulic [DGIB EAPEB 77-052] A78-21111 System Quiet propeller/rotor concept evaluation of [SAE PAEEB 771007] 878-23839 the CH-1 helicopter AIBCBJFT IBS1BUHBHTS [AD-A017297] B78-16017 Airborne navigation systems Physical analysis of the impulsive aspects of A78-22317 helicopter noise Testing a modern strike aircraft navigation systen [AD-A039715] B78-16059 A78-22852 AIBCBAFT PABTS Application of light-emitting diodes /LF.DS/ in Outline of atroelastic phenomena aircraft analog indicators B78-17003 A78-230S9 AIBCBAFT PEBFOBBABCB The dissection of an aircraft loads spectrum EBP noise suppression and aerodynamic penalties produced by peak-counting accelerometers Externally Blown Flaps [LTB-ST-951] H78-16391 [AIAA EAPEB 78-210] A78-20763 AIBCBAFT L4BEIBG Application of laminar flow control to large Effect of mnd turbulence and shear on landing subsonic military transport airplanes performance of jet transports [AIAA EAPEE 78-95] A78-22571 [AIMt EAEEE 78-219] A78-20771 Distributed load aircraft concepts Lateral stability of a light aircraft during landing [AIAA EAPEB 78-100] A78-22573 A78-21020 Transonic computational design modifications of Measured wake-vortex characteristics of aircraft the F-111 TACT in ground effect [AIAA EAPEE 78-106] A78-22577 [AIAA PAPEE 78-109] A78-22578 Beal flow limitations in supersonic airplane design Airports for short takeoff and landing [AIAA PAEEE 78-117] A78-22586 A78-23171 Some special boundary layer problems /20th Ludwig The technical potential of instrument landing Erandtl Remorial Lecture/ aircraft wing systems in the present and in the future stall characteristics [DG1B E1FEE 77-019] A78-21112 A78-23295 Hission management in the airport vicinity The Bell Bodel 222 twin engine executive digital flight ccntrcl for terminal maneuvering transport helicopter area [SAE PAPEB 770951] A78-23802 fDGlE PAEEE 77-037] A78-21127 XV-15 tilt rotor test - Progress report Piloted flight simulator study of Ion-level »ind [SAE PAEEB 770953] A78-23801 shear, phase 1 Approaches to improving aircraft efficiency [AD-A017985] H78-17078 [AIAA EAEEE 78-305] A78-21007 AIBCBAFT BAI1TEBJBCE Digital simulation of aircraft flight path Optinum schedule for replacement of aircraft dynamics using quaternions systen parts under incomplete information on [AIAA EAPEB 78-311] A78-21012 their reliability Technology readiness for an SSI A78-20879 [AIAA EAPEE 78-356] A78-21031 Hodnlar engine maintenance concept considerations Aircraft performance improvement through for aircraft turbine engines retrofitting of Kinglets [SAE PAEEB 770991] A78-23827 [DGLB EAEEE 77-031] A78-21122 Advanced turboprop propulsion system reliability Sensitivity analysis of optimal flight trajectories and maintenance cost 878-16011 [SAE PAPER 771009] A78-2381-1 Characterization of nonGanssian atmospheric Basic considerations concerning the possibilities turbulence for prediction of aircraft response of wing families it civil aviation statistics [DGLB PAEEE 77-029] A78-21120 [BASA-CB-2913] B78-16011 An investigation into the nature of aircraft AIBCBAFT BBLIABILITT supportability in the CI1C environment Distribution of reliability characteristics among [AD-A017226] H78-15991 aircraft units to ensure a given flight-safety An analysis of user acceptance and perceived level usability of C-111A job guides A78-22639 [AD-AOS7111] N78-15992 •Hew look' in assurance technology - 'The Bcrnet* An evaluation of the capability of the logistics reliability and maintainability of F-18 composite model to project the monthly aircraft [AIAA PAPEE 78-323] A78-21017 sortie effectiveness of an F-15 wing Including fleet usage variability in reliability [AD-A017227] H78-15993 analyses for both safety and economic limit Development of cost estimating relationships for [AD-A017711] B78-17398 aircraft jet core-engine overhaul costs AIBCBAFT SAIETT [AD-A017667] H78-17067 Air Force research and development activities Determination of the flight eguipment maintenance related to aircraft fire protection costs of ccmmuter airlines [AIAA EAPEE 78-269] A78-20782 [NASA-CB-152069] B78-17931 Fire detection devices for aircraft cabins AIBCBAFT BAHIDVEBS A78-22900 Dse of the polynomial nethcd to calculate the Systems analysis of safety in aviation. I parameters of the stabilized maneuver of an A78-23170 elastic aircraft Besearch requirements to improve safety of civil A78-20930 helicopters AIBCBAFT BODELS [SASA-CB-115620] B78-16026 The experimental determination of the parameters An investigation of lightning damage to of a matheiatical model of an aircraft passenger nonmetallic composite aircraft materials and compartment as a control plant with respect to associated protective systems air temperature B78-17292 A78-22652

A-6 SUBJECT IBDIZ AIBFOILS

Including tleet usage variability ID reliability AIBFOII PBOFIIBS analyses for both safety and economic limit Computational transonic airfoil design in free air CAD-A017711] B78-17398 and a wind tunnel AIBCBAFT STABILITY [AIAA SAPEB 78-103] 478-20685 Taking into account the effect of elasticity of The prediction of two-dimensional airfoil stall the structure on the longitudinal short-period progression motion cf an aircraft [AIAA IAPEE 78-155] A78-20709 A78-20882 Steady and unsteady transonic flow Dse of the polynomal methcd to calculate the [AIAA PAPEE 78-160] A78-20713 parameters of the stabilized maneuver cf an Effect of blade loading and thickness on the elastic aircraft aerodynamics of oscillating cascades 478-20930 [AIAA IAPEB 78-227] 478-20756 lateral stability of a light aircraft daring landing Approximate method of calculating the lifting 478-21020 force and the longitudinal moment of an airfoil Influence of gnst modelling on the identification section at low velocities with allowance for of the derivatives of the longitndinal lotion of viscosity an aircraft 478-20819 tB4E-HEj-TBAHS-1911] H78-17071 An aerofoil with control surface in incompressible Aircraft compensator design nethcds viscous flow [AD-A017811] B78-17073 478-23050 AIBCBAFT STBtJCTOBBS Analysis of unsteady viscous flow past an airfoil. Economical method for calculating unsteady II - numerical formulation and results temperature fields in thin-walled aircraft A78-23185 structures An experimental stndy of sound diffraction at an 478-20903 airfoil trailing edge Determination of the stress-strain state in the A78-23217 end region of a stress-raiser rib Rethod of calculating the compressible flov round 478-20917 an aerofoil or a cascade up to the shock free Dpgrading the carrying capacity of stretched transonic range panels with a stress-raiser rib by the technique 478-23271 of strain-compensating holes Successive-approximation calculation of a steady 478-20918 subsonic gas flow about an airfoil lattice Use of a fast Fourier transformation and the Honte 478-21085 Carlo method to calculate repeatibility of load Turbulent airfoils for general aviation and fatigue damage of aircraft structural 478-214361 elements under vibration excited by external Profile design for an advanced-technology airfoil stationary randon loads for general aviation aircraft 478-20932 [DGIB PAPEB 77-027] 478-21118 External interaction of the nuclear EHP iiith Rings with controlled separation aircraft and missiles [DGLB S4PEB 77-028] 478-21119 478-21989 The significance of wing end configuration in Surface current and charge density induced on airfoil design for civil aviation aircraft aircraft [DGIB F4PEE 77-030] A78-21121 478-21990 A new airfoil family for rotor blades Development of candcm fatigue data for adhesively [OHEBA, TP BO. 1977-113] A78-21163 bonded and weldbcnded structures subjected to The effect of whitcotb winglets and other wingtip dynamic excitation aircraft structures modifications on wake vortices [ASHE PJPEB 77-IA/HA1-1} 478-23373 B78-16988 Stresses and displacements due to load transfer by ilBFOIIS fasteners in structural assemblies Calculation of unsteady transonic flows using the 478-23575 integral eguation method Dse of the finite element method in fracture [AIAA FAPEB 78-13] A78-20632 mechanics An analysis method for the viscous flow over [DGLB PAPEE 77-055] A78-2

A-7 &IBFB1HB BATIBIJIS , SUBJECT IBDBI

AIHFB1HB BATIBIAI.S ALDRI1DB ALLOYS An introduction to the problem of dynamic Fatigue of AHg6fl sheet with Sprnt 5H and VAK stroctnral daoping coatings in the linear and plane states of [AGABD-B-663] H78-17071 stress under high-freguency loads AIBFB1BES 478-22108 A superelenent technique for designing helicopter Fracture analysis of aerospace metals fuselages 478-22721 478-22627 Airworthiness criteria for aluminum alloy covering & irf rame noi£e, the loner noise limit for aircraft with uniform corrosion damage [DGIB PAPEF 77-052] A78-21111 978-22737 A critigue of aircraft airframe cost models The strength of structures and the applications of [9D-A017181] 878-16018 the fracture mechanics Applications of structural optimization for 478-23571 strength and aercelastic design reguirements ABEBOBETEBS [AG9BD-B-661] H78-17018 A digital continuously updated two minute Dean AIBLIHE OPEB4TIOSS windspeed indicator for use at airports Distribution of reliability characteristics among B78-17598 aircraft units to ensure a given flight-safety AIGLB OF ATTACK level The analysis of wing-body combinations at moderate 478-22639 angles of attack The collision risk [9194 EAEEE 78-62] 978-20663 A78-22851 Hormal-force and pitching-monent coefficients of Planning for the next generation aircraft - An wing-body combinations at very high angles of airline view attack [AIAA EAEEB 78-361] 478-24033 [4IA4 PAPEE 78-63] 978-20661 Reducing aircraft noise through retrofitting Experimental investigation of support interference [DGLB EASES 77-0173 &78-2UU36 on an ogive cylinder at high incidence Airline delay trends, 1971-1975. A study of block [9199 IAEEB 78-165] 978-20717 time delays, ground and airborne, for scheduled Pressure distribution over sharp-nosed cones air carriers situated at angles of attack from 0 to 10 [AD-A039

A severe dcvnslope viedstern and aircraft Integrity in flight control systems turbulence event induced by a mountain wave A78-23873 478-21356 Specifications for IDABS1 software for short Characterization of nonGaossian atmospheric takecff aircraft avionics turbulence for prediction of aircraft response [AD-A017163] B78-16019 statistics Evaluation of S10L navigation avionics [BASA-CB-2913] H78-1601« [NASA-CB-155566] B78-17051 ATTACK AIBCB1FT Technical evaluation report on the Avionics Testing a modern strike aircraft navigaticn system Panel/Guidance and Control Panel Joint Symposium A78-22852 on Avionics/Guidance and Control for Bemotely TAH-61 advanced attack helicopter design tradeoffs Piloted Vehicles (BPVs) [SAE PAJZB 770950] A78-23801 [AGABD-AB-113] H78-17075 Sensitivity studies for several high performance AXIAL FL01 VSTOI concepts An analysis of the influence of some external [SAE PAPEB 770982] A78-23822 disturbances on the aerodynamic stability of ATTITUDE COITBOL turbine engine axial flow fans and compressors Aircraft compensator design methods 878-17051 [AD-A017811] H78-17073 AXISIBBETBIC PLOB ATTITODE IHDICATOBS Bearrangement of the flow between a pair of Aircraft attitude measurement using a vector bodies, one of which is situated in the other's magnetometer wake, in supersonic flow [BASA-CB-155565] H78-17050 A78-20913 ADTOBATIC COITBOL Ose of the singular pertnrtation nethcd to B investigate automatic control systems for automatic pilot BASE PBISSOBE A78-20802 Computation of the base pressure in ejector Su degrees of freedom system for store separation nozzles of different length with zero studies in ONEBA wind-tunnels coefficient of ejection COHEBA, IP NO. 1977-100] A78-21160 A78-21098 Automated meteorological data from ccmmcrcial BATES TBBOBEB aircraft via satellite: Present experience and Failure state detection of aircraft engine output future implications sensors [HASA-TB-73750] H78-17558 A78-23906 AOTOBJTIC FLIGHT COITBOL BBABIBG (DIBECTIOB) Integrity in flight control systems An evaluation of the fidelity of motion simulators A78-23873 using a model of human dynamic orientation Integrated flight control system for future [AD-A017120] H78-16071 transport aircraft BELL AIBCBAFT [DGLB PAPEB 77-035] A78-21125 The Bell Bodel 222 twin engine executive From analog to digital control systems - Improved transport helicopter performance by means of advanced technology [S4E EAPEB 770951] A78-23802 used for commercial aircraft BE1DIIG BOBEBIS [DGLB PAPEB 77-036] A78-21126 A study of pull-through failures of mechanically Hission management in the airport vicinity fastened joints digital flight ccntrcl for terminal maneuvering [AD-A017112] H78-16372 area BIBLIOGBAEHIES [DGLB PfPEB 77-037] A78-211427 Bibliography of lewis Besearch Center technical Study of the application of an implicit contributions announced in 1976 model-following flight controller to lift-fan [NASA-1B-73860] B78-17921 VTOL aircraft BLADE TIES [8ASA-TP-1010] H78-16C63 An improved method of calculating the tip vortex Design of noninteracting flight ccntrcl systems in geometry for hovering rotors the presence of large parameter variations H78-159S7 [NASA-CF-155589] S78-16061 BLADES iOTOHATIC PHOTS Effect of blade loading and thickness on the Dse of the singular perturbation method to aerodynamics of oscillating cascades investigate automatic control systems for [AIAA EAPEB 78-227] A78-20756 automatic pilot BIOFF BODIES A78-20802 An investigation into the effects of shear on the Robustness of linear guadratic state feedback flow past bluff bodies designs in the presence of system uncertainty [AIAA PAPEB 78-331] A78-21025 application tc Augmentor Ding Jet STOt BLOBT BODIES Besearch Aircraft flare control autopilot design Calculation of the three-dimensional supersonic A78-23917 viscous heat-conducting gas flow past blunted 40TOBATIC TEST BCOIPBEBI bodies Condition monitoring experience on CF6 engines A78-21096 [SAE PAFEB 7709914] S78-23830 BLOBT LEADIH6 EDGES ADTOBATIC WEJ7BEB STATIOBS The effect of blunting the leading edge of a delta A current weather information display system for wing on its aerodynamic characteristics during use at airports supersonic flight S78-17600 A78-20920 AOTOIOBILB B16ISES BODY-ilSG 1ID TAIL COBFIGOBJTIOSS Conversion of an automotive engine for aircraft Experimental observations of wall interference at application transonic speeds [AIAA PAPIB 78-309] A78-2U010 [AIAA FAPEB 78-161] A78-20716 Cold-air performance of free-power turbine GEBPAK: An arbitrary aircraft geometry generator designed for 112-kilowatt automotive gas-turbine [HASA-1P-1022] B78-16012 engine. 1: Design Statcr-vane-chord setting BODY-WI1G COHFIGDBAflOHS angle of 35 deg The analysis of wing-body combinations at moderate [BASA-TE-1007] S78-16053 angles cf attack AVIOHICS [AIAA FAPEB 78-62] A78-20663 Glass-fiber data bus systems for signal Cooputaticnal transonic flow about realistic transmission on board aircraft configurations A78-21976 [AIAA IAPEB 78-101] A78-22576 An evaluation cf weight optimization of aircraft Some special boundary layer problems /20th Ludwig radioelectronic eguipment Frandtl Memorial lecture/ aircraft wing A78-22616 stall characteristics A78-23295

A-9 BOEIJG 717 AIBCB&FT SUBJECT IHDEX

Special problems IB the development of the EOS COBDOCTOBS propulsion system for an over-the-wing engine Glass-fiber data bus systems for signal configuration transmission on board [DGIB PAPIB 77-006] H78-21135 678-21976 BOEIFG 717 AIBCBAFT 7a7 shuttle Carrier Aircraft/Space Shuttle Orbiter Bated ground vibration test - Data via transient excitation and fast Fourier transform analysis C-130 JIBCBAM [SAJ PAPEB 770970] S78-23815 Service experience of conposite parts on the Flutter tests of the Bated 717 Shuttle Carrier 1-1011 and C-130 Aircraft-Orbiter A78-2U548 [SAB PAPIB 770971] 478-23816 C-135 AIBCBAFT BOBOH-BEOIY COBEOOBDS Electronic ccnverter electric power supply /ECEPS/ Service experience of composite parts on the - KC-135 1-1011 and C-130 tSUE PAEEB 771003] &78-23E37 A78-21518 CABLES (BOPES) BOOHHiBY 11IEB C01TEOI Deployment forces in towing systems by aircraft Development and test of an inlet and dnct to A78-2H365 provide airflow for a mrg boundary layer CABBEBED IIHGS control system A study of the inviscid flow about conically [AISA PAEEE 78-111] A78-20701 cambered delta wings Application of laminar flow control to large [AIAA EAPEE 78-58] A78-22561 subsonic ulitary transfert airplanes Aerodynamic characteristics of an F-8 aircraft [AISA PAPEE 78-95] A78-22571 configuration with a variable camber wing at Sings with controlled separation Bach nnabers fron 1.5 to 2.0 conducted in CDGIB PAPEB 77-028] A78-21119 the Ames 9 by 7 foot supersonic wind tunnel BODNDABY LSYEB F.QDATIOHS [NASA-1H-73271] B78-16062 Turbulent boundary layer on a moving surface CASCADE FIO! A78-20850 Effect of blade loading and thickness on the BOOHDABY liYEB HOB aerodynamics of oscillating cascades Viscous thin airfoil theory and the Kutta condition [AIAA EAPEB 78-227] A78-20756 [AISA PAPEB 78-152] "178-20707 Perturbing forces in the hydrodynamic interaction An investigation of strut-sail intersection losses of thin-blade cascades in a potential flew [AISA PAPEE 78-2C5] A78-207U3 978-21219 Numerical solution for airfoils near stall in Method of calculating the compressible flow round optimized boundary-fitted curvilinear coordinates an aerofoil or a cascade up to the shockfree [AISA PAPEB 78-281] A78-20791 transonic range Plow visualization in the region of intersection A78-23271 of aerodynamic surfaces CA7ITA1IOS FIO« 1178-20951 The effect of fluid oscillations in a fuel line on Real flow limitations in supersonic airplane design the pressure head of a pump operating in a [AISA PAPEB 78-1117] A78-22586 regime without reverse streams An aerofoil with ccntrol surface in incompressible A78-21259 viscous flow CEHTBIFOGAL COBEBESSOBS A78-23050 Investigation of the ]et-wake flow of a highly Airfrane noise, the lower noise limit for aircraft loaded centrifugal conpressor mpeller [DGIB PAPEE 77-052] A78-21411 [NASA-1B-75232] N78-16051 BOUHD1BY LAYIB SBPABATIOH CEBTBIFOGA1 POBPS The prediction of two-dimensional airfoil stall The effect of fluid oscillations in a fuel line on progression the pressure head of a pump operating in a [AIBA PAPES 78-155] A78-20709 regime without reverse streams An expernental study of scnnd diffraction at an A78-21259 airfoil trailing edge CEB1HICS A78-2321I7 Ceramics in gas turbine: powder and process Some special boundary layer problems /20th Ludwig characterization Prandtl Regional lecture/ aircraft wing [BASA-TB-73875] B78-17059 stall characteristics CBABBE1 FI01 A78-23295 large amplitude shock wave motion in two The stall problem dimensional transonic channel flows S78-17006 [tIAA IASEB 78-2U73 A78-2C770 Effect of separation bobbles on the lift of wing Analysis and calculation of plane skew symmetric profiles contours of second-order smoothness for 878-17012 channel surface design BOOHDABY lAYEB TFJISITIOH A78-22636 Influence of nosetip shape on boundary layer CH6BGE DISlBIBimOB transition in arc heated jets Surface current and charge density induced on [AIAA PJPEB 78-235] &78-20759 aircraft BODHDABY 11YEBS A78-21990 Boundary layers in dissipative media CHECKOUT A78-22091 Arrival inspections/pre-operational inspections BBOAEBAHD (aviation materiel) Broad-band analysis of V1F/IF aircraft wire antennas [AD-A01I7260] B78-16376 B78-21995 CIVII AYI1TIOS BOBBIES A review of BASA's propulsion programs for civil Effect of separation bubbles on the lift of wing aviation profiles [AIAA PAPEB 78-13] A78-20651 K78-17012 Technology readiness for an SST BDILDIHGS [AIAA EAPEB 78-356] A78-21031 Preliminary comparison of model and prototype wakes Fuels outlook I - Transportation and the U.S. building wake effects on atmospheric petroleum resource, an aviation perspective boundary layer [AIAA IAPEE 78-357] A78-2H032 TAIAA PAPEB 78-254] A78-2077I1 Planning for the next generation aircraft - An BDBHIBG BATE airline view Antimisting fuel kinematics related to aircraft [AIAA PAPEB 78-361] A78-21033 crash landings Prospects for a new generation air transport [AIAA PAEEE 78-270] A78-20783 [AIAA EAPEB 78-363] A78-21035 Terminal area forecast 1978-1988 [AD-A0165U3] S78-16027

A-10 SUBJECT IBDEI COBPDTEBIZBD DBSI6B

General aviation avionics statistics: 197H COHPOSI1E SIBUCtOBBS [AD-A015209] S78-16050 Service experience of composite parts on the A review cf B&SA's propulsion programs fcr aviation 1-1011 and C-130 fHASA-TB-73831] H78-16055 A78-20518 Technical evaloaticn repcrt on the Plight COBPBBSSED AIB nechanics Panel Symposium on rotorcraft Design The start-up of a gas turbine engine using [AGAED-AB-111] H78-17019 compressed air tangentially fed onto the blades CLIBBIBG FLIGBT of the basic turbine Prediction of the ascending speeds of gliders in A78-21119 thernal convection over a plain COBPBBSSIELE FLOS A78-23398 Approximate method of calculating subsonic CLUTCHES compressible flows past a lifting wing profile A clutch for V/STCI J78-20883 [SAE PAPEB 770989] A78-23826 Velocity profiles in the Laval nozzle throat for COCKPITS uniform compressible swirling flow On so Be singular acoustic signatures observed in J78-20905 the cockpit of a twin engined jet aircraft Bethod of calculating the compressible flow round [AIAA PAPIE 78-212] A78-20765 an aerofoil or a cascade up to the shockfree COLLISION AVCIDJSCB transonic range The collision risk A78-23271 A78-22851 A numerical method for calculating the unsteady Initial collision avoidance algorithms for the aerodynamic pressure distribution on beacon-based collision avoidance sjsten harmonically oscillating wings with control [AD-AOU72501 H78-16031 surfaces in subsonic flow. Theory and results Assessment of the performance of an active ATCEBS for compressible flow, part 2 node for beacon collisicr avoidance [ESA-T1-130] B78-17C29 [AD-A017670] N78-16032 COBPBESSOBS The Single-Site Collision Avoidance System (SS-CAS) An analysis of the rotor blade stresses of the [AD-AOI45977] B78-16035 three stage compressor of the Ames Besearch COBBDSTIOB PHTSICS Cente'r 11- by 11-foot transonic wind tunnel Trends and research opportunities in airbreathing [KASA-CB-152083] B78-17061 propulsion COBPDTBB GBAPBICS [AIAA PAPEB 78-111] A78-20652 Touch input as alternative to keyboard and rolling CQHBOSTIOB VIBBATIOB ball fcr the radar controller at the Theory of two frequency ranges of unstable display-screen place of operation in oscillations of turbulent combustion in a ground-based flight control ]et-engine chamber. I - formulation of the [DGtE IAPEE 77-021] A78-21111 stability problem, the characteristic equation COBPOTEB EBOGBAHHIBG A78-21253 Organization of a programmed matrix-operation COBHEBCIA1 AIBCEJPT system in an airborne digital compnter Big fans for the airlines A78-2U585 A78-22269 Specifications for IDABST software for short Fracture analysis cf aerospace metals takeoff aircraft avionics A78-22721 [iD-1017163] B78-16009 Planning for the next generation aircraft - An COaPDTBE PBCGBABS airline view A least square finite element technique for [AIAA PAPEB 78-361] A78-21033 transonic flow with shock Prospects for a new generation air transport [AIAi EAPEB 78-328] A78-21022 [AIAA PAPZB 78-363] A78-21035 A generalized vortex lattice method for subsonic Future development cf ccmmercial aircraft: and supersonic flow applications Technological challenge - Economic constraints [BASA-CB-2865] B78-16002 [DG1E PAPEB 77-005] A78-21102 Feasibility study of an Integrated Program for Problems of supersonic transport Aerospace vehicle Design (IPAD). Volume 5: [DG1B PAPEE 77-007] A78-211IOU Catalog of IPAD technical program elements The significance of wing end configuration in [BASJ-CB-132395] B78-16015 airfoil design for civil aviation aircraft GEBPAK: An arbitrary aircraft geometry generator [DOLE PBPEB 77-030] A78-21121 [BASA-IP-1022] B78-16012 From analog to digital control systems - Improved A discrete-event digital simulation model of the performance by means of advanced technology F-16 fire control compnter operational flight used for commercial aircraft program using simscript 2.5 [DGIB PAPEE 77-036] A78-2UQ26 [AD-A018161] B78-17017 General aviation avionics statistics: 1971 An examnaticn of selected digital flight generators [AD-A015209] 878-16050 [AD-A017815] B78-17081 Automated metecrolcgical data from commercial COBPUTEB STSTEBS DES1GB aircraft via satellite: Present experience and Integrated flight control system for future future implications transport aircraft [BASA-TB-73750] B78-175'58 [DGLB PAPEE 77-035] A78-21125 COHPOBEBT BELIABIUTT COBIOTEBIZED DBSIGB Optimum schedule fcr replacement of aircraft Solving the problem of numerical construction of a system parts under incomplete information on model cf similar rigidity to the initial their reliability structure as a problem of quadratic programming A78-20879 A78-20861 Analysis of the determination of Calculation of nonlinear aerodynamic acceptance-inspection parameters for gas-turbine characteristics of wing of complex planform engines allowing for nose vortex sheet B78-22630 A78-22359 COBPOSITB BiTBBISlS Aerodynamic optimization and analysis as part of Trends and research opportunities in airbreathing the computer-aided design process propulsion [AIAA PAPEE 78-97] A78-22572 [AIAA PAPEB 78-11] A78-20652 Computational wing optimization and wind tunnel Holographic inspection cf jet engine composite fan test of semi-span model blades [AIAA FAPEE 78-102] A78-22575 [SAE PAPEB 770975] A78-23819 Transonic computational design modifications of An investigation cf lightning damage to the F-111 1ACT nonoetallic composite aircraft materials and [AIAA PAPEB 78-106] A78-22577 associated protective systems Determination of the longitudinal lines of an N78-17292 aircraft fuselage by the special-contour method A78-22610

A-11 COHPDTBBIZED SIBD1ATIOB SUBJECT IBDBX

System identificaticn principles applied to C01TODBS multivanable control syrthesis of the F100 Analysis and calculation of plane skew symmetric tucbofan engine contours of second-order smoothness for &78-238S9 channel surface design Frequency donain compensation of a DYHGEB turbofan A78-22636 engine nodel Determination of the longitudinal lines of an A78-23890 aircraft fuselage by the special-contour method Flight on 0.33 horsepower - The Gossamer Condor A78-22610 [AIAA PAEEJ 78-308] A78-21009 C01TBOL BOAEDS COBPOTEBIZED SIBOIATI01 Instructor pilot's role in simulation training, numerical siiulaticn of the interaction of jet anfl phase 2 freestream flows in engine exhaust systems [AD-AOU7919] B78-17082 [AIAA PAEEB 78-111] A78-22E81 COBTBOL EC01PBEBT Gas path analysis applied to pre and post overhaul Detection of sensor failure and output testing of JT9D tarbofan engine reconstruction for aircraft engine controls [SAE PAPEE 770993] A78-23829 [AIAA EAPEB 78-1] A78-20627 A singular perturbation analysis cf optimal Aircraft compensator design methods aerodynamic and thrust magnitude control [AD-A047811] S78-17073 A78-23900 COITBOI SIBOIAIIOS Stress history simulation. Volume 2: A nsers Filtered seguential regression parameter manual for a coiputer program to modify stress identification applied to a gas turbine engine history simulations crack propagation in model fighter aircraft A76-23879 [AD-A012785] H78-17C11 Hinimum-time acceleration of aircraft turbofan Airport improvement task force delay study: Delay engines model validation plan A78-23892 [AD-A018112] N78-17077 COBTBOL SOEFiCBS An exanination of selected digital flight generators A study of the influence of slits on the [AD-AOIJ7BU5] N78-17C8I1 effectiveness of wing mechanization and controls COHCOEDE AIBCBAFT in separated flow Concorde AIDS - Powerplant applications A78-22617 Airborne Integrated Data Systems An aerofoil with control surface in incompressible [SAE PAPEB 770995] A78-23831 viscous flow Problems of supersonic transport A78-23050 [OGLE PAPIB 77-007] A78-21101 Electromechanical flight control actuation COHDBCTIVZ BEAT TBABSJBB [SAE EAPEB 771004] 478-23838 Steady-state balk temperature field in cooled Study of a supercritical profile with oscillating turbine blades control surface in sub- and transonic flews A78-21156 [OBF.BA, TP HO. 1977-136] A78-21168 Calculation cf the thermal state of turbine blades COBTBOI 1BBOBY with film cooling Use of the singular perturbation method to A78-21271 investigate automatic control systems for COBFEBBBCBS automatic pilot Design to cost/life cycle costing; Proceedings of A78-20802 the Conference, Washington, D.C., November Dynamic oodel of a system of scientific research 16-18, 1977 and industrial plants A78-21838 A78-22C15 Technical evaluation report on the Flight The experimental determination of the parameters Mechanics Panel Symposium on rotorcraft Design of a mathematical model of an aircraft passenger [AGABD-AB-111] N78-17019 compartment as a control plant with respect to Technical evaluation report on the Avionics air temperature Panel/Guidance and Control Panel Jcint Symposium A78-22652 on Avionics/Guidance and Control for Eemotely COBTB01IAEILITI Piloted Vehicles (BSVs) Intermittent positive control. Phase 1: [AGSBD-AE-113] H78-17075 Operational test and evaluation COHFOBBAI 8AEPIBG [AD-A0172I19] B78-16030 Uniformly precise conformal mapping of the Study of the application of an implicit exterior cf a circle cnto the exterior of a wing model-following flight controller to lift-fan section VTOI aircraft A78-22612 [NASA-TP-1010] N78-16063 numerical solution for seme problems concerning COBVEBGEBT-EIVEB6EHT BOZZLES unsteady mcticn cf airfcils Velocity profiles in the laval nozzle throat for H78-15995 uniform compressible swirling flow COHICA1 BODIES A78-20905 Pressure distribution over sharp-nosed cones Calculation of the Laval-nozzle flow by a modified situated at angles of attack from 0 to 10 Lax-Rendroff method of second-order accuracy degrees in supersonic flc« A78-20970 478-20889 Experimental investigation of asymmetric Laval COHICil FlOB nozzles Supersonic flow near a thin trapezoidal wing A78-22361 A78-20921 COOLIBG Hypersonic flow past a conical wing with detached Steady-state bulk temperature field in cooled shock wave at the leadinc edges turbine blades A78-22C78 A78-21156 Study of supersonic separated flos past ccnical COOLIBG STSTBHS wings and inside a right angle Evaluation of a large capacity heat pump concept A78-22C79 for active cooling of hypersonic aircraft A study of the inviscid flew about conically structure camrered delta vings [BASA-CB-115301] B78-17339 [AIAA PAPEF 78-58] A78-22561 COBBEB FLOB COWICiL SBELIS Study of supersonic separated flow past conical Unsteady aerodynamic forces on harmonically wings and inside a right angle oscillating pointed circular ccnical shells with J78-22079 small aperture angle Some special boundary layer problems /20tb Ludwig H78-17C07 Prandtl Bemorial Lecture/ aircraft wing stall characteristics A78-23295

A-12 SUBJECT IIDEI DEI 14 BUGS

CQBBEL1TIOI CBITICAI IOADIB6 Two point correlations of jet noise Taking structural and technological constraints J78-23219 into account in the design of uaiiinn-stiffness COBBOSIOB PBBVB1TIOB load-bearing structures Coatings for fretting prevention A78-20880 A78-231U1 CBOSS COOP1UG COBBOSI01 BF.SISTABCE Design of noninteracting flight control systems in Airworthiness criteria for aluminum alloy covering the presence of large parameter variations with uniform corrosion damage [BASA-CB-155589] B78-16C61 J78-22737 CBOSS FLOS COST AIA1TSIS Laser-velocineter surveys of merging vortices in a Design to cost/life cycle costing; Proceedings of wind tunnel the Conference* Hashingtcn, D.C., Bovenber [AIAA EAPEB 78-107] A78-20687 16-18. 1977 Calculation of general three-dimensional turbulent A78-21838 boundary layers Bio fans for the airlines A78-23188 S7S-22269 CBODE Oil Advanced turboprop propulsion system reliability Fuels outlook I - Transportation and the U.S. and naintenance cost petroleum resource, an aviation perspective [SiE PAEEB 771009] A78-23841 [SIAA EAPEB 78-357] A78-21I032 A critique of aircraft airframe ccst models CBOISIBG PLIGHT [AD-A047181] S78-160148 Configuration development of a supersonic cruise Bemoteness-ccmpensation methodology fcr strike-fighter benefit/cost establishment and discontinnance [AIAA PAPEB 78-1Q8] A78-22567 criteria Arrow wings for supersonic cruise aircraft [AD-AOH3836] B78-1607H [AIAA EAPEB 78-151] A78-22588 Preliminary United surveillance radar (LSB) COBBEBT DEBSITT cost/benefit analysis Surface current and charge density induced on [AD-A046829] B78-16215 aircraft Determination of the flight egnipient naintenance A78-21990 costs of counter airlines [BASA-CB-152069] B78-17931 COST EFJECTI1BBESS Approaches to improving aircraft efficiency DABEIBG [AIAA PAPEB 78-305] A78-2«007 An introduction to the problem of dynamic lling mth fork tips as Deans of increasing cost structural damping effectiveness of transpcrt aircraft [JGABC-B-663] B78-17071 [DGLB PAPEB 77-017] A78-21U10 DATA 1IBRS Basic considerations concerning the possibilities A-7 A1CF1 economic analysis and EBI-IBP test results of wing families in civil aviation B78-16816 [DG1B PAPEB 77-029] &78-2ia20 Proposed technical characteristics for the COST ESTIHATBS Discrete Address Beacon System (DA£S) A methodology for estinating the economic benefits [AD-AOM82U6] B78-17035 of an aircraft engine warranty DATA PBOCESSIBG [AD-AOU7282] N78-16057 Observational computation in the case of redundant Development of cost estimating relationships for measurements for position sensor data in aircraft jet core-engine overhaul costs radio navigation systems [AD-A017667] B78-17C67 A78-23133 COST BEDOCTIOB DATA SISTERS A combined potential and viscous flow solution for Condition monitoring experience on CC6 engines V/STOL engine inlets [SAE PAPEB 77C99U] A78-23830 CAIAA PAPEB 78-112] A78-20702 Concorde AIDS - Powerplant applications Application of skin technology to turbine blades Airborne Integrated Data Systems zero gravity manufacture [SAE PAPEB 770995] A78-23831 [AIAA PAPEB 78-285] A78-20792 DATA TBAHSBISSIOB Ccnversion of an automotive engine for aircraft An optical fibre, multi-terminal data system for application aircraft [AIAA PAPEE 78-3C9] A78-21010 B78-168D9 COSIS DC 10 AIBCBAFT Establishaent of new major public airports in the Piloted flight simulator study of low-level wind Dnited States shear, phase 2 [AD-AO!)6<)62] B78-16C75 [AD-A017251] B78-16C67 CRACK EBOPAGJTIOH DECISIOI BARIBG Fatigue crack growth in a pressure-fuselage panel An assessment of relevant decision making factors A78-226U9 for organic versus contract maintenance options Fracture analysis cf aerospace netals on OSAF flight simulators A78-22720. [AD-A017136] B78-16070 Spectrum crack growth in adhesively bended structure DEGBEES OF FBEEDOB [ASBE PAPFB 77-SA/HAT-7] A78-23372 Six degrees cf freedom system for store separation The strength of structures and the applications of studies in CNEBA wind-tunnels the fracture mechanics [OHEBA, TE BO. 1977-100] A78-21P60 87.8-23573 DE1AI Stress history simulation. Volume 2: A users Airport improvement task force delay study: Delay manual fcr a computer program tc ncdify stress model validation plan history siiolations crack propagation in [AD-A018112] B78-17C77 fighter aircraft DELTA 8IBGS [AD-A012785] H78-1704H Calculation of the mean flow characteristics at CBAC1QBG (FBACTOBIBG) the inlet to the air intake located under a In-state delivery and reinforcenent cf rigid delta wing airport causeways - Soie technical prcbleis and A78-2C895 attempts using special coatings The effect of blunting the leading edge of a delta A78-2I1375 wing on its aerodynamic characteristics during CBASB LABDIBG supersonic flight Antiaisting fuel kinematics related tc aircraft A78-20920 crash landings Two new correlation dependencies for parameters of [AIAA PAPEB 78-27C] A78-20783 flow on a plane delta wing A78-20933

A-13 DBPLOYBEBT SOBJECT IHDEI

Effect of the thickness of profile and trailing From analog to digital control systems - Improved edge on the flow field and the aerodynamic performance by means of advanced technology characteristics of a lo«-aspect-ratio delta wing used for commercial aircraft at B = 3 [DGIE PAPEB 77-036] A78-2II126 978-20919 Specifications for IDABST software for short Hypersonic gas flov past a flat delta «ing takeoff aircraft avionics A78-20966 [AD-A017163] 878-16019 Effect of a ccnical break cf delta-iiings on the DIGITAL TBCBBIQDBS aerodynamic characteristics An examination of selected digital flight generators A78-21081 [AD-AOH7815] H78-17081 Hypersonic flow past a conical meg with detached DIBECTIOHJI COHTEOL shock wave at the leading edges Expansion oj flight simulator capability for study A78-22078 and solution of aircraft directional control Study of supersonic separated flow past conical problems on runways, appendixes wings and inside a right angle [BASA-CB-115281] B78-16066 A78-22079 Aircraft attitude measurement using a vector Calculation of nonlinear aerodynanic magnetometer characteristics cf wing cf couple! planfcrm [HASA-CB-155565] B78-17050 allowing fcr nose vortex sheet DISCBABGB COEFFICIEBT 978-22359 Experimental investigation of the characteristics A study of the inviscid flew about conically of snail-sized nozzles cambered delta wing* A78-21090 [AIAA FAFEE 78-58] A78-22561 DISCRETE ADD6ESS BBACOH STSTEB DEPLOYBEBT Proposed technical characteristics for the Deployment forces in towing systems by aircraft Discrete Address Beacon System (DABS) A78-21365 [AD-A018216] H78-17035 DESIGB 4BALYSIS DISCBETE FOBCIIOBS Subsonic vortex-flew design study for slender wings flethod of calculating the compressible flow round [AIAA PAPEE 78-151] A78-20708 an aerofoil or a cascade up to the shockfree Design to cost/life cycle costing; Proceedings of transcnic range the Conference, Hashington, D.C., Bovember A78-23271 16-18, 1977 DISPLAY DEVICES A78-21838 Application of light-emitting diodes /LEEs/ in Performance-optimized horizontal-axis wind turbines aircraft analog indicators A78-22232 A78-23C59 Design and analysis of propellers for low Eeynolds Touch input as alternative to keyboard and rolling number application to mini-BPV's ball for the radar controller at the [SAE PAFEB 770999] A78-23831 display-screen place of operation in DEB ground-based flight control A current weather information display system for [DGLE FAEEB 77-021] A78-21111 use at airports Evaluation of and operational procedures fcr a B78-17600 helicopter simulation system utilizing an DIFFEHEBTIA1 EQOATIOBS integrated electronic instrument display A numerical stnfly of incompressible viscous flow [AD-A017166;) S78-16069 around airfcils A current weather information display system for N78-16996 use at airports DIGITAI COBPDTEBS F78-17600 Organization of a programmed matru-cperation DBAS system in an airborne digital computer Subsonic vortex-flow design study for slender wings A78-211585 [AIAA FAPEB 78-151] A78-20708 DIGITAL BAVIGITIOB DBAG BEDOCT10H Observational computation in the case of redundant Tnrbulent airfoils for general aviation measnrenents for position sensor data in A78-21361 radio navigation systems Hing with fork tips as means of increasing cost A78-23133 effectiveness of transport aircraft Mission management in the airport vicinity [DGIE EAPEF 77-017] A78-21110 digital flight ccntrcl for terminal maneuvering Theoretical aspects of dromedaryfoil area [AD-A017150] B78-16023 [DGLE PAPEE 77-037] A78-21127 DBOBE AIBCBAFT DIGITS! BAEAE SYSTBBS Twenty year evolution of the WB2/HB21 series of Touch input as alternative to keyboard and rolling small turbojet engines ball for the radar controller at the [SAE PAPEB 770998] 478-23833 display-screen place of operation in DDCTED FA1 E1GIIES ground-based flight control Development and test of an inlet and duct to TDGIF PAEEE 77-021] A78-21111 provide airflow for a wing boundary layer DIGITAL SIHOLATIOB control system Effect of wind turbulence and shear en landing [AIAA PAPEE 78-111] A78-20701 performance cf jet transports DYBABIC CSABACTEBISTICS [ilAA PAPEB 78-219] A78-20771 An introduction to the problem of dynamic System identification principles applied to structural damping •ultivariable control synthesis of the E100 [AGABE-B-663] B78-17071 turbofan engine DYBABIC BODELS A78-23689 Dynamic model of a system of scientific research Frequency domain compensation of a DYBGIN turbofan and industrial plants engine model J78-22615 A78-23890 Unsteady hovering wake parameters identified from Digital simulation of aircraft flight path dynamo model tests dynamics using quaternions B78-16992 [AIAA PAEEE 78-311] A78-21C12 DYBABIC BESPOISE A discrete-event digital simulation model of the The endangerment of flight safety due to wind shear F-16 fire control computer operational flight [DG1B EAPEE 77-062] A78-21H18 program using simscript 5.5 Dynamic stall experiments on the BACA 0012 airfoil [AE-A018161] 1178-17017 [BASA-1P-1100] B78-17000 DIGITAL SYSTEMS DYBABIC STEOCTDBAL ANALYSIS Integrated flight control system for future Significance of structural nonlinearities from the transport aircraft structural dynamics and aeroelasticity point of [DG1B PAJEE 77-035] 978-24125 view B78-17005 SDEJECT IRDII EBGIBF. DESIGB

DTHABIC TESTS EBE response of aircraft antennas Seynolds naaber criticality ID dynamo tests A78-21992 [SIAA PAPIE 78-166] A78-20718 ELECTBOI&GBETIC IBTBBFEBBBCE A-7 ALOFT economic analysis and EHI-IHP test results B78-16816 ILECTBOBAGBEIIC POISES EC08CBIC A8AITSIS Eiternal interaction of the nuclear EBP with Planning for the nezt generation aircraft - Sn aircraft and missiles airline view A78-21989 [AIAA PAPEE 78-361] A78-24033 Surface current and charge density induced on Comments en 'Feasibility stndy cf a hybrid airship aircraft operating ID ground effect1 A78-21990 A78-21367 EBP response of aircraft antennas Future development of ccmnercial aircraft: A78-21992 Technological challenge - Econonic constraints ELECTBOHECBASICAL DEVICES [DGLB PAPEE 77-005] A78-21402 Electromechanical flight control actuation Including fleet usage variability in reliability [SAE PAPEB 771004] A78-23838 analyses for both safety and economic limit BLECTBOBIC COBTEOL [AD-A017711] 1178-17398 Integrity in flight control systems BCOSOBIC BACTOBS A78-23873 Prospects for a new generation air transport ELECTBOBIC COUHTEBBEASOHES [AIAA PAPEB 78-363] A78-2H035 Airborne electronic warfare in the modern military A methodology for estnating the eccncmic benefits force of an aircraft engine warranty [AIAA PAPEB 78-321] A78-21018 [AD-A047282] S78-16057 ELECTBOHIC EQBIPBEBT EJECTORS Evaluation of and operational procedures fcr a The prediction of the performance of low helicopter simulation system utilizing an pressure-ratio tbrust-augmenter ejectors integrated electronic instrument display [AIAA PAPEB 78-115] A78-20701 [AD-A017166] N78-16069 Computation of the base pressure in ejector ELEVOBS nozzles cf different length with zero Analysis of heat transfer in a simulated coefficient cf ejecticn wing-elevon cove in hypersonic flow A78-21098 [AIAA IAPEE 78-1(0] A78-22E56 ELASTIC DBFOEBATICN EHEEGT COISEBTATIOR Elastic deformations of rapidly-rotating prismatic The challenge of advanced fuel-conservative mirrors aircraft - A manufacturer's view A78-2137I! [AIAA PAPEE 78-362] J78-2M031 Outline of aeroelastic phenomena General aviation energy-conservation research H78-17003 programs at HASA-Lewis Besearch Center E1ASTIC P1ATES [MASA-Tn-738811] H78-17060 Stress-strain state of simply-supported BNEBGI COBSDBPTIOH three-layer trapezoidal plates Alternative aircraft fuels A78-21205 [NASA-TB-73836] S78-17229 EIASTOPLASTICITI EHEBGT COBVEBSIOB Concerning the relationship between element Electronic converter electric power supply /ECEPS/ stability and system stability in wing-truss - KC-13S structure made frcm elastic and elastc-plastic [SAE PAPEB 771003] J78-23837 materials BBEBGT EOLICI A78-21971 Fuels outlook I - Transportation and the O.S. EIECTBIC COBTiCTS petroleum resource, an aviation perspective Turbine engine slip ring technology - A survey [AIAA EAPEE 78-357] A78-24032 for aircraft EHEBGT TECBBOLOGT [SAE PAPEB 770976] A78-23820 Performance-optimized horizontal-axis wind turbines EIECTBIC EOOIPBEHT A78-22232 Aircraft electrical equipment Enssian book where aerospace can serve afresh - Paths to energy A78-21175 independence ELECTBIC GBHEBATOBS A78-23120 Variable speed constant freguency /VSCP/ aircraft EBGIRE COBTBOL electrical power Detection of sensor failure and output CSAE PAPEB 771002] A78-23836 reconstruction for aircraft engine controls ELECTBIC POSES SUPPLIES [AIAA EAPEE 78-Q] A78-20627 Power conditioning systems for high-power, Filtered sequential regression parameter airborne, pulsed applications identification applied to a gas turbine engine A78-23112 model Constant speed generating systems for aircraft A78-23879 electric pcwer supply System identification principles applied to [SAE PAPEB 771001] A78-23835 multivariable control synthesis of the F100 Electronic converter electric pcwer supply /ECEPS/ turbcfan engine - KC-135 A76-23689 [SAE PAPEB 771003] A78-23837 Freguency domain compensation of a DINGED tnrbofan EIECTBIC POISES engine model Electrical fluctuations in turbulent A78-23890 electrogasdynamic flews The application of the Bouth approximation method A78-2236q to turbcfan engine models ELBCTBICAt IBEEDAICE A78-23891 EHF response of aircraft antennas Optimal ccntrols for an advanced turbofan engine A78-21992 A78-23893 ELECTBODYiASICS Design of turbofan engine controls using output Electrical fluctuations in turbulent feedback regulator theory electrogasdynamic flows A78-23907 A78-22361 EBSIBB DESICB ELECTBOBSGBBTIC IBTEBACTIOBS A review of BASA*s propulsion programs fcr civil Eiternal interaction of the nuclear EHP with aviation aircraft and mssiles [AISA FAPEB 78-13] 478-20651 A78-21989 Trends and research opportunities in airbreathing Surface current and charge density induced on propulsion aircraft [AIAA PJPEE 78-11] A76-20652 A78-21990 EHGIBE FAIltJBE SUBJECT IBDEI

Construction of a mathematical model of a ]et EBGIHE TESTS engine fcr analyzing transient floss Analysis of the determination of A78-20971 acceptance-inspection parameters for gas-turbine Bag fans fcr the airlines engines A78-22269 A78-22630 Research needs for U.S. Army aircraft propulsion Toward scranjet aircraft progress in engine [AIAA PAPIB 78-115] S78-22558 development Twenty year evcluticn of the WB2/HB21 series of A78-23121 small turbojet engines Development cf low pressure ratio vectoring fSAE PAFEE 770998] A78-23833 nozzles for V/STOL aircraft Preliminary QCSEE program - Test results Quiet [SAE PAPEB 770988] A78-23625 Clean Short-haul Experimental Engine Gas turbine module performance analysis [SAF PiPIE 771008] A78-23610 [SAE PAPEE 770992] A78-23828 Eamjet propulsion for single-stage-to-orbit vehicles Gas path analysis applied to pre and post overhaul [SAE FAEEE 771011] A78-23813 testing of JT9D turbofan engine Design of tnrbcfan engine controls nsing output [SHE PBSEB 77C993] A78-23829 feedback regulatcr theory Condition monitoring experience on CF6 engines A78-23907 [SAE PAPEB 770991] A78-23830 Approaches to improving aircraft efficiency Preliminary QCSEE program - Test results Quiet [AIAA PAPFB 78-305] A78-21007 Clean Short-haul Experimental Engine Engine development toward lover energy consumption [SAF PAPEE 771008] A78-23810 and reduced environmental impact Theory cf two frequency ranges of unstable [AIAA P--PF.E 78-307] A78-21C08 oscillations of turbulent combustion in a Conversion of an automotive engine for aircraft jet-engine chamber. I - Formulation of the application stability problem, the characteristic equation [AIAA PAEEI 78-3C9] 478-21010 A78-21253 Investigation cf the inclination cf nozzle blades Internal performance predictions for langley on the alternating stress level in working scramjet engine module turbine blades [BASA-TH-X-71038] H78-17C57 178-21273 low speed test of a high-bypass-ratio propulsion Advanced quiet propulsion for general aviation system with an asymmetric inlet designed for a CDGIE SJPEB 77-0113 A78-2H33 tilt-nacelle V/STOL airplane Special problems in the developnent of the [BASA-CE-152072] B78-17062 propulsion system for an over-the-wing engine Evaluation of the extended use of ferrocene for configuration test cell smoke abatement engine and [DGLB PJPF.B 77-016] A78-21135 environmental test results Cold-air performance of a tip turbine designed to [AD-A017659] B78-17079 drive a lift fan. 3: Hffect of sinulated fan EBTBOP* leakage on turbine performance Interaction of a shock wave with an entropy layer [HASA-TP-1109] B78-16001 J78-20886 Cold-air performance of free-power turbine Entropy layer in two-dimensional flows designed for 112-kilo»att automotive gas-turtine hypersonic ideal gas flow behind shock wave engines 1: Design Statcr-vane-chord setting A78-21132 angle of 35 deg EBVIBOIBEBT EFFECTS rsiSA-Tp-1007] 1178-16053 The effect of ambient conditions on the emissions Optimization study for high speed radial turbine of an idling gas turbine with special reference to design variables [AIAA PAPEE 78-3] A78-22551 [BASA-CB-152091] B78-17063 EBTIBOBHE1T POLLDTIOB ERGIBE FAIIQBE Engine development toward lower energy consumption Modular engine maintenance concept considerations and reduced environmental impact for aircraft turbine engines [AIAA PAPEE 78-307] A78-21008 [SAE PAPER 770991] A78-23827 EHVIBOHBEBT PEOTECTIOB Failure state detection of aircraft engine output The effect of ambient conditions on the enissions sensors of an idling gas turbine A78-23906 [AIAA PAPEE 78-3] A78-22551 Failure detection and correction for turbofan EBTIBOBBEBTAI TESTS engines Evaluation of the extended use of ferrocene for A78-23918 test cell smoke abatement engine and EHGIBE IHIETS environmental test results A combined potential and viscous flow solution for [AD-A017659] B78-17079 v/STCl engine inlets EQOIVilBBT CIRCUITS [AIAA PAPEB 78-112] A78-20702 EHP response of aircraft antennas Advanced scavenge systems for an integrated engine A78-21992 inlet particle separator Broad-band analysis of VIF/LF aircraft wire antennas [AD-A017872] S78-17C69 A78-21995 EHGIBE HOBHOBIBG IHSTBOHEBTS EVS1DATIOB Failure state detection of aircraft engine output Airport improvement task force delay study: Delay sensors model validation plan A78-23906 [AD-A018112] N78-17C77 EBGIBE NOISE EXBAOST F10I SIBOIATIOB On some singular accustic signatures observed in Bumerical sivulation of the interaction of jet and the cockpit of a twin ergined jet aircraft freestream flows in engine exhaust systems [AIAA WPEE 78-212] A78-20765 [AIAA PAPEB 78-111] A78-22581 EBGISE P6ETS BIHftDST CASES Temperature distributions and thermal stresses in Hind tunnel model study of the hot exhaust plume a graded zirccnia/metal gas path seal system for from tie Compressor Research Facility at aircraft gas turbine engines Bright-Patterson Air Force Base, Ohio [AIAA PAPEB 78-93] A78-20683 [AD-A017205] B78-16072 ENGIBE STABIEBS Optical measurements of BO and BC sub 2 in the The start-up of a gas turbine engine using exhaust of an F101-GE-100 engine at simulated compressed air tangentially fed onto the blades altitudes of the basic turbine [AD-A017882] . B78-17C6B A78-21119 EXBAOST BOZZLES EBGIBE TESTIBG 1AEOB1TOBIES Bumerical simulation of the interaction of jet and T-30-P-7 installed trim correction freestream flows in engine exhaust systems [ AE-AOI)7023] B78-16058 [AIAA PAPEB 78-111] A78-22E81 General ^viaticn energy-conservation research prograus at SASA-Iewis research center [NASA-T1-73881] B78-17060

A-16 SOBJECT IBDFI FIGBTEB AIBCBAFT

EXBAOST SISTERS FAST IOOBIEB TE4BSFOBB4IIOBS The effect of ambient conditions on the emissions Ose of a fast Fourier transformation and the Rente of an idling gas turbine Carlo method to calculate repeatibility of load [AIAA E-AEEB 78-3] 478-22551 and fatigue damage of aircraft structural EITBBH4L STOBB SBEABATIOB elements under vibration excited by external Six degrees cf freedom system for store separation stationary random loads studies ID CBEBA wind-tunnels 478-20932 [OBEBA, TF BC. 1977-1CO] «78-20160 FASTEBEBS BITBBBil STOBBS Stresses and displacements dne to load transfer by The OBEBA position on the use of feed-back control fasteners in structural assemblies against flutter due tc eiternal ving-mcnnted 478-23575 stores A study of pall-through failures of mechanically [OBEBJ, IF BO. 1977-101] A78-21161 fastened jcints EITBBIALII BIOSB FIAPS [AD-A017112] B78-16372 EBP noise suppression and aerodynamic penalties FATIGUE TESTS Externally Blown Flaps Ose of a fast Fourier transformation and the Honte [AIAA PAPEE 78-210] A78-20763 Carle method to calculate repeatibility of load •ings with controlled separation and fatigue damage of aircraft structural [DGLB E4PEB 77-028] A78-21119 elements under vibration excited by external Rind-tunnel investigation of aerodynamic stationary random loads performance, steady and vibratory loads, surface 478-20932 temperatures, and acoustic characteristics of a Fatigue cf 4Rg6H sheet with Sprut 5(l and YAK large-scale twin-engine upper-surface blown coatings in the linear and plane states of jet-flap configuration stress under high-frequency loads [1ASA-TB-D-8235] H78-15999 478-22108 Airworthiness criteria for aluminum alloy covering with uniform corrosion daaage 478-22737 P-8 4IBCBAFT Stresses and displacements due to load transfer by Aerodynamic characteristics of an F-8 aircraft fasteners in structural assemblies configuration with a variable camber wing at 478-23575 Bach numbers from 1.5 tc 2.0 conducted in FEASIBILITY ABAIISIS the Ames g by 7 foot supersonic vind tunnel Comments on 'Feasibility study of a hybrid airship [HASA-Tfl-73271] B78-16062 operating in grcund effect* P-15 AIBCESFT A78-21361 An evaluation cf the capability of the logistics Feasibility study of an Integrated Program for composite model tc project the monthly aircraft Aerospace vehicle Design (IPAD). Volume 5: sortie effectiveness of an 1-15 Ming Catalog of IPAD technical program elements [AD-AOH7227] B78-15993 [BASA-CB-132395] B78-16015 f-16 1IBCBAFT Feasibility study of negative lift circumferential A discrete-event digital simulation model of the type seal for helicopter transmissions P-16 fire ccntrol computer operational flight [BASA-CB-135302] H78-17390 program using sinscript 2.5 FEEDBACK COSTBOI [AD-A048161] H78-17017 Electromechanical flight control actuation P-18 SIBCBAFT [SAE EAPEB 7710011] A78-23838 'Sew look1 in assurance technology - 'The Hcrnet' System identification principles applied to reliability and maintainability of F-18 multivariable control synthesis of the F100 TAISA P4PEB 78-323] 478-2*017 turbofan engine P-100 AIBCBAEI A78-23889 Analytical study of thermal barrier coated Frequency domain compensation of a DTHGER turbofan first-stage Hades in ar F100 engine engine model [HASA-CE-135359] S78-17058 A78-23890 P-101 AIBCB4FT Design of tnrbofan engine controls using output Optical measurements of HC and HO sub 2 in the feedback regulator theory eihaust of an F101-GF.-10C engine at simulated A76-23907 altitudes Bobustness of linear quadratic state feedback [AD-A017882] H78-17C68 designs in the presence of system uncertainty ?-111 AIBCBAFT application to Angmentor Ding Jet STOI Transonic computational design modifications of Besearch Aircraft flare control autopilot design the F-111 TACT 478-23917 TAIAA PJPEE 78-106] A78-22577 Failure detection and correction for turbofan TF-30-P-7 installed trim correction engines [AD-A017023] N78-16058 A78-23918 yill-SAPE SISTERS The ONEBA position on the use of feed-back control Electromechanical flight ccntrol actuation against flutter due to external ving-ncanted [SAE PAEEf 7710011] 478-23838 stores PAILOBB ABAIISIS [OBEBA, TP BO. 1977-101] A78-21U61 Systems analysis of safety in aviation. I FEBBOCBBBS 478-23170 Evaluation of the extended use of ferrocene for Failure state detection of aircraft engine output test cell smoke abatement engine and sensors environmental test results A78-23906 [AD-A01765S] B78-17079 Failure detection and correction for turbofan FIBEB OPTICS engines A-7 ALCFT economic analysis and EBI-IBP test results A78-23918 B78-16816 PAILOBB BODES An optical fibre, multi-terminal data system for Detection of sensor failure and output aircraft reccnstructicn fcr aircraft engine controls 878-16819 [AIAA PAPEB 78-1] A78-20627 FISBTBB AIBCBAFT A study of pull-through failures of mechanically Relating take off gross weight and mission fastened jcints requirements for geometrically optimized aircraft [AD-A017112] B78-16372 [AIAA EAPEE 78-98] 478-20681 FAB FIELDS Configuration development of a snperscnic cruise Two pcint correlations cf jet noise strike-fighter 478-23219 [AIAA EAPEB 78-118] A78-22587 Impact of engine cycle parameters on V/ST01 Type A configuration and commonality [SAE PAPBB 770980] A78-23821

A-17 FILAHEBT RIDDING SUBJECT IHDEI

Sensitivity studies for several high performance Application of the finite element method to the VSTCl concepts stability analysis of triangular plates in [SAB PAPER 77C982] A78-23822 supersonic flow The inpact of emerging technologies on tactical A78-2C866 V/STOL airplane design ard utility FLAT SOBFJCES [SAE PAPIB 770985] A78-23821 localization and shielding of noise sources Longitudinal aerodynamic characteristics at Hach generated by the interaction of free jets with 0.60 to 2.86 of a fighter configuration mth flat surfaces strut traced wing [DGIB PAPEE 77-019] A78-21H38 [NASA-TP-1102] B78-16000 FLEXIBLE RIHGS Further studies of aerodynamic loads at spin entry Shy the flexible wing. II for glider design [90-8047952] N78-17028 A78-23058 Stress history simulation. Volume 2: A users FLIGHT CBAB1CTEEISTICS manual for a computer program to modify stress The integrated shielded propeller as a drive history Emulations crack propagation in system for general aviation aircraft fighter aircraft [DGIE EAPEB 77-045] A78-2443M [AD-A102785] B78-170f|« FLIGHT COBDITIOIS FHAHEHT URGING Simulation of the flight conditions in the Filament-winding fabrication of QCSEE ionosphere configuration fan blades A78-20915 [NASA-CE-135332] N78-16052 FLIGHT COBTBOL FI1H COOLING Glass-fiber data bus systems for signal Calculation of the thermal state of turbine blades transmission on board with filn cooling A78-21976 A78-2427I! Electromechanical flight control actuation FIHITI DIFFEBEBCE THEOBY [SAE PAPEB 771004] A78-23838 Numerical solution for airfoils near stall in Sensor failure detection using analytical redundancy optimized boundary-fitted curvilinear coordinates A78-23862 [AIAA PAPEE 78-284] A78-20791 Research and development of aircraft control Calculation of the Laval-nozzle flew by a modified actuation systems. The development of a direct Lax-Hendroff method of second-order accuracy drive fly-by-wire flight control system and A78-20970 evaluation of a force sharing fly-ty-wire actuator Analysis of unsteady viscous flew past an airfoil. [AD-A041283] 1178-16065 II - Numerical formulation and results Experimental testing of flight control head up 878-23185 displays Calculation of general three-dimensional turbulent [NASA-TH-75205] N78-17053 boundary layers FLIGHT LOAD BECOBDBBS A78-23188 The dissection of an aircraft loads spectrum The practical application of a finite difference produced by peak-counting accelerometers method for analyzing transonic flow over [LTB-ST-951] N78-16391 oscillating airfoils and wings FLIGHT BECH2RICS [NASA-CB-2933] 878-16999 Sensitivity analysis of optimal flight trajectories FINITE ELEBBHT BBTBOD N78-16041 Application of the finite element method to the FLIGHT OPIIBIZITIOB stability analysis of triangular plates in Singular perturbation analysis of optimal flight supersonic flow profiles fcr transport aircraft A78-20866 A78-23901 An interaction solution algorithm for viscous FLIGHT PAIHS aerodynamic performance prediction Digital simulation of aircraft flight path [AIAA PAPEE 78-153] A78-22589 dynamics using guaternions A superelement technigue for designing helicopter [AIAA PAPEE 78-311] A78-24012 fuselages Hission management in the airport vicinity A78-22627 digital flight control for terminal oianeuvering A least square finite element technigue for area transonic flow with shock [DGLB PAPEB 77-037] A78-2!)l|27 [AIAA PAPEE 78-328] A78-24022 An examination of selected digital flight generators Dse of the finite element method in fracture [AD-A047845] N78-17084 mechanics FLIGHT SAFETY [DGLB PAPEF 77-055] A78-24443 Distribution of reliability characteristics among FIBE COHTBOL aircraft units to ensure a given flight-safety A discrete-event digital simulation mcdel of the level F-16 fire ccntrol computer operational flight A78-22639 program using simscript 2.5 The collision risk [AD-A048164] H78-17047 A78-22851 FIBE PBEVENTION The Low-level Rind Shear Alert program Air Force research and development activities A78-2U346 related to aircraft fire protection Touch input as alternative to keyboard and rolling [AIAA PAPES 78-269] A78-20782 ball for the radar controller at the Antimisting fuel kinematics related to aircraft display-screen place of operation in crash landings ground-based flight control [AIAA PAPEE 78-270] A78-20783 [DGIE SAPEE 77-021] A78-20qi!l Fire detection devices for aircraft cabins The endangerment of flight safety due to wind shear A78-22900 [DGLB EAPEB 77-062] A78-24448 FLAPS (COBTBOl SURFACES) FLIGHT SIBOLATIOB Measurements of noise produced by flow past Digital simulation of aircraft flight path lifting surfaces dynamics using guaternions [AIAA PAPEE 78-239] J78-20762 [AIAA PAPEB 78-311] A78-24C12 Turbulent boundary layer on a moving surface Simulation tests of flight technical error in A78-20850 2D/3D area navigation (BHAV) using a multiple FLAT PLATES waypcint ENAV system with and without a flight Numerical solution for airfoils near stall in director system optimized boundary-fitted curvilinear coordinates [AD-A047246] N78-16029 [AIAA PAPEE 78-2811] A78-20791 Piloted flight simulator study of low-level wind Calculation of the flow of a rarefied gas past a shear, phase 1 plate of infinite span [AD-A047985] H78-17078 A78-20857 An examination of selected digital flight generators [AD-A047845] B78-17084

A-18 SUBJECT IBDZI FOSSIL FOBIS

FLIGHT SIBULiTOBS FlOi GEOBBTEY Development of the propulsion sinulator - A test Bearrangement of the flow between a pair of tool applicable to V/STCL configurations bodies, one of which is situated in the other's [SAE PAPEB 7709811] A78-23823 wake, in supersonic flow Expansion of flight sinulator capability for study 478-20913 and solnticn of aircraft directional control FLOS BEtSDBEBElt problems on runways, appendixes Heasurements of unsteady vortex flow fields [HASA-CB-115281] H78-16066 [4ISA PAPEB 78-18] A78-22551 Piloted flight sinalator study of Ion-level wind wake vortex measurements of bodies at high angle shear, phase 2 of attack [4D-4017251] B78-16067 [AIAA FAPEE 78-23] 478-22555 Evaluation of and operatioDal procedures for a FLOR TBBOBT helicopter simulation systen utilizing an Viscous thin airfoil theory and the Kntta condition integrated electronic instrument display [4I4A PAPEB 78-152] 478-20707 [4D-A017166] B78-16C69 FLOR VELOCITY An assessment of relevant decision making factors The flew about a slender propeller-driven body in for organic versus contract maintenance options a temperature stratified fluid on OSAF flight simulators [AIAA PAPEB 78-209] 478-20736 [AD-A017136] H78-16070 Velocity profiles in the Laval nozzle throat for An evaluation of the fidelity of notion simulators uniform compressible swirling flow using a acdcl of human dynamic orientation J78-20905 [AD-AOII7120] H78-16071 An analytical model for the study of highly Instructor pilot's role in simulation training, separated flow en low speed airfoils phase 2 B78-16S95 [AD-A017919] B78-17082 FLOR VISOALIZATIOI FUGBI TBSIS An investigation of strut-wall intersection losses Reynolds number criticality in dynamic tests [AIAA PAPEE 78-205] 478-20713 [AIAA PAPEB 78-166] A78-2071S Flow visualization in the region of intersection On sone singular acoustic signatures observed in of aerodynamic surfaces the cockpit of a twin engined jet aircraft 478-20951 [AIAA PAPEB 78-212] S78-20765 FLUID BOC1DIBIES Testing a modern strike aircraft navigation system Boundary layers in dissipative media S78-22852 478-22091 XV-15 tilt rotor test - Progress report FLOID DIBASICS [SAF, PAPEB 770953) 478-23804 Optimization study for high speed radial turbine Flutter tests cf the mated 717 Shuttle Carrier with special reference to design variables Aircraft-Orbiter [NAS4-CB-152091] H78-17C63 rSAI PAIEB 770971] H78-23816 FLOTTBB Flight testing an 8000 psi lightveight Hydraulic Effects of structural non-linearities on aircraft System vibration and flutter CSAE PAPIF 771007] 478-23839 [4G4BD-B-665] 1178-17076 Flight on 0.33 horsepower - The Gossamer Condor FLUTTER 1BALYSIS [AIAA PAPEB 78-3C8] 478-21009 4pplication of the finite element method to the An analysis of the aircraft trailing vortex systen stability analysis of triangular plates in [AIAA PAPIE 78-312] A78-21013 supersonic flow New methods for flight vibration studies using A78-20866 Fourier analysis Taking into account the effect of elasticity of [DGLB PAPEB 77-050] A78-21139 the structure on the longitudinal short-period Evaluation cf slimtack style parachute in CT1A motion of an aircraft airtrainez aircraft A78-20882 [AD-AOU7083] H78-16021 Dse of the polynomial method to calculate the FLIGBT TBJIBIBG parameters of the stabilized maneuver cf an Instructor pilot's role in simulation training, elastic aircraft phase 2 478-20930 [AD-A0147919] B78-17082 Ose of a fast Fourier transformation and th€ Honte FLOR CHAEJCTBBISTICS Carlo methcS to calculate repeatibility of load Calculation of the mean flew characteristics at and fatigue damage of aircraft structural the inlet tc the air intake located under a elements under vibration excited by external delta wing stationary random loads A78-20895 478-20932 The low-speed air tunnel of the Institute of Flutter tests of the mated 747 Shuttle Carrier Hydromechanics at the University of Karlsruhe Aircraft-Orbiter A78-23297 [S4F PAPEB 770971] A78-23816 FLOS DISTOBIIOI The effect of angle of attack on the aerodamping A study on the mechanise cf compressor surge due of wing-profile vibrations to inlet pressure disturbances 478-211252 [AIAA PAPEB 78-216] A78-20769 Investigation of the inclination of nozzle blades FLOS DISTBIBOTIOR on the alternating stress level in working Effect of the thickness of profile and trailing turbine blades edge on the flow field and the aercdyramic 478-21273 characteristics of a low-aspect-ratio delta wing New methods for flight vibration studies using at B = 3 Fourier analysis 478-20949 [DG1B PAPEB 77-050] 478-21139 A method for the ccnstruction of flow nozzles and The ONEBA position on the use of feed-back control wind tunnel ccntracticn sections against flutter due to external wing-mcunted 478-21635 stores Measurements of unsteady vortex flow fields [OBEB4, TP BO. 1977-101] 478-21161 [AISS PAPEB 78-18] 478-22551 Research on the flutter of axial-turtomachine wake vortex measurements cf bodies at high angle blading of attack [AD-A017086] B78-16021 [AIAA PAPEB 78-23] 478-22555 FLI BT RIBE COITBOI An interaction solution algorithm for viscous Preliminary design study of an integrated tail aerodynamic performance [rediction rotor serve power module [AIAi P4PEB 78-153] 478-22589 [AD-4017678] B78-17C72 A solution to the direct problem of an open FOSSIL FUELS propeller using the streamline curvature method 41ternative aircraft fuels [AIAA PAPEE 78-310] 478-2q011 [BASA-TB-73836] N78-17229 Flowfield and pressure field of a model propeller 478-20051

i-19 FOOBISB AB41TSIS SDBJECT IHDEI

FOOBIBB 4BA11SIS General aviation energy-conservation research New methods for flight vitiation studies using programs at NASA-Lewis Besearch Center Courier analysis [BASA-lli-73881] B78-17060 (DGIB PAEIB 77-050] 878-21139 EOE1 FOB PS FBACTOBE HECBABICS The effect of fluid oscillations in a fuel line on The strength of structores and the applications of the pressure head of a pump operating in a the fracture mechanics regime without reverse streams S78-23571 A78-21259 Use of the finite elenent method in fractnre JOEL tABKS mechanics The weight of fuel tanks in aircraft [DG1B PAPSB 77-055] 478-21113 A78-22818 FBACfOBE STBIBGTB POEI IESTS Fracture analysis cf aerospace netals Antimisting fuel kinematics related to aircraft 878-22721 crash landings FBEE COWVECTIOB [AIAA FAPEE 78-270] A78-20783 Prediction of the ascending speeds of gliders in FOIL SCAIB fEStS thermal convection ever a plain Beynolds number criticality in dynamic tests S78-23398 [AIAA FAPEB 78-166] A78-20718 FBEB SLOS Preliminary comparison of model and prototype wakes Numerical simulation of the interaction cf jet and building wake effects on atmospheric freestream flews in engine exhaust systems boundary layer [8148 FAPEB 78-111] 478-22581 [AIAA I4PEE 78-251] 478-20771 Drag on an oscillating airfoil in a fluctuating FOSBLAGES free strean Calculation of the flow past a fuselage of S78-16991 arbitrary configuration at low velocities Effects of acoustic and vortical disturbances on A78-2C815 the turbulent boundary layer at free-stream nach A superelement technique for designing helicopter- number 0.5 fuselages [AD-A01I7921] S78-17C26 A78-22627 FBBB JETS Determination of the longitudinal lines of an Interaction of a shock wave with an entropy layer aircraft fuselage by the special-contour method 478-20886 478-22610 Localization and shielding of ncise sources Fatigue crack growth in a pressure-fuselage panel generated by the interaction of free jets mth A78-22619 flat surfaces On some structure-turbulence interaction problems [DGLK PJEEB 77-019] 178-21138 N78-15996 FBBIGBTEBS The interference problem of the oscillating Distributed lead aircraft concepts fuselage near ground [AIAA EAPEB 78-100] 878-22573 B78-17008 FBEQDEHCIES Snperelement method of designing a helicopter Filtering technigue based en high-frequency plant fuselage modelinc fcr high-gain ccntrol B78-17013 [BASA-C8SE-LSB-12215-1] N78-17070 FBEQOEBCJ SSSIGBBEBT Automated DBF freguency assignment system for F4A air traffic ccntrcl communications GAS DETECTOBS [8D-A017817] B78-17031 Fire detection devices for aircraft cabins FBEQOEBCY BESEOBSE A78-22900 Broad-band analysis of VIF/LF aircraft wire antennas GAS DTBSBICS 478-21995 Special areas of gas dynamics: Sonic, hypersonic, Hew freguency domain methods for system lifting surfaces, wave propagation German book identification 478-22937 478-23883 GAS F10S Freguency domain compensation of a DYBGEB turbofan Three-dimensional hypersonic gas flow past a thin engine ncdel wing 478-23890 A78-20795 The application of the Bouth apprcumaticn method The basic characteristics of the variation of to turbcfan engine models aerodynamic parameters in the transition region 678-23891 at hypersonic flow velocities FBBTTISG A78-20900 Coatings for fretting prevention Bypersonic gas flow past a flat delta wing 878-23111 878-20966 FBICTIOB EBAG Calculation cf the Laval-nozzle flow by a modified Drag on an oscillating airfoil in a fluctuating Lax-Rendroff method of second-order accuracy free stress 478-20970 H78-16991 Construction of a mathematical model of a jet FBICIIOB IACTOB engine for analyzing transient flows Friction and wear cf sintered fibermetal abradable 878-20971 seal materials Entropy layer in two-dimensional flows 478-23151 hypersonic ideal gas flow behind shock wave FUEL COHEDSTIOH 878-21132 The effect of ambient conditions en the emissions Transonic swirling gas flow through a nozzle cf an idling gas turbine J78-22355 [AI4A P4PEB 78-3] 878-22551 Outline of aeroelastic phenomena FDEI COHSOBETIOH B78-17003 4 singular perturbation analysis cf cptnal GAS IMECtlOB aerodynamc and thrust magnitude ccntrol Thrust characteristics of thrust vector control 478-23900 systems with blowing injection of chemically Engine development toward lower energy consumption nonreactive gases and reduced environmental impact 478-21251 [SI84 PSPEE 78-3C7] 478-21008 GAS TEBPEBATOBB Fuels out leek I - Transportation and the O.S. Rind tunnel model study of the hot exhaust plume petroleni resource, an aviation perspective from the Compressor Besearch Facility at [AIAA P8PIB 78-357] 478-21032 Wright-Patterson Air Force Base, Ohio The challenge cf advanced fuel-conservative [AD-A017205] B78-16072 aircraft - 4 manufacturer's view [JIA4 P4fEF 78-362] 478-21031

A-20 SUBJECT HDEI

GiS TOBBIBE EB6IHES GLASS PIBEBS Temperature distributions and thermal stresses in Glass-fiber data bus systems for signal a graded zirconia/metal gas path seal system for transmissicn on board aircraft gas turbine engines A78-21976 fAIJA PAPEB 78-93] A78-20683 GLIDEBS The effect of anbient conditions on the emissions Shy the flexible wing. II for glider design of an idling gas turbine A78-23C58 [1I4A PAPEB 78-31 A78-22551 Prediction of the ascending speeds of gliders in Research needs for O.S, Amy aircraft propulsion thermal convection over a plain [AUK PAPEF 78-15] A78-22558 S78-23398 Analysis of the determination of GOVEBHEBT/IBDOSTBT BE16TIOBS acceptance-inspection parameters for gas-turbine Planning for the next generation aircraft - An engines airline view A78-22630 [AIAA FAPEE 78-361] A78-21033 Friction and near cf sintered fibermetal abradable Prospects for a new generation air transport seal materials [AIAA PAPEB 78-363] A78-21035 A78-23151 6B4PHITB-EPOIT COBPOSITE BATEBIAIS Transient expansion of the components of an air Service experience of composite parts on the seal on a gas turbine disc 1-1011 and C-130 [SAE PAFIB 77097U] A78-23818 A78-21518 Development of the propnlsion simulator - A test Filament-winding fabrication of QCSEE tool applicable tc VXSTOL configarations configuration fan blades [SAE PAPEB 7709811] A78-23823 [HASA-CB-135332] B78-16052 Hodular engine maintenance concept considerations GBOOID BASED COBTBOl for aircraft turbine engines The technical potential of instrument landing [SAE PAPEB 770991] A78-23827 systems in the present and in the future Gas turbine module performance analysis [DGLE IAPEB 77-019] A78-21112 [SAE PAPEB 770992] A78-23828 Touch input as alternative to keyboard and rolling Filtered sequential regression parameter ball fcr the radar controller at the identification applied to a gas turbine engine display-screen place of operation in model ground-based flight control A78-23879 [DGIE SAPEF 77-021] A78-21111 Engine development toward lower energy consumption GBOOBD EFFECT (AEBODJBABICS) and reduced environmental impact Heasured wake-vortex characteristics of aircraft [AIAA PAPEB 78-3C7] A78-24008 in ground effect The start-up of a gas turbine engine using [AIAA PAPEB 78-109] A78-22578 compressed air tangettially fed onto the blades The role of atmospheric shear, turbulence and a of the basic turbine ground plane on the dissipation of aircraft A78-21119 vortex wakes Calculation of the thetmal state of turbine blades [AIAA PAPEB 78-110] A78-22579 sith film ceding Hodeling the influence of the ground effect on the A78-21271 aerodynamic characteristics of a wing by means Cold-air performance of free-power turbine of a flat screen of finite dimensions designed fcr 112-Xilcwatt automotive gas-turbine A78-22631 engine. 1: Design Stator-vane-chord setting Comments on 'Feasibility study of a hybrid airship angle of 35 deg operating in ground effect1 [HASA-TF-1007] B78-16053 A78-21367 Ceramics in gas turbine: Ponder and process The interference problem of the oscillating characterization fuselage near ground [NASA-TB-73875] 878-17059 H78-17008 Evaluation of the extended use of ferrocene for GBOOBD SDPPOBT EQOIPBEHT test cell smoke abatement engine and Heliccpter Ground nobility System (HGBS) concept environmental test results formulation and selection [AD-A017659] H78-17C79 [AD-A0175C7] B78-17080 GAS TOBBIBBS GBOOBD TESTS Advanced scavenge systems for an integrated engine Testing a modern strike aircraft navigation system inlet particle separator A78-22852 [AD-A007872] K78-17069 Tovard scramjet aircraft progress in engine GASES development Toxicologic gas evaluation of the utility tactical A78-23121 transport aircraft system (DH-60) 717 Shuttle Carrier Aircraft/Space Shuttle Orbiter [AD-A017801] H78-17016 mated ground vibration test - Data via transient GEBBBAl AtlATIOB AIBCBIFT excitation and fast Fourier transform analysis The Bell Hodel 222 twin engine executive [SAI PAPEB 770970] A78-23815 transport heliccpter GOIDABCE SEBSOBS [SAE PAPIB 770951] A78-23802 Observational computation in the case of redundant Approaches to improving aircraft efficiency measurements for position sensor data in [AIAA PAPEB 78-305] A78-21I007 radio navigation systems Engine development tovard lover energy consumption A78-23133 and reduced environmental impact GOST LOADS [AIAA PAPEB 78-307] A78-21008 Sellable lifting surface solutions for unsteady flow Turbulent airfcils for general aviation [AIAA PAPEB 78-228] A78-20757 A78-21361 Atmospheric turbulence loads on aircraft Profile design for an advanced-technology airfoil A78-23019 for general aviation aircraft COSTS [DGIB PAPEB 77-027] A78-21118 Characterization of nonGanssian atmospheric Advanced quiet propulsion for general aviation turbulence for prediction of aircraft response [DGIB PAPEB 77-011] A78-21133 statistics The integrated shielded propeller as a drive [HASA-CB-2913] B78-16011 system for general aviation aircraft Influence of gust modelling on the identification [DGLB PJPEB 77-015] A78-21131 of the derivatives of the longitudinal motion of General aviaticn energy-conservation research an aircraft programs at HASA-tewis Besearch Center [BAE-LIB-TFASS-1911] H78-17071 [HASA-TB-73881] H78-17060 GEOHETBT An improved method of calculating the tip vortex geometry fcr hovering rotors H78-15997

A-21 BAHHOBIC OSCILHTIOB SUBJECT IBDBI

Helicopter Ground nobility System (BGBS) concept H formulation and selection [AD-A017507] H78-17080 BjBaomc OSCILLATIOI Feasibility study of negative lift circumferential Calculation of unsteady transonic flows using the type seal for helicopter transmissions integral equation netbod [BASA-CB-135302] B78-17390 [AIAA PAPEE 78-13] S78-20632 BIGB iCCELEBATIOB Study of a supercritical profile tilth oscillating Hinimnm-time acceleration of aircraft tnrbcfan control surface in sut- and transonic flows engines [ONEBA, TP NO. 1917-136] 978-211168 A78-23892 Unsteady aerodynamic forces on harmonically BIGB ALTITUDE oscillating pointed circular conical shells with The tropospheric and stratospheric composition snail aperture angle perturbed by HO/i/ emissions of high-altitude 878-17007 aircraft BEAD-DP DISPLAYS A78-21003 Experimental testing of flight control head up BIGB GAIN displays Filtering technique based on high-frequency plant rBASA-TB-75205] H78-17053 modelinc for high-gain control BEAT PUBES [NASA-CASE-LAB-12215-1] 878-17070 Evaluation of a large capacity heat punp concept BIGB STBENGTB for active cooling of hypersonic aircraft Applications of structural optimization for structure strength and aeroelastic design reguirements [NASA-CE-115301] 878-17339 [AGABD-B-661] 878-17008 HEAT SBIELDIBG BOLE DISIBIBDTIOB (BECBABICS) Evaluation of a large capacity heat pump concept Upgrading the carrying capacity of stretched for active cooling of hypersonic aircraft panels with a stress-raiser rib by the technique structure of strain-compensating holes [BASA-CE-115301] 878-17339 A78-20918 BEAT SINKS BOLOGBAPBIC IBTEBFEBCHETBY Study of heat sink themal prctecticn systems for Holographic inspection of jet engine composite fan hypersonic research aircraft blades fAIAA EAEEE 78-36] A78-20618 [SAE PAPEB 770975] A78-23819 BEAT TBABSFBB BOT-FILB ASEBOBBTEBS Analysis of heat transfer in a simulated An experimental study of three-dimensional wing-elevon cove in hypersonic flow characteristics of propeller wakes under [AIAA PAPEB 78-10] A78-22556 stalling conditions BELICOPTEB DESIGN A78-21632 A superelement technique fcr designing helicopter BOVEBIBG fuselages An improved method of calculating the tip vortex A78-22627 geometry for hovering rotors Mechanism of wear in helicopter hydraulic systems K78-15997 S78-23139 Evaluation of and operational procedures for a YAH-61 advanced attack helicopter design tradeoffs helicopter simulation system utilizing an [SAE PAPEB 770950] A78-23801 integrated electronic instrument display The Bell aodel 222 twin engine executive [AD-A017166] 878-16069 transport helicopter Unsteady hovering wake parameters identified from [SAE EAPEB 770951] J78-23802 dynamic model tests Army UTTAS program UB-GOA helicopter for 878-16992 Utility Tactical Transport Aircraft System BOVEBIBG STABILITY [SAE PAPEB 770952] S78-23803 Analysis of spread multi-jet VTOL aircraft in hover Status report en the Advancing Blade Concept /ABC/ [BASA-CB-155582] 878-16016 technology demonstrator program HOBAB PEBFOBHABCE [SAE PAPEE 770951] A78-23805 An analysis of user acceptance and perceived A new airfoil family for rotor tlades usability of C-111A job quides [ONEBA, TP HC. 1977-113] 478-21163 [AD-A017111] B78-15992 Snperelement method of designing a helicopter BYBBID NAVIGATION SISTEBS fuselage Navigation procedure - present systems and B78-17013 development trends BELICOPTEB EBGIBBS [DGLB PAPEE 77-018] A78-21111 Besearch needs for D.S. Army aircraft propulsion BYDBAOLIC EQUIPBEBT [AIAA PAPEB 78-15] A78-22558 flechanism of wear in helicopter hydraulic systems BELICOPTEB EEBFOBBABCE A78-23139 Stability of helicopter slung leads Preliminary design study of an integrated tail [AEL/AEEO-SOTE-361] 878-16010 rotor serve power module Helicopter Ground Bobility System (BGHS) concept [AD-A017678] B78-17072 formulation and selection BYDBOCABBOB FUELS [AD-A017507] B78-17080 Future aviation turbine fuels BELICOPTEBS [AIAA PAPEB 78-268] A78-20781 Evaluation of slinpack style parachute in CT1A BYDBODIBABIC EQUATIONS airtrainer aircraft Construction of a mathematical model of a jet [AD-A017083] 878-16021 engine for analyzing transient flows Besearch reguirements tc ntprove safety of civil A78-20971 helicopters BYDBOGEB-BASED EBEBGI [NASA-CE-115620] 878-16026 Where aerospace can serve afresh - Paths to energy Quiet propeller/rotor concept evaluation of independence the OH-1 helicopter A78-23120 [AD-A017297] B78-16017 BYPBBSOBIC AIBCBJPT Physical analysis of the iipulsive aspects of Aerodynamic heating to the hypersonic research helicopter noise aircraft, J.-21C [AD-A039715] B78-16C59 [AIAA PAPEE 78-37] A78-20617 Evaluation of and operational procedures for a Study of heat sink thermal protection systems for helicopter simulation system utilizing an hypersonic research aircraft integrated electronic instrument display [AIAA FAPEB 78-38] A78-20618 [AD-A017166] 878-16C69 The application of dual fuel /JP-LB2/ for Preliminary design study of an integrated tail hypersonic cruise vehicles rotor servo power module [AIAA FAPEB 78-119] A78-20705 [AD-A017678] H78-17072 An aerodynamic analysis of several hypersonic research airplane concepts from fl = 0.2 to 6.0 [AIAA EAPEE 78-150] A78-20706

A-22 SOBJZCT IIDII ITERATIVE SOLOTIOB

Toward scraujet aircraft progress ID engine IHFIBHB SP4I ilBGS development Calculation of the flow of refied gas past a A78-23121 plate of infinite span BYPEBSOHIC FIOS 478-20857 Three-dimensional hypersonic gas flow past a thin IHFOBHATIOB PLOI wing The problem of technology transfer: Beal or 478-20795 imagined Calculation of the flow of a rarefied gas past a [AD-1012961] H78-17913 plate of infinite span IBFOBBATIO1 B4BA6BBEBT 178-20857 Feasibility study of an Integrated Program for A formulation of the problem of the minimum-drag Aerospace vehicle Design (IP4D). Volume 5: wing Catalog of IPAD technical progran elements 478-20867 [B4S4-CB-132395] B78-16015 The basic characteristics cf the variation cf IBLBT F10B aerodynamic parameters in the transition region A combined potential and viscous flow solution for at hypersonic flew velocities V/STOL engine inlets 478-20900 [4I4A EAPEB 78-112] 478-20702 Characteristics of the ]et acceleration cf a flow 4 study on the aecbanism of compressor surge due to hypersonic speeds to inlet pressure disturbances A78-20953 [AIAA EAPEB 78-216] 478-20769 HYpersonic gas flow past a flat delta mng Calculation cf the mean flow characteristics at A78-20966 the inlet to the air intake located under a Effect of a ccnical break cf delta-Mings en the delta wing aerodynaoic characteristics A78-20895 A78-21C81 Stress analysis study in cooled radial inflow Entropy layer in two-dimensional flo*s turbine hypersonic ideal gas flov behind shock wave [AI44 EAEEE 78-91] 478-22570 A78-21132 IBSPEC1IOB Hypersonic flow past a conical wing tilth detached Arrival inspections/pre-operational inspections shock wave at the leading edges (aviation materiel) A78-22078 [AD-4017260] B78-16376 Analysis cf heat transfer in a sinalated IBSTBOBEBT LABDIHG SISIEBS •ing-eleven cove in hypersonic flow The technical potential of instrument landing [AIAA EAPEB 78-140] 478-22556 systems in the present and in the future Special areas of gas dynamos: Sonic, hypersonic, [DOLE EAPEE 77-019] A78-21112 lifting surfaces, wave propagation German took Experimental testing of flight control head up A78-22937 displays [HASA-1B-75205] B78-17053 IBTAEE STSTEBS Development and test of an inlet and duct to IDBAl GAS provide airflow for a wing boundary layer Entropy layer in two-dimensional flows control system hypersonic ideal gas flew behind shock wave [AIAA EAPEB 78-111] A78-20701 478-21132 ISTEGBi! 2QD1II01S IBPBDASCI HEASDIE1EJTS Calculation of unsteady transonic flows using the EBE response of aircraft antennas integral eguation method 478-21992 [AIAA EAEEE 78-13] 478-20632 IBPBLIBBS Viscous thin airfoil theory and the Kntta condition Investigation of the jet-wake flow of a highly [AIAA EAFEB 78-152] A78-20707 loaded centrifugal compressor impeller IRTEBFEBBICI HIT [H4SA-TB-75232] N78-16051 Experimental observations of wall interference at IBPOLSBS transonic speeds Physical analysis of the itpulsive aspects of [AI44 FAPEE 78-161] A78-20716 helicopter noise IBTEBBAL CORBOSTIOB EBGIBES [AD-A039715] H78-16059 Conversion of an automotive engine for aircraft IH-FIIGBT BOSITOBIHG application Condition icnitoring experience on CI6 engines [AIAA EAPEB 78-309] 478-21010 [SAI PAEEB 770991] 478-23830 IBVISCID FIOI IHCOBEBESSIEIE FIOI Inviscid supersonic flow about a thin rectangular Viscous thin airfoil theory and the Kutta condition plate [AIAA PAEIE 78-152] A78-20707 478-20906 An analysis method foe the viscous flow over Calculation of the Laval-nozzle flow by a modified circulation-controlled airfoils Laz-Rendroff method of second-order accuracy [4144 FAEEF 78-157] 478-20710 478-20970 Approximate wind-tunnel sunlation of the dynamics Effect of nozzle shape on characteristics of of a system composed cf a bcdy with a trailing three-dimensional subsonic and supersonic flows cable 478-21093 A78-20902 A study of the inviscid flow about conically Two-dimensicnal separated wake modeling and its cambered delta wings use to predict Banana section lift coefficient [AIAA EAPEB 78-58] A78-22561 [AIAA EAEEE 78-156] 478-22590 IOBOSPBBBIC COBPOSItlOB 4n aerofoil with control surface in incompressible Simulation of the flight conditions in the viscons flow ionosphere 478-23050 A78-20915 A nnaerical study of incompressible viscous flow IPAD around airfoils Feasibility study of an Integrated Prograa for H78-16996 Aerospace vehicle Design (IPAD). Volume 5: IBDICJTIBG IHSTBDBB8TS Catalog of IPAD technical program elements Application of light-emitting diodes /LEDs/ in [BASA-CB-132395] B78-16015 aircraft analog indicatcrs ITERATIVE SOIDTIOH 478-23059 The analysis of wing-body combinations at moderate IHDOSTBIiL PliSTS angles cf attack DynaBic Bodel of a system of scientific research [AIAA PAPEE 78-62] A78-20663 and industrial plants A split-recoupled-semidirect computational 478-22615 technigue applied to transonic flow over lifting IBBBTIAL BAVIGATIOB airfoils Airborne navigation systems [AIAA EAPEE 78-11] A78-22E53 478-22317

»-23 JABHIBG SUBJECT IFDEI

A solution to the direct problem of an open Investigation of TTOI upwash flows formed by two propeller using the streamline curvature method impinging jets [AIAA PAPEB 78-310] A78-21011 [AD-A017805] H78-17025 Successive-approximation calculation of a steady JBT LIE! subsonic gas flov about an airfoil lattice Minimum induced drag configurations with jet 478-21085 interaction [BASA-CB-155929] S78-17002 JET BOZZIBS Becent advances concerning an understanding of JAHBIBG sound transmission through engine nozzles and jets Airborne electronic warfare in the modern military [DG1B EAPEB 77-0118] A78-21137 force JET PBOPDLSIOH [AIAA ESPEB 78-321] A78-2

4-2" SOBOECT IHDEX BAGBETOBTDBODIBABIC GEBEB1TOBS

LIFE CTCtE COSTS LOAD DISTBIBOTIOI (FOBCBS) Design to cost/life cycle costing; Proceedings of Distributed load aircraft concepts the Conference, Washington, E.C., Bovember [AIAA FAPEB 78-100] A78-22573 16-18. 1977 LOADS (FOBCES) 178-21838 Stability of helicopter slang loads Development of cost estimating relationships for [ ABL/AEBO-BOTE-361 ] B78-16010 aircraft jet core-engine overhaul ccsts LOGICAL ELEHEITS [AD-AOU7667] B78-17C67 Initial collision avoidance algorithms fcr the LIFT beacon-based collision avoidance system Subsonic vortex-flew design stud; for slender tiings [AD-A017250] B78-16031 [AIAA PAPEE 78-151] A78-20708 LOGISTICS B1BAGEBBBT Approximate method of calculating the lifting An investigation into the nature of aircraft force and tie longitudinal moment cf an airfoil supportability in the CILC environment section at lov velocities with allowance for [AD-A00.7226] B78-15991 viscosity An evaluation of the capability of the logistics A78-208a9 composite model to project the monthly aircraft Determination of airfoil lift from pressure sortie effectiveness of an F-15 wing measurement at the test secticu vails in a [AD-A017227] F78-1S993 subsonic wind-tunnel LOIGITDDIBIL STABILITY A78-20973 Approximate method of calculating the lifting Two-dimensional separated take modeling and its force and the longitudinal moment of an airfoil use to predict maximum section lift coefficient section at low velocities with allowance for [AIAA PAPEB 78-156] A78-22590 viscosity The significance of wing end configuration in A78-20819 airfoil design fcr civil aviaticn aircraft Longitudinal aerodynamic characteristics at Hach [DG1B PAPES 77-030] A78-21121 0.60 to 2.86 of a fighter configuration with LIFT AOGBEBTATIOB strut traced wing Aircraft performance improvement through [BASA-TP-1102] B78-16000 retrofitting of singlets Influence of gust modelling on the identification [DG1B PAPEB 77-031] A78-24122 of the derivatives of the longitudinal motion of LIFT PAHS an aircraft Cold-air performance of a tip turtine designed to [BAE-HE-TBAHS-194Q] 878-17071 drive a lift fan. 3: Effect of simulated fan Aircraft compensator design methods leakage en turbine performance [AD-A017811] B78-17073 [NASA-TF-1109] N78-16001 LOB ASPECT BATIO SIBGS LIFTI1G BODIES Three-dimensional hypersonic gas flow past a thin Reliable lifting surface solutions for unsteady flow wing TAIAA PAFEE 78-228] A78-20757 A78-20795 neasurements cf noise produced by flew past Effect of the thickness of profile and trailing lifting surfaces edge on the flow field and the aerodynamic [AIAA PSPEB 78-239] A78-20762 characteristics of a low-aspect-ratio delta wing Approiimate method cf calculating subsonic at B = 3 compressible flews past a lifting wing profile A78-20919 A78-20883 Calculation of nonlinear aerodynamic A split-recoupled-senidirect computational characteristics of wing of complex planfcrm technigue applied to transonic flow over lifting allowing for nose vortex sheet airfoils S78-22359 [AIAA PiPEE 78-11] A78-22553 LOR DEBSITI FLOS Special areas of gas dynamics: Sonic, hypersonic. Calculation of the flow of a rarefied gas past a lifting surfaces, wave propagation German book (late of infinite span 178-22937 A78-20657 LIGHT 1IBCBAFT LOR LEVEL TDBBOTEBCE Boise transmission into a light aircraft An investigation into the effects of shear on the [AIAA PAPEB 78-197] A78-20739 flow past bluff bodies Lateral stability of a light aircraft during landing [AIAA PAPEB 78-331] A78-21025 A78-21020 The low-level Bind Shear Alert Program Flight on 0.33 horsepower - The Gossamer Condor A78-21316 [AIAA PAPEB 78-308] A78-2K009 LOi SPEED Conceptual design cf single turbofan engine Approximate method of calculating the lifting powered light aircraft force and the longitudinal moment of an airfoil [KASA-CB-151972] H78-16C15 section at low velocities with allowance for LIGHT EBITTIBG DIODES viscosity Application of light-emitting diodes /LEDs/ in A78-20819 aircraft analog indicatcrs An analytical model for the study of highly A78-23059 separated flow on low speed airfoils LIGHTBISG B78-16995 An investigation of lightning damage to LOR SPEED RIBD TOBBBIS nonmetallic composite aircraft materials and The low-speed air tunnel of the Institute of associated protective systems Hydromechanics at the Oniversity of Karlsruhe B78-17292 A78-23297 LIBEAB SISTEBS Low speed test of a high-bypass-ratio propulsion Rev fregaency domain methcds for system system with an asymmetric inlet designed for a identification tilt-nacelle v/STOL airplane A78-23883 [BASA-CB-152072] B78-17062 Optimal ccntrols fcr an advanced torbofan engine LOBBICATIOi SISTBHS A78-23893 Twenty year evolution of the BB2/BB21 series of Robustness of linear guadratic state feedback small turbcjet engines designs in the presence of system uncertainty [SAE PAPEB 770998] A78-23833 application tc Augmentor ling Jet STOL Research Aircraft flare control autopilot design M A78-23917 LIBE4B VIBBATIOg BACH COBBS Effects of structural non-linearities on aircraft The location of the ground focus line produced by vibraticn and flutter a supersonic aircraft [AGABD-B-665] B78-17076 A78-23H57 LIQUID HTDBOGBH BAGBETOHTDBODTBABIC GBBEBATOBS The application of dual fuel /JF-LH2/ fcr Power conditioning systems for high-power, hypersonic craise vehicles airborne, pulsed applications fAIAA PAFEE 78-119] J78-20705 A78-23U12

A-25 HAGHiTOBETEBS SUBJECT IHDBI

HAGHFTOBETBBS BETAI FATIGUE Aircraft attitude measurement using a vector Development of random fatigue data for adhesively magnetometer bonded and weldbonded structures subjected to [NASA-CB-155565] N78-17050 dynamic excitation aircraft structures BAIBTAIBABIIITY [ASBE PAPEE 77-SA/BAT-1] A78-23373 •New look1 in assurance technology - 'The Hornet1 The strength of structures and the applications of reliability and naintainability of P-18 the fracture mechanics [AIAA PAPEE 78-323] A78-21017 A78-2357II An investigation into the natnre of aircraft BETAI FIB1BS supportability in the CIIC environment Friction and wear of sintered fibermetal abradable [AD-A017226] H78-15991 seal materials HAIHTB8AHCE A78-23151 "*n assessment cf relevant decision making factors BETA! SHEETS for organic versos contract maintenance options Fatigue of ABg6B sheet with Sprut 5B and 7AK on OSAF flight simulators coatings in the linear and plane states of [AD-A01I7136] S78-16070 stress under high-frequency loads HAH OPERATED FBOPDLSICI S1STEBS A78-22108 Flight on 0.33 horsepower - The Gossamer Condor Spectrum crack growth in adhesively bonded structure [AIAA FAPIB 78-3C8] A78-21009 [ASBE FAPEE 77-HA/BAT-7] A78-23372 BINAGEBEST BETBODS BETAI-BETAL BOIDIHG Design to cost/life cycle costing; Proceedings of Development of random fatigue data for adhesively the Conference, Washington, D.C., November bonded and weldbcnded structures subjected to 16-18, 1977 dynamic excitation aircraft structures A78-21838 [ASBE PAPEB 77-BA/BAT-1] A78-23373 BANAGEBEBT PLASBIBG BETEOEOLOGICAL PAEABETEES Terminal area forecast 1978-1988 Prediction of the ascending speeds of gliders in [AD-AOU6543] B78-16027 thermal convection over a plain BANEOVEEABIIITY A78-23398 Configuration development cf a supersonic cruise BETEOEOIOGICA1 SATELLITES strike-fighter Automated meteorological data from commercial [AIAA PAPEE 78-118] A78-22E87 aircraft via satellite: Present experience and BANDALS future implications An analysis cf user acceptance and perceived [BASA-TB-73750] 1178-17558 usability of C-111A job guides BICBOFBOIES f AD-A04711H] B78-15992 Method of fan sound mode structure determination HA8KIT BESEABCB computer program user's manual: Hicrophone Future development cf commercial aircraft: location program Technological challenge - Econcmc constraints [SASA-CE-13529«] S78-17065 [DGIB PAPEE 77-OC5] A78-21H02 BICBOPBOCESSOBS BATEBIALS SCIEBCE Investigation of new techniques for aircraft Hear studies on aircraft brake materials navigation using the omega navigation A78-23H33 [HASA-CE-115303] S78-17C37 BATHEHATICAL BODEIS BICBOIAVE 1A1DIMG SISTEBS Construction of a mathematical model of a jet navigation procedure - Present systems and engine for analyzing transient flows development trends A78-20971 [DG1B PAPEE 77-018] A78-21111 Dynamic model cf a system of scientific research The technical potential of instrument landing and industrial plants systems in the present and in the future A78-22615 [DGIB EAPEB 77-019] A78-21412 Tie experimental determination of the parameters BTDAIB COI1ISIOIS of a mathematical model of an aircraft passenger The collision risk compartment as a control plant witb respect to A78-22851 air temperature BIlITiBI AIB FACILITIES A78-22652 Rind tunnel model study of the hot exhaust plume The application of the Eouth apprcximaticn method from the Compressor Research Facility at to turbofan engine models Uright-Patterson Air Force Base, Ohio A78-23891 [AD-A017205] B78-16072 Research en the flutter of axial-turbomachine The problem of technology transfer: Seal or blading imagined [AD-A017086] H78-16021 [AD-A012961] B78-17913 Characterization of nonGaussian atmospheric BILITABT AIBCBAFT turbulence for prediction of aircraft response Research needs for O.S. Army aircraft propulsion statistics [AIAA PAPEE 78-15] 878-22558 [NASA-CB-2913] H78-16011 Application of laminar flow control to large A critique of aircraft airframe cost models subsonic military transport airplanes [AD-A017181] N78-16018 [AIAA PAPEE 78-95] A78-22571 Unsteady aerodynamic modeling and active Statistical review of counting accelerometer data aeroelastic control for Havy and Marine fleet aircraft from 1 N78-16061 January 1962 to 30 June 1977 BATBICES (BATBEBATICS) [AD-A017857] 878-17015 Organization of a programmed matrix-operation BILITABI AVIA1IQ1 system in an airborne digital computer Future aviation turbine fuels A78-21585 [AIAA PAPEE 78-268] A78-20781 BAXIBDH 11KBIIHOOD BSTIHATIS BILITABY BEtlCOPtEBS New frequency domain methods for system Bechanism of wear in helicopter hydraulic systems identification A78-23139 A78-23883 Toxicologic gas evaluation of the utility tactical BECBAHICAI DBIVES transport aircraft system (OH-60) A clutch for V/STO1 [AD-A017801] H78-17016 (SAE PAEFS 770989] A78-23826 Technical evaluation report on the Flight BESOBBTEOEOLOGT Mechanics Panel Symposium on rotorcraft Design A severe downslope windstorm and aircraft [AGAEE-AB-111] F78-17019 turbulence event induced by a mcuntain wave BI1ITABY TICBB010GT A78-21356 Air Force research and development activities BETA1 COATINGS related to aircraft fire protection Coatings fcr fretting prevention ' [AIAA PAPF.E 78-269] A78-20782 A78-23111 Testing a modern strike aircraft navigation system A78-22852

A-26 SUBJECT ISDEZ BOISE BBDOCTIOH

Arny OTTfiS program UH-60A helicopter for General aviation energy-conservation research Dtility Tactical Transport Aircraft System programs at BBSs-Lewis Research Center [SSE EAPIB 770952] A78-23803 [BASA-TH-73881] H78-17060 The impact of emerging technologies on tactical Bibliography of lewis Besearch Center technical V/ST01 airplane design and otility contributions announced in 1976 [SAE SASIB 770985] A78-2382U [BASA-1B-136601 H78-17921 Variable speed constant frequency /VSCF/ aircraft BAVIGATIOB AIDS electrical power Airborne navigation systems [SAE PAEIB 771002] A78-23836 A78-223117 Airborne electronic warfare in the modern military navigation procedure - Present systems and force development trends [AIAA PAPEB 78-324] A7S-21018 [BG1B FAPEB 77-018] A78-2HH11 BIBICOBPOTEBS Evaluation of STOL navigation avionics Bodifications to FALSTAIF that were required for [BASA-CB-155566] B78-17051 operation en a 16 K PDP-£e minicomputer IAVICATIOI IBSTBOBEBTS [LTR-ST-899J H78-16392 Testing a modern strike aircraft navigation system BIHIBDB DBAG A78-22852 A formulation of the problem of the minimum-drag BA7I ving VST01 - can Bavy needs be met A78-20E67 [AIAA tAPEE 78-322] A78-2Q016 Binimum induced drag configurations vith jet BEAB IAKES interaction Bearrangement of the flow between a pair of IHASA-CB-155929] H78-17C02 bodies, one of which is situated in tne ether's BISSIIE BODIES wake, in supersonic flow Normal-force and pitching-monent coefficients of 478-20913 wing-body ccibinaticns at very high angles of An experimental study of sound diffraction at an attack airfoil trailing edge [AIAA PAPEE 78-63] A78-20664 A78-232P7 BISSIIE STBDCTOBES An improved method of calculating the tip vortex External interaction of the nuclear EBP with geometry for hovering rotors aircraft and missiles H76-15997 A78-21989 RICKEL ALLOTS BISSIIB TESTS Friction and wear of sintered fibermetal afcradable Reynolds number criticality in dynamic tests seal materials CAIAA FAFEB 78-166] 878-20718 A78-231S1 BODES BLTBOGEB OXIDES Hethod of fan sound mode structure deternination The tropospheric and stratospheric composition [HASA-CB-135293] N78-17061 perturbed by BO/x/ emissions of high-altitude Hethod of fan sound mode structure determnation aircraft computer prcgran user's manual: nodal A78-21003 calculation program Optical measurements of BO and NO sab 2 in the [NASA-CB-135295] N78-17066 exhaust of an P101-GE-100 engine at simulated BOBOPLABES altitudes Conceptual design of single turbofan engine [AD-AOQ7882] B78-17068 powered light aircraft NOISE GEIEBiTOBS [NASA-CB-151972] 878-16045 Measurements of noise produced by flow fast BOBOSOLSE ABTEB1AS lifting surfaces Development of a discrete address beaccn system [AIAA FAPEE 78-239] A78-20762 testing nonoFUlse beacon antennas Semiempirical theory of the generation of discrete [AD-A008217] B78-17C36 tones by a supersonic underexpanded jet flowing BOHTE CABIO BETBOD over an obstacle Ose of a fast Fourier transformation and the Honte A78-21133 Carlo method to calculate repeatibilitj of load Becent advances concerning an understanding of and fatigue damage of aircraft structural sound transmission through engine nozzles and jets elements under vibration excited ty external [DGLB PAPEB 77-008] A78-2U137 stationary random leads BOISE BBASDBEBEBT A78-20932 Beasurements of noise produced by flew past BOTIOB PERCBPTIOB lifting surfaces An evaluation of tie fidelity of motion simulators [AIAA PAPEB 78-239] A78-20762 using a model of human dynamic orientation Airframe noise, the lower noise limit for aircraft [AD-A047120] N78-16C71 [DG1B IAPEE 77-052] A78-2<11|1H HOTIOB SIBOIATOBS BOISE POLLOTIOB An evaluation of the fidelity of motion simulators Physical analysis of the impulsive aspects of using a model of human dynamic orientation helicopter noise [AD-A017120] N78-16071 [AD-J03971S] R78-16059 BDLTIBBGIBB TBBICIES BOISE PBOPSG1TIOB Analysis of spread nulti-jet VTOL aircraft in hover Noise transmission into a light aircraft [BASA-CE-155582] H78-160H6 [AIAS FAPEB 78-197] A78-20739 HOISE BEDOCIIOH N Noise transmission into a light aircraft [AIAA EAPEE 78-197] A78-20739 •ISA PBOGBABS EBF noise suppression and aerodynamic penalties & review of NASA's propulsion programs for civil Externally Blown Flaps aviation [AIAA EAPEB 78-200] A78-20763 [AIAA PAPEB 78-13] A78-20651 Big fans for the airlines Advanced supersonic transport propulsion sy stems A78-22269 CSAE PAPEB 771010] A78-23842 Advanced quiet propulsion for general aviation Technology readiness fcr an SST [DGLE PAPEE 77-000] A78-20033 [AIAA PAPEB 78-356] A78-21031 Beducing aircraft noise through retrofitting The challenge of advanced fuel-conservative [DGIB PAPEE 77-017] A78-20036 aircraft - A manufacturer's view Localization and shielding of noise sources [AIAA PAPEB 78-362] A78-21C30 generated by the interaction of free jets with Conceptual design cf single tnrbofan engine flat surfaces powered light aircraft [DGLB FAPBF 77-009] A78-20038 [NASA-CB-151972] B78-16015 Bethod of fan sound mode structure determination A review of BASA's propulsion programs for aviation [BASA-C8-135293] N78-17064 [BASA-TB-73831 ] S78-16C55

A-27 HOHDESTBOCTIVB TESTS SUBJECT INDEX

BONDESTBOCTHE TESTS HOCLEAB BADIATIOB Holographic inspection of jet engine composite fan External interaction of the nuclear EBP with tladet- aircraft and missiles [SAE PAFEB 770975] A78-23819 478-21989 HOHIIBBAB PB06BABBIHG BOBEBICAL ABALTSIS Solution of transient optimization problems by Numerical solution for some problems concerning using an algorithm based on nonlinear programming unsteady motion of airfoils A78-23909 B78-15995 NONL.IBEABITT A numerical study of incompressible viscous flew Significance of structural nonlinearities from the around airfoils structural dynamics and aeroelasticity point of H78-16996 view HDBEBICAL F10S fISDALIZATIOB H78-17005 Calculation of the flow past a fuselage of Effects of structural ncn-linearities on aircraft arbitrary configuration at low velocities vibration and flutter 478-20615 [AGABD-B-665] S78-17C76 An analytical model for the study of highly H01STABILIZED OSCILLATION separated flow en lew speed airfoils Theory of two fregaency ranges of unstable H78-16995 oscillations cf turbulent combustion in a jet-engine chamber. I - Formulation of the stability problem, the characteristic eguation J78-21253 OFF-OB COiTBOl HOSE CODES Solution of transient optimization problems by Further studies of aerodynamic loads at spin entry using an algorithm based on nonlinear programming [AD-AOU7952] S78-17028 A78-23909 NOZZLE DESJGB OGIVES A method for the construction of floti nozzles and Experimental investigation of support interference mnd tunnel contraction sections on an ogive cylinder at high incidence A78-21635 [AIA» EAPEB 78-165] 478-20717 Experimental investigation of asymmetric Laval OBEGA BAVIGJTIOH SISTER nozzles Airborne navigation systems A78-22361 A78-22317 Development cf Ion pressure ratio vectoring Investigation of new techniques for aircraft nozzles for 1/STOL aircraft navigation using the omega navigation [SAE PAPIB 770988] A78-23825 [B4SA-CB-11S303] B78-17C37 HOZZLE FLOS OPTICAI COBBDHICATIOB The prediction of the performance of Ion A-7 ALOFT economic analysis and EBI-EBE test results pressure-ratio thrust-augmenter ejectors B78-16816 [AIA? PAPEE 78-115] A78-2070« OPTICAI BEASOBEBBNT The basic characteristics of the variation of Optical measurements of BO and BC sub 2 in the aerodynamic parameters in the transition region exhaust of an F101-GE-100 engine at simulated at hypersonic flow velocities altitudes &78-20900 [AD-A017882] B78-17068 Velocity profiles in the Laval nozzle throat for OPTIC4L iAVEGDIDES uniform compressible swirling flov Glass-fiber data bus systems for signal 478-20905 transmission on board Characteristics of the jet acceleration of a flow A78-21976 to hyperscnic speeds OPTIB1L COBTB01 A78-20953 Filtered sequential regression parameter Calculation of the Laval-nozzle floti by a modified identification applied to a gas turbine engine Iax-»endroff method of second-order accuracy model A78-20970 A78-23879 Experimental investigation of the characteristics New frequency domain methods for system of snail-sized nozzles identification A78-21090 A78-23883 Effect of nozzle shape on characteristics of Optimal controls for an advanced tnrbcfan engine three-dimensional subsonic and supersonic flows S78-23893 A78-21C93 Singular perturbation analysis of optimal flight Computation of the fcase pressure in ejector profiles for transport aircraft nozzles cf different length with zero A78-23901 coefficient cf ejection Solution of transient optimization problems by A78-21098 using an algorithm based on nonlinear programming A method for the ccnstruction of flow nozzles and A78-23909 wind tunnel contraction sections OPTIBIZATIOB 178-21635 Belating take off gross weight and mission The start-up of a gas turbine engine usug requirements for geometrically optimized aircraft compressed air tangentially fed onto tie blades [AIAA P4PEE 78-98] A78-20681 of the basic turtine Optimum schedule for replacement of aircraft 178-2111(9 system parts under incomplete information on Investigation of the inclination of nozzle blades their reliability on the alternating stress level in working A78-20879 turbine Hades Taking structural and technological constraints A78-2Q273 into account in the design of maximum-stiffness NOZZLE GECBBTBT load-bearing structures Effect of nozzle shape on characteristics of A78-20880 three-dimensional subsonic and supersonic flows Bational parameters of reinforced panels operating A78-21C93 under conditions of unsteady heating NOZZ1E TBBDST COEFPICI1BTS A78-20881 Thrust characteristics of thrust vector control Aerodynamic optimization and analysis as part of systems with bloting injection of chemically the computer-aided design process nonreactive gases [AIAA PAPEB 78-97] A78-22E72 478-21251) Computational wing optimization and wind tunnel NOZZLES test of semi-span model Variable thiust nozzle for quiet torbcfan engine [AIAA PAPEB 78-102] A78-22575 and metbcd cf operating same Determination of the longitudinal lines of an fNfSA-CASE-LEW-12317-1] N78-17C55 aircraft fuselage by the special-contour method A78-2261C

4-28 SUBJECT IHDII POSITI01 (LOCATIOS)

Basic considerations concerning the possibilities i solution to the direct problem of an open of sing families in civil aviation propeller using the streauline curvature method [DG1B PAPEE 77-029] J78-21120 [Alii liPEB 78-310] i78-2llC11 Applications cf structural optimization for A new airfoil family for rotor blades strength and aercelastic design requirements [OSEE1. TP BO. 1977-113] A78-2I4163 [AGABD-B-66q] B78-17018 Assessment of the performance of an active ATCBES OBBITAL BECBJ8ICS mode for beacon collision avoidance Sigalation of the flight conditions in tie [AD-A017670] H78-16032 ionosphere Investigation of new techniques for aircraft A78-20915 navigation using the omega navigation OSCIlliTIJG FIOI [HASA-CH-145303] S78-17037 Effect of blade loading and thickness on the Including fleet usage variability in reliability aerodynamics cf oscillating cascades analyses for both safety and economic limit [ilii PJEEE 78-257] 878-20756 [iD-AOQ771

A-29 POTEBTIAL FL01 SUBJECT IHDEX

POTEBTIAL PICS PBESSOBI2ED CABIBS Development and test of an inlet and dnct to Fatigue crack growth in a pressure-fuselage panel provide airflow for a meg boundary layer A78-22C1I9 control system PBESTBESSIIG [AIAA PAPEB 78-1U1] A78-20701 Determination of the stress-strain state in the ? combined potential and viscous flow solution for end region of a stress-raiser rib v/STOl engine inlets J78-20917 [AIAA PAPF.B 78-1112] A78-20702 Upgrading the carrying capacity of stretched The prediction cf two-dimensional airfoil stall panels with a stress-raiser rib by the technique progression of strain-compensating holes [AIAA PAPEB 78-155] A78-20709 S78-20918 fn analysis method for the viscous flow ever PBISBS circulaticn-ccntrclled airfoils Elastic deformations of rapidly-rotating prismatic [AHA PAPES 78-157] A78-20710 mirrors High-freguency approximation for a nonlifting thin A78-2137P airfoil in subsonic flow PBOB1EB SOLVIHG [AIAA PAPEB 78-226] A78-20755 Expansion of flight simulator capability for study Calculation of the flow past a fuselage cf and solution of aircraft directional control arbitrary configuraticn at lo» velocities problems on runways, appendixes S78-20815 [SASA-CB-1H5281] S78-16066 Perturbing forces in the hydrodvnamic interaction PBOCDBEBEBT POLICY of thin-tlade cascades in a potential flow The role of engineering in the flight equipment A78-21219 purchasing process A split-recoupled-semidirect conputational [HASA-CB-156839] S78-17915 technigue applied to traisonic flow over lifting PBODOCTIOB EBGIBEBBIB6 airfoils Dynamic model of a system of scientific research [AIAA PAPEE 78-11] A78-22553 and industrial plants Method of calculating the compressible flew round A78-226I45 an aerofoil cr a cascade up to the shockfree Ceramics in gas turbine: Powder and process transonic range characterization A78-2327U [SASA-TH-73875] B78-17C59 Theoretical aspects of drcnedaryfoil PBOPELLEB BLADES [AD-?01|7150] H78-16023 An experimental study of three-dimensional Drag on an oscillating airfoil in a fluctuating characteristics of propeller wakes under free streau stalling conditions S78-16991 A78-21632 POiDEB (PABTICLES) A solution to the direct problem of an open Ceramics in gas turbine: Powder and process propeller using the streamline curvature method characterization [AIAA EAPEE 78-310] A78-2I4011 [NASA-TB-73875] H78-17C59 Quiet propeller/rotor concept evaluation of POSEB COBDITIOHIH6 the DH-1 helicopter Power conditioning systems for high-power, [AD-AOII7297] B78-160U7 airborne, pulsed applications PBOPELLEB DBIVE A78-23II12 The flow about a slender propeller-driven body in POWEB SOPP1Y CIBCHITS a temperature stratified fluid Variable speed constant freguency /VSCf/ aircraft [AIAA FAPEE 78-209] A78-207U6 electrical pcwer The integrated shielded propeller as a drive [SAE PAPEB 771002] A78-23836 system for general aviation aircraft PBAHETL-HEYEE BXPJBSICB [DGLB PAPEB 77-0115] A78-2I1430 Interaction of a shcck wave with an entrcpy layer PBOPELLEB SLIPS1BEABS A78-20886 Flowfield and pressure field of a model propeller PBEDICTIOB ABAIYS1S TICBBIQOES A78-211151 An analysis of the aircraft trailing vortej system PBOPBLLEBS [AIAA PAPEB 78-312] A78-24013 Design and analysis of propellers for low Beynolds PBEFLIGHT OPEBATICHS number application to mni-EPV's Arrival inspections/pre-operational inspections [SAE PAPEB 77C999] A78-2383q (aviation nateriel) PBOP01SIOB SISTEB COBPIGOBATIOBS [AD-A047260] B78-16376 Research needs for O.S. Army aircraft propulsion PBBSSDBB DIS1BIEOTIOH [AIAA EAPEE 78-«5] A78-22558 Pressure distribution over sharp-nosed cones Status report on the Advancing Blade Concept /ABC/ situated at angles cf attack from 0 tc 10 technology demonstrator program degrees in supersonic flew [SAE PAPEB 770950] A78-23805 A78-20889 Impact of engine cycle parameters on V/STOL Type A Experimental investigation of asymmetric Laval configuration and commonality nozzles [SAE PAPEB 770980] A78-23821 A78-22361 Special problems in the development of the Computaticnal transonic flew abcot realistic propulsion system for an over-tbe-wing engine aircraft configurations configuration [AIAA PAPEB 78-1014] A78-22576 [DGIB IAPEB 77-OU6] A78-2UII35 Flowfield and pressure field of a model propeller Low speed test of a bigh-bypass-ratio propulsion A78-2HQ51 system with an asymmetric inlet designed for a Unsteady pressure distribution measurements at two tilt-nacelle V/STOL airplane trapezoidal wings with unit aspect ratio [BASA-CB-152072] S78-17062 B78-17020 PBOPDLSIOB SISTEB PEBFOBHAICB A numerical method for calculating the unsteady A review of BASA's propulsion programs for civil aarodynaiic pressure distribution on aviation harmonically oscillating wings with control [AIAA EAPEB 78-113] 878-20651 surfaces in subsonic flot. Theory and results Development of the propulsion simulator - A test for compressible flew, part 2 tool applicable to V/STOL configurations [ESA-TT-Q30] tnS-17029 [SAE BASES 77098*3 A78-23823 PBESSOBE EFFECTS Concorde AIDS - Powerplant applications A study on the mecbanisn cf ccmpresscr surge due Airborne Integrated Data Systems to inlet pressure disturbances [SAE PAPEB 770995] A78-23831 [AIAA PAPEB 78-2U6] A78-20769 Advanced supersonic transport propulsion systems PBESSDBE BEiSOBEBEBTS [SAE PAPEB 771010] A78-238H2 Detemination of airfoil lift from pressure Study of metallic structural design concepts for measurement at the test section walls in a an arrow wing supersonic cruise configuration subsonic wind-tunnel [BASA-CB-2713] S78-160B3 A78-20973

1-30 SUBJECT IBDEI BEHOTE BEGIOBS

Preliminary study cf propulsion systems and BADIO BEACOBS airplane wing paraneters for a OS Navy subsonic Initial collision avoidance algorithms for the v/STOL aircraft beacon-based collision avoidance system [HASA-TH-73652] N78-17011 [AD-AOQ725

i-31 BBBOTELY PILOTED VEHICLES SUBJECT IBDBI

BBBOTELT PILOTED VEHICLES Technical evaluation report on the Flight Design and analysis of propellers for low Beynolds Mechanics Panel Symposium on rotorcraft Cesign number application tc mini-BPV's [AGABD-AB-114] B78-17C49 [SAE PAFEB 770999] S78-23834 BOTABT 1IBGS Technical evaluation report on the Avionics Coatings for fretting prevention Panel/Guidance and Ccutrcl Panel Jcint Sjnposi.no A78-23441 on Avionics/Guidance and Control for Bemotely A new airfoil family for rotor blades Piloted Vehicles (BFVs) [OBEBA, IP BO. 1977-113] A78-24463 [AGABD-AB-113] B78-17075 An improved method of calculating the tip vortex BEPOBT GEBBBATOBS geometry for hovering rotors GEHPAK: An arbitrary aircraft geometry generator B78-15997 [BASB-TP-1022] B78-16042 Two-dimensional wind tunnel test of an oscillating BEPOBTS rotor airfoil, volume 1 Project SCOID [BASA-CB-2914] B78-16003 [AD-A047076] B78-16056 Two-dimensional wind tunnel test of an oscillating BESEABCH AIBCBAFT rotor airfoil, volume 2 tabulated test results Aerodynamic heating to the hypersonic research [BASA-CB-2915] N78-16S98 aircraft, X-24C Aerospatiale is ready to develop a convertiplane CAIAA PAPEF 78-37] A78-20647 with tethering rotors Stndy of beat sink thermal protection systems for [BASA-TB-75038] B78-17042 hypersonic research aircraft BOTATISG GBBEB1TOBS fAIAA PAPEB 78-38] A78-206

A-32 SUBJECT IBDEI SPACE BiBOFACTOBIBG

Transient expansion of the components of an air Hypersonic flov past a conical ving vith detached seal on a gas turbine disc shock vave at the leading edges [SAE PAIEB 770971] A78-23818 A78-22078 Feasibility stndy of negative lift circumferential Special areas of gas dynamics: Sonic, hypersonic, type seal for helicopter transmissions lifting surfaces, vave propagation German book [BASA-CB-135302] H78-17390 A78-22S37 SELECTIVE DISSEBIIATIOf OF IBFOBHJTIOB A least sguare finite element technique for The problem of technology transfer: Real or transonic flov vith shock imagined [AIAA IAPEB 78-328] A78-21022 [AD-A012961] B78-17913 SHOBT BAOL AIBCBAFI SEBISPAB BODBLS Preliminary QCSEE program - Test results Cuiet Computational ving optimization and vind tunnel Clean Short-haul Experimental Engine test of seni-span model [SAE PAPEB 771008] A78-238qO [AIAA PAPEf 78-102] A78-22575 SHOBT TAKEOFF AIBCBAFT snsmtiTi EBF noise suppression and aerodynamic penalties Sensitivity analysis of optimal flight trajectories Externally Elovn Flaps B78-160111 [AIAA PAPEB 78-210] A78-20763 SE1SOBS Airports for short takeoff and landing Sensor failure detection using analytical redundancy A78-23171 A78-23862 Bobustness of linear guadratic state feedback SBPABATED FlOf designs in the presence of system uncertainty Steady and unsteady transonic flow application to Augmentor Wing Jet STOL [AIAA PAPEE 78-160] 878-20713 Besearch Aircraft flare control autopilot design StDdy of supersonic separated flov past conical A78-23917 wings and inside a right angle Specifications for IDABST "softvare for short A78-22C79 takeoff aircraft avionics Tvo-dinensional separated vake modeling and its [AD-A017163] H78-16019 ose to predict maximum section lift coefficient Evaluation of STOL navigation avionics [AIAJ SAFES 78-156] A78-22590 [BiSA-CE-155566] H78-17051 A study of the influence of slits on the SIGBJL TBABSBISSIOB effectiveness of King mechanization and controls Glass-fiber data bos systems for signal in separated flov transmission on board A78-226I17 A78-21976 Rings vitb controlled separation SIGBATDBE ABALJSIS CDGLB PAPEB 77-028] A78-21119 On some singular acoustic signatures observed in An analytical nodel for the stndy of highly the cockpit of a tvin engined jet aircraft separated flcv en lev speed airfoils [AIAA tAPEE 78-212] A78-20765 B78-16995 SIIGLE STAGE TO OBBIT VEHICLES Effect of separation bubbles on the lift of King Eamjet propulsion for single-stage-to-orbit vehicles profiles [SAI PAEEB 771011] S78-23E13 S78-17C12 SKIB (STBDCTDBAL BEHBEB) SBPAEATOBS Application of skin technology to turbine Hades Advanced scavenge systems for an integrated engine zero gravity manufacture inlet particle separator [AIAA PAPEE 78-285] A78-20792 [AD-A017872] H78-17C69 SLEBDEB BODIES SEQUENTIAL ABALISIS The flov about a slender propeller-driven body in Filtered seguential regression parameter a temperature stratified fluid identification applied tc a gas turbine engine [AIAA PAPEB 78-209] A78-20716 model Rake vortex measurements of bodies at high angle A78-23879 of attack SEBVOBECBABISBS [AIAA PAPEB 78-23] A78-2255S Research and development cf aircraft control Unsteady aerodynamic forces on harmonically actuation systems. The developient of a direct oscillating pointed circular conical shells vith drive fly-by-vire flight control system and small aperture angle evaluation of a force sharing fly-by-vire actuator H78-17007 [AD-A017283] N78-16065 SLESDBB IIBGS Preliminary design study cf an integrated tail Subsonic vortex-flov design stndy for slender vings rotor servo pover nodule [AIAA PAPEB 78-151] A78-207C8 [AD-AOI17678] H78-17C72 SBOKB JBA1EBBHT SHEAB FlOf Evaluation of the extended use of ferrocene for An investigation into the effects of shear on the test cell smoke abatement engine and flov past bluff todies environmental test results [AJAA PAPEE 78-331] J78-21025 [AD-A017659] B78-17079 SHEAB SfBESS SOIIC BOOBS Stresses and displacements due tc load transfer by The location of the ground focns line produced by fasteners in structural assemblies a supersonic aircraft A78-23575 A78-23157 A study of pull-through failures of mechanically SODBD PBESSOBB fastened joints Fatigue crack grovth in a pressure-fuselage panel [AD-A0171121 B78-16372 A78-22619 SHOCK iAVB IITBBACTIOB SOOBD TBAHSBISSIOI Interaction of a shock vave with an entropy layer Becent advances concerning an understanding of A78-20886 sound transmission through engine nozzles and jets SHOCK BATE PBOPIIES [DSLH PAPEE 77-018] A78-21137 Hypersonic gas flov past a flat delta ving SOOBD iAVBS A78-20966 Effects of acoustic and vortical disturbances on SHOCK IAVE PEOPAGATIOB the turbulent boundary layer at free-stream Bach Calculation of unsteady transonic flows using the number 0.5 integral eguation method [AD-A017921] B78-17C26 [AIAA PAPEB 78-13] A78-20632 SPACE BB5IBOBBEBT SIBOLJTIOB Large amplitude shock vave motion in tvo Simulation of the flight conditions in the dinensicnal transonic channel flcvs ionosphere [AIAA PAPEE 78-217] A78-20770 A78-20915 Tvo nev correlation dependencies for parameters of SPACE BABOFJCTDBIBG flov on a plane delta virg Application of skin technology to turbine blades A78-20933 zero gravity manufacture Entropy layer in tvo-dimensional flovs [AIAA PAPEE 78-285] A78-20792 hypersonic ideal gas flov behind shock vave A78-21132

»-33 SPACE SBUTTLE OBBITBBS SUBJECT IHDEI

SPACE SHUTTLE OBEITEBS STBESS A1ALISIS Analysis of heat transfer in a simulated Stress analysis study in cooled radial inflow wing-eleven cove in hypersonic flow turbine [AIAA PAPEB 78-40] A78-22556 [AIAA PAPEE 78-94] 478-22570 Flutter tests of the mated 747 shuttle Carrier Stress history simulation. Volume 2: A users Aircraft-Orbiter manual for a computer program to modify stress fSAF. PAPER 770971] 478-23816 history simulations crack propagation in SPACE SHUTTLES fighter aircraft 747 Shuttle Carrier Aircraft/Space Shuttle Orbiter [4D-A042785] B78-17044 mated ground vibration test - Data via transient An analysis of the rotor blade stresses of the excitation and fast Fourier transform analysis three stage compressor of the Ages Research fSAE PAPEE 770970] A78-23815 Center 11- by 11-foot transonic wind tunnel SPACICBAFT PBOPOtSIOI [SASA-CB-152083] B78-17C61 Ban3et propulsion for single-stage-to-orbit vehicles S1BBSS COSC111BA1IOB [SAE PAPER 771011] 478-23843 Determination of the stress-strain state in the SPAB1ISE ELOtlBG end region of a stress-raiser rib Rings with controlled separation A78-20917 [DGLB PAFSB 77-028] A78-24419 Stress-strain state cf simply-supported SPEED COHTBOL three-layer trapezoidal plates Constant speed generating systems for aircraft A78-21205 electric pcwer supply Spectrum crack growth in adhesively bonded structure [SAE PAPEB 771001] A78-23835 [ASHE EAPFB 77-SA/HAT-7] A78-23372 STATISTICS! AB4ITSIS Stresses and displacements due to load transfer by Statistical evaluation of the effect of a jet fasteners in structural assemblies reverser on the parameters of a turbofan engine A78-23575 in the direct thrust regime Investigation of the inclination of nozzle tlades S78-2U275 on the alternating stress level in working J study on the capacity of runway systems turbine blades 478-24374 A78-2P273 General aviation avionics statistics: 1974 STBESS CICLES [AD-A045209] N78-16050 The strength of structures and the applications of Statistical reviev of counting acceletometer data the fracture mechanics for Navy and Marine fleet aircraft from 1 A78-23574 January 1962 to 30 June 1977 STBIBGEBS [AD-A047857] H78-17C45 Determination of the stress-strain state in the STATOB BLADES end region of a stress-raiser rib Cold-air performance cf free-power turbine A78-20917 designed for 112-kilowatt automotive gas-turbine Upgrading the carrying capacity of stretched engine. 1: Design Statcr-vane-chord setting panels with a stress-raiser rib by the technique angle of 35 deg of strain-compensating holes FNASA-TE-1007] R78-16053 A78-20918 STEAD! FLOS STBDCTDBAL ABALISIS Steady and unsteady transonic flew Dse of the finite element method in fracture [AIAA P8PEF 78-160] A78-20713 mechanics A split-recoupled-semidirect computational [DGLB PAPEB 77-055] 478-24443 technique applied to transonic flow over lifting STBDCTOBAL DBSIGB airfoils Taking structural and technological constraints [AIAA PAPEE 78-11] A78-22553 into account in the design of maximum-stiffness Successive-approximation calculation of a steady load-bearing structures subsonic gas flow about an airfoil lattice A78-20880 478-24085 Bational parameters of reinforced panels operating Contributions to steady and unsteady aerodynamics under conditions of unsteady heating [DLB-FE-77-34] H78-17004 478-20881 STEEL STBOCTDBES Study of metallic structural design concepts for Fracture analysis of aerospace metals an arrow wing supersonic cruise configuration 478-22724 [HASA-CB-2743] S78-16043 STIFFHESS 8A1BII STBOCTORA1 EBGIBEEBIBG Taking structural and technological constraints Stresses and displacements due to load transfer by into account in the design of maximum-stiffness fasteners in structural assemblies load-bearing structures A78-23575 A78-20880 STBUCTOBA1 FAI1UBE STOCBASTIC PIOCESSES Development of random fatigue data for adhesively Optimum schedule for replacement of aircraft bonded and weldbonded structures subjected to system parts under inccnflete information on dynamic excitation aircraft structures their reliability [ASHE EAPEB 77-WA/BAT-1] A78-23373 A78-20879 STBDCTOBAI RELIABILITY STOBBS (HBTEOBOLOGT) Airworthiness criteria for aluminum alloy covering A severe downslcpe windstorm and aircraft with uniform corrosion damage turbulence event induced by a mountain wave 478-22737 A78-24356 STBDCTOBAI STABILITI STBAIB EBEBGT BE1HODS Upgrading the carrying capacity of stretched Taking structural and technological constraints panels with a stress-raiser rib by the technique into account in the design cf maximum-stiffness of strain-compensating holes load-bearing structures A78-20918 A78-20880 Rational arrangement of the structural and STBATIFIED FIOB load-bearing elements of the wing with allowance The flow about a slender propeller-driven body in for certain aerodynamic requirements a temperature stratified fluid 478-20984 [AIAA PAPEB 78-209] 478-20746 Concerning the relationship between element STBA10SPBEBE stability and system stability in wing-truss The tropospheric and stratospheric composition structure made from elastic and elasto-plastic perturbed by NO/i/ emssions of high-altitude materials aircraft 478-21971 478-21003 On some structure-turbulence interaction problems STBEABLIBIHG H78-15996 A solution to the direct problem of an cpen STBOCTOBAL STBAIB propeller using the streamline curvature method Fatigue crack growth in a pressure-fuselage panel [AIAA PAPFB 78-310] A78-24011 A78-22649

A-3«l SOBJICT IBM! SOPBBSOBIC TB1BSPOBTS

STBDCTOBAL VIBBATIOB SDPBBSOBIC COHBDSTIOB Effect of blade loading and thickness on the Internal performance predictions for Langley aerodynamics of oscillating cascades scramjet engine module [AIAS PAPZB 78-257] A78-20756 [BSSi-TB-X-71038] B78-17057 Taking into account tie effect of elasticity of SDPBBSOBIC COBBOStlOB BiBJET EBGIBBS the structure on the longitudinal short-period Toward serasJet aircraft progress in engine notion cf an aircraft development A78-20882 478-23121 717 Shuttle Carrier aircraft/Space Shnttle Orbiter SDPBBSOBIC CBOISE AIBCBAFT BBSBABCB mated ground vibration test - Data via transient Advanced supersonic transport propulsion systems excitation and fast Fonrier transform analysis [SAE PAPEB 771010] A78-23812 [SAE PAPEB 77097C] A78-23815 Technology readiness for an SST STBOCTOBH BEIGHT [AIAA EAPEB 78-356] A78-21031 Relating take off gross Height and mission Study of metallic structural design concepts for regnirenents for geometrically optimized aircraft an arrow wing supersonic cruise configuration [AIAA PJPF.B 78-98] A78-20681 [BASJ-CB-2713] B78-16013 The weight of fuel tanks in aircraft SDPEBSOBIC PLIGHT A78-22818 The effect of blunting the leading edge of a delta Plight testing an 8000 psi Lightveight Hydraulic wing on its aerodynamic characteristics daring Systeo supersonic flight [SAB FAPEB 771007] 478-23839 A78-20920 STBOTS SDPEBSOBIC FLOB An investigation of strut-wall intersection losses Application of the finite element method to the [UAA PAPEB 78-205] A78-20713 stability analysis of triangular plates in Longitudinal aerodynamic characteristics at Hach supersonic flow 0.6C to 2.86 of a fighter configuration with A78-20S66 strut braced wing A formulation of the problem of the minimum-drag fNASA-TE-1102] B78-16000 wing SUBSOBIC AIBCBAM A78-20867 Application of laminar flew contrcl to large Pressure distribution over sharp-nosed cones subsonic mlitary transport airplanes situated at angles of attack from 0 to 10 [AIAA PAPEB 78-95] A78-22571 degrees in supersonic flow SOBSOHIC FLOf A78-20889 A combined potential and viscous flow solution for Inviscid supersonic flow about a thin rectangular VSTOL engine inlets plate [AIJA PAPEB 78-112] J78-20702 A78-20906 Subsonic vortex-flew design study for slender wings Supersonic flow near a thin trapezoidal wing [SIAA PSPEB 78-1511] A78-207C8 A78-2C921 High-freguency approximation for a nonlifting thin Two new correlation dependencies for parameters of airfoil in subsonic flow flow en a plane delta wing [AIJA PAPEB 78-226] A78-20755 A78-20933 Approximate method of calculating subsonic Effect of the thickness of profile and trailing compressible flows past a lifting wing profile edge on the flow field and the aerodynamic S78-20883 characteristics of a low-aspect-ratio delta wing Effect of nozzle shape en characteristics of at H = 3 three-dimensional subsonic and supersonic flows A78-20919 A78-21093 Effect of nozzle shape on characteristics of Successive-approximation calculation of a steady three-dimensional subsonic and supersonic flows subsonic gas flow about an airfoil lattice A78-21093 478-21085 Study of supersonic separated flow past conical Study of a supercritical profile with oscillating wings and inside a right angle control surface in sub- and transonic flows A78-22C79 [OHEBA, TP HO. 1977-136] A78-21168 Nearly wedge-shaped antisymmetric wing in A generalized vortex lattice method for subsonic superscnic flow and supersonic flew applications 478-22080 [NASA-CB-2865] B78-16002 A study of the inviscid flow about conically SOBSOBIC SPEED cambered delta wings Effects of acoustic and vertical disturbances on [AIAA PAPEB 78-58] A78-22561 the turbulent boundary layer at free-stream Hach Calculation of the three-dimensional supersonic number 0.5 viscous heat-conducting gas flow past blunted [AD-A017921] H78-17026 bodies SOBSTBDCTDHBS 478-21096 Snperelement methcd of designing a helicopter A generalized vortex lattice method for subsonic fuselage and superscnic flow applications B78-17013 [BAS4-CB-2865] B78-16002 SOPEBCBITICil PBBSSDBBS SDPBBSOBIC JET FLOB Study of a supercritical profile with oscillating Interaction of a shock wave with an entropy layer control surface in sut- and transonic flews A78-20886 [OBEBA, TP SO. 1977-136] A78-21168 Semiempirical theory of the generation of discrete SOPEBCBITICAI IIB6S tones by a supersonic nnderexpanded jet flowing Study of a supercritical profile with oscillating over an obstacle control surface in sub- and transonic flows A78-21133 [OHEBA, TP 80. 1977-136] A78-21168 SOPBBSOHIC HOZZLZS Theoretical aspects of dromedaryfoil Computation of the base pressure in ejector [AD-A017150] B78-16023 nozzles of different length with zero SOPEBSOSIC JIBCBJPI coefficient of ejection Configuration development cf a supersonic cruise A78-21098 strike-fighter Experimental investigation of asymmetric Laval [AIAA PAPF.B 78-1Q8] A78-22587 nozzles Arrow wings for supcrscnic cruise aircraft A78-22361 [AIAA PAPEB 78-151] J78-22588 SOEBBSOBIC TBABSPOBTS The locaticn of the ground focus line produced by Advanced supersonic transport propulsion systems a supersonic aircraft [SAE PAPEB 771010] A78-23812 A78-23157 Technology readiness for an SST SOPBBSOBIC JIBFOILS [AIAA FAPEB 78-356] A78-21031 Real flow liaitations in snperscnic airplane design Problems of supersonic transport [AIAA PAPF.E 78-117] A78-22586 [DGLB PAPEB 77-007] A78-21101

4-35 SDPEBSOSIC IAKES SUBJECT IHDEX

SDPEBSOSIC 14KBS SISTERS STABILITY. Rearrangement cf the flov between a fail of Concerning the relationship between element bodies, one of which is situated in the other's stability and system stability in wing-truss wake, ID supersonic flow structure made from elastic and elasto-plastic A78-20913 materials SOPPOBT IHTBBFEBEBCB A78-21971 Experimental investigation of support interference Design of noninteracting flight control systems in on an ogive cylinder at high incidence the presence of large parameter variations [4IAA PAPEE 78-165] 478-20717 [BASA-CR-155589] B78-1606I1 SOPPOBTS Design study of a centerplate mount for Kind tunnel mcdels [AD-A017201] 878-16073 TACT PBOGB8H SOBFACE DISTOBTIOH Transonic computational design modifications of Elastic deformations of rafidly-rctating prismatic the 1-111 TACT nirrors [AIA4 EAPBB 78-106] A78-22577 478-21374 TAIL BOTOBS SOBPACE PIBISBIBG Quiet propeller/rotor concept evaluation of In-state delivery and reinforcement of rigid the DB-1 helicopter airport causeways - Scue technical problems and [AD-A0117297] 878-16017 attempts using special ccatings T8IIIBG A78-24375 Airport surface traffic control visual ground aids SDBFACB GEOHETB1 engineering and development plan Analysis and calculation of plane skew symmetric [AD-A038153] B78-16037 contours of seccnd-crder smoothness for TECHBOLOGIC&l FOSBC8STIBG channel surface design Trends and research opportunities in airbreathing 878-22636 propulsion SOBFACE PBOPEBTIES [AIAA PAPEB 78-44] 478-20652 Modeling the influence cf the ground effect on the VSTCL - Can Bavy needs be met aerodynamic characteristics of a wing ty means [AIAA PAPEE 78-322] 478-21016 of a flat screen of finite dimensions TECBB010GIES A78-22634 Bibliography of Lewis Research Center technical SOBFACB BEACTIOBS contributions announced in 1976 Surface current and charge density induced on [BAS8-TH-73860] 878-17921 aircraft TECHNOLOGY ASSESSBEBT A78-21990 Toward scramjet aircraft progress in engine SOBFACE TEBPEBSTOBB development flear studies on aircraft brake materials 478-23121 478-23133 Aircraft wake vortices: A state-of-the-art review SURGES of the United States R and D program A study on the mechanism of compressor surge due [AD-A042112] 878-16025 to inlet pressure disturbances Research regnirements to improve safety of civil [AIA4 P8PER 78-216] A78-20769 helicopters SDBVBII1AFCB BADAB [B4S4-CB-105620] 878-16026 The Single-Site Collision Avoidance System (SS-CAS) Technical evaluation report on the Avionics [4D-4015977] H78-16035 Panel/Guidance and Control Panel Joint Symposium Airport surface traffic control TAGS planning on Avionics/Guidance and Control for Bemotely alternatives and cost/benefit analysis Piloted Vehicles (BPVs) [AD-A03779C] 878-16038 [AGABD-AK-113] 878-17075 Preliminary limited surveillance radar (1SB) TECBBOLOGY TBABSPEB cost/benefit analysis Conversion of an automotive engine for aircraft fAD-4016829] B78-16245 application Development of a discrete address beaccn system [AIAA PAPEB 78-309] 478-21010 testing oonopolse beacon antennas The problem of technology transfer: Real or [AD-A048247] S78-17C36 imagined SOHVE1S [4D-4012961] 878-17913 An analysis of user acceptance and perceived TECBBOLOGY OTILIZATIOB usability cf C-141A job guides Application of skin technology to turbine blades [AD-4047141] 878-15992 zero gravity manufacture SHEPT RIHGS [4144 PAPER 78-285] 478-20792 Real flow limitations in supersonic airplane design Future development of commercial aircraft: tAIAA PSPII 78-1il7] A78-22586 Technological challenge - Economic constraints SBEPTBACF BIBGS [DGLE F4PEE 77-005] 478-21102 Design of a transonically profiled wing TEHPEBATOBE COBTBOL [DGIB PAPEB 77-026] A78-24417 The experimental determination of the parameters SBIRLIBG of a mathematical model of an aircraft passenger Transonic swirling gas flow through a nozzle compartment as a control plant with respect to A78-22355 air temperature SYSTEB F4ILUBBS 478-22652 sensor failure detection using analytical redundancy TEHPEB4TOBE DISTBIBOTIOB J78-23862 Temperature distributions and thermal stresses in STSTEBS ABA1YSIS a graded zirconia/metal gas path seal system for Systems analysis of safety in aviation. I aircraft gas turbine engines A78-23470 [AIAA PAPER 78-93] 478-20683 STSTEBS EBGIBEEBIBG Economical method for calculating unsteady Robustness of linear guadratic state feedback temperature fields in thin-walled aircraft designs in the presence of system uncertainty structures application to Augventor Bing Jet STOL 478-20903 Research Aircraft flare control autopilot design Steady-state balk temperature field in ccoled J78-23917 turbine blades Aircraft electrical egnipient Russian bcok 478-21156 A78-21I175 TEBPEBATDBE BE4SOBEBBBT Design of ncninteracting flight control systems in 4 current weather information display system for the presence of large parameter variations use at airports rNASA-CB-155589] B78-16C6<1 H78-17600 TEBSILE STBESS Deployment forces in towing systems by aircraft 478-21365

4-36 SDBJBCT IBDEI TBAILIBG EDGES

TEBHIIAl COIDAICE Calculation of general three-dimensional turbulent Hission management in the airport vicinity boundary layers digital flight ccotrcl for terminal maneuvering A78-23188 area Calculation of the three-dimensional supersonic [DG1B PAPEB 77-037] A78-21127 viscous heat-conducting gas flow past blunted TEST BAB6JS bodies Soie applications of a test track for aerod;naiic A78-21096 testing TBBOA1S [AIAA PAPEB 78-167] A78-20719 Velocity profiles in the laval nozzle throat for TBST VBBICIES uniform compressible swirling flow Analysis cf spread inlti-jet VTOL aircraft in hover A78-20905 [BASA-CB-155582] B78-16016 1BBOST A06BBITATIOB TBTBEBII6 The prediction of the performance of low Aerospatiale is ready to develop a convertiplane pressure-ratio thrust-angmenter ejectors •ith tethering rotors [AIAA FAPEB 78-115] A78-20701 [BASA-TB-75038] B78-17012 TBBDST COITBOt TBBBBAL BODID1BI 1AIBB A singular perturbation analysis of optimal The flow about a slender propeller-driven body in aerodynamic and thrust magnitude control a temperature stratified fluid A78-23900 [AIAA PAPEB 78-209] A78-20716 TBBDST VECTOB COITB01 THEBBil COBIEOL COATIRGS Thrust characteristics of thrust vector control An analytical stndy of thermal barrier coated systems with blowing injection of chemically first stage Hades in a JT9D engine nonreactive gases [BASA-CE-135360] B78-16051 A78-21251 Analytxcal study of therial barrier coated TUT BOTOB AIBCBAFT first-stage blades in an F100 engine IV-15 tilt rotor test - Progress report [HASA-CB-135359] B78-17058 [SAE PAPEB 770953] A78-23801 THBBBA1 BXPAISI01 TIRE OPTIBAl COJTBOL Transient eipansion of the components of an air Minimum-time acceleration of aircraft turbofan seal on a gas torbine disc engines [SAE PAEEB 770970] A78-23818 A78-23892 THEBBil EHOTECHOH A singular perturbation analysis cf optimal Stndy of heat sink thermal protection systems for aerodynamic and thrust magnitude control hypersonic research aircraft A78-23900 [AIAA PAPEB 78-38] A78-20618 TIRE BESPOBSE THEBBAL STBESSES The application of the Bouth approximation nethod Temperature distributions and thermal stresses in to tnrbofan engine models a graded zirconia/metal gas path seal systea for A78-23891 aircraft gas turbine engines TIP DBIVB1 EOTOBS [AIA» PAPEB 78-93] A78-20683 Cold-air performance of a tip turbine designed to Stress analysis stndy in cooled radial inflow drive a lift fan. 3: Effect of simulated fan turbine leakage on tnrbine performance [AIAA PAPEE 78-91] A78-22570 [HASA-TP-1109] H78-16001 Calculation of the thernal state of tnrbine blades TITAIIOH AtlOIS with film cooling Ccatings for fretting prevention A78-24270 A78-23111 TBEBBODYBABIC CTCIBS TOLBBABCES (BECHABICS) Inpact of engine cycle parameters on V/STOL Type A Analysis of the determination of configuration and commonality acceptance-inspection parameters for gas-turbine [SAF PAFEB 770980] A78-23821 engines TBIH AIBFOILS A78-22630 Viscous thin airfoil theory and the Rotta condition TOiBD BODIES [AIAA PAPEB 78-152] A78-20707 Approximate wind-tunnel simulation of the dynamics High-frequency approximation for a nonlifting thin of a system composed of a body with a trailing airfoil in subsonic flow cable [AIAA PAPEB 78-226] A78-20755 A78-20902 Perturbing forces in the hydrodynamic interaction Rearrangement of the flow between a pair of of thin-blade cascades in a potential flow bodies, one of which is situated in the other's A78-21219 wake, in supersonic flov THIN lALIBfi SBEIIS A78-20913 Economical nethod for calculating unsteady T01IBG temperature fields in thin-walled aircraft Deployment forces in towing systems by aircraft structures A78-21365 A78-20903 TOIICITT TBII VIHGS Toxicologic gas evaluation of the utility tactical Three-dimensional hypersonic gas flow past a thin transport aircraft system (DB-60) ving [AD-A017801] B78-17016 A78-20795 TBADEOFFS Inviscid supersonic flow about a thin rectangular IAB-61 advanced attack helicopter design tradeoffs plat? [SAE PAPEB 770950] A78-23801 ^78-20906 TBAFFIC COSTEOI Supersonic flow near a thin trapezoidal wing A tandem-gueue algorithm for evaluating overall A78-20921 airport capacity THBBE DIBBISIOHAl F10B B78-16711 Three-dimensional hypersonic gas flow past a thin TBAI1IBG EDGES wing An analysis method for the viscous flow over A78-20795 circulation-controlled airfoils Effect of nozzle shape en characteristics of [AIAA PAPEB 78-157] A78-20710 three-dimensional subsonic and supersonic flows Effect of the thickness of profile and trailing A78-21093 edge on the flow field and the aerodynamic An experimental stndy of three-dimensional characteristics of a low-aspect-ratio delta wing characteristics of propeller wakes under at B = 3 stalling conditicns A78-20919 A78-21632 Uniformly precise conformal mapping of the A stndy of the inviscid flew about conically exterior of a circle onto the exterior of a wing cambered delta vings section [AIAA PAPEE 78-58] A78-22561 A78-22C12

»-37 TBAIBIBG AIBCBAFT SUBJECT ISDBI

AD experimental study cf sound diffraction at an TBABSOBIC BOZZIES airfoil trailing edge Transonic swirling gas flow through a nozzle 878-23217 S78-22355 in analysis of the aircraft trailing vortex systen TBABSOBIC SPEED [AIAA PAPEB 78-312] A78-21013 Experimental observations of wall interference at TBAIBIBG AIBCBAFT transonic speeds Evaluation cf slinpack style parachute in CT1A [AIAA PAPEB 78-161] 478-20716 airtrainer aircraft TBABSOBIC IIBD TOBBBIS [AD-P017083] B78-16021 An analysis of the rotor blade stresses of the TBAJECTOBIES three stage compressor of the Ames Besearch Sensitivity analysis of optimal flight trajectories Center 11- by 11-foot transonic wind tunnel H78-16011 [NASA-CB-152083] B78-17061 TBAJECTOBT ABJITSIS TEABSPOHDEBS Gas path analysis applied to pre and post overhaul Proposed technical characteristics for the testing of JT9D tnrbcfan engine Discrete Address Beacon System (DAES) [SAE PAFEE 770993] A78-23829 [AD-A0182Q6] S78-17035 TBABSFOBHEBS TBABSPOBT AIBCBAPI Pc»er conditioning systems for high-power, Effect of wind turbulence and shear on landing airtorne, pulsed applications performance of jet transports A78-23112 [AIAA PAPEB 78-219] A78-20771 TBABSIEBT BB1TIBG Application of laminar flow control to large Rational parameters of reinforced panels operating subsonic military transport airplanes under conditions of unsteady heating [AIAA PAPEB 78-95] A78-22571 A78-20881 Singular perturbation analysis of optimal flight TBABSITIOB P10B profiles for transport aircraft The basic characteristics of the variation of A78-23901 aerodynamic parameters ir the transiticn region The challenge of advanced fuel-conservative at hypersonic flow velocities aircraft - A manufacturer's view A78-20900 [AIAA PAPEB 78-362] A78-21031 TBASSBISSIOHS (BACHIHE EIEBEITS) Prospects for a new generation air transport Feasibility study cf negative lift circumferential [AIAA FAPEB 78-363] 478-21035 type seal for helicopter transmissions ling with fork tips as means of increasing cost [RASA-CB-135302] H78-17390 effectiveness of transport aircraft TBAHSOBIC FLIGHT [DGIB PAPEB 77-017] 478-21110 Computational transonic airfoil design in free air Integrated flight control system for future and a wind tunnel transport aircraft TAIAA PAPEB 78-1C3] A78-20685 [DGIB PAPEE 77-035] 478-21125 Transonic King analysis using advanced TBAPBZOIDAL IIBGS computational methods Supersonic flow near a thin trapezoidal wing [AIAA PAPEB 78-105] A78-20686 A7B-20921 Transonic computational design oodifications of Stress-strain state of simply-supported the F-111 TACT three-layer trapezoidal plates [AIAA PAPEB 78-106] A78-22577 A78-21205 Design of a transonically profiled wing Unsteady pressure distribution measurements at two [DGIB PAPEB 77-026] A78-21117 trapezoidal wings with unit aspect ratio TB1BSOHIC FlOi B78-17020 Calculation of unsteady transonic flows using the TBAVBLIBG CBABGE integral equation method Electrical fluctuations in turbulent [AIAA PAPEB 78-13] A78-20632 electrogasdynamic flows Steady and unsteady transcnic flov A78-22361 [AIAA PAPEB 78-160] A78-20713 TBEES (BATHEBATICS) Experimental investigation of support interference An assessment of relevant decision making factors on an ogive cylinder at high incidence for organic versus contract maintenance options [AIAA PAPEE 78-165] A78-20717 on OSAF flight simulators large amplitude shock wave moticn in tiio [AD-A017136] B78-16070 dimensional transonic channel flows TBOPOSPBEBE [AIAA PAPEB 78-2117] A78-20770 The tropospheric and stratospheric composition Flow visualization in the region of intersection perturbed by BO/x/ emissions of high-altitude of aerodynamic surfaces aircraft A78-20951 A78-21003 A split-recoupled-semidirect computational TBOSSES technique applied to transonic flow over lifting Concerning the relationship between element airfoils stability and system stability in wing-truss [AIAA PAPEB 78-11] A78-22553 structure made from elastic and elasto-plastic Computational wing optini2ation and wind tunnel materials test of semi-span model A78-21971 [AIAA PAPEE 78-102] A78-22575 TOBBIBE EI.ADES Computational transonic flow about realistic Application of skin technology to turbine tlades aircraft configurations zero gravity manufacture [AIAA PAPEE 78-101] A78-22576 [AIAA PAPEB 78-285] A78-20792 Special areas of gas dynamics: Sonic, hypersonic, Perturbing forces in the hydrodynamic interaction lifting surfaces, wave propagation German book of thin-blade cascades in a potential flew A78-22937 A78-21219 Hethod of calculating the compressible flow round Steady-state bulk temperature field in cooled an aerofoil or a cascade up to the shockfree turbine blades transonic range A78-21156 A78-23271 Investigation of the inclination of nozzle blades A least sguare finite element technique for on the alternating stress level in working transonic flew with shock turbine blades [AIAA PAPEB 78-328] A78-21022 A78-21273 Study of a supercritical profile with oscillating Calculation of the thermal state of turbine blades control surface in sob- and transonic flows with film ccoling [ONEBA, TP BC. 1977-136] A78-21168 478-21271 The practical application of a finite difference Filament-winding fabrication of QCSEE method for analyzing transonic flow over configuration fan blades oscillating airfoils and wings [BASA-CB-135332] B78-16052 [HAS4-CR-2933] H78-16999 An analytical study of thermal barrier coated first stage blades in a JT9D engine [BASA-CB-135360] H78-16051

A-38 SUBJECT 1BDEJ TOBBOIBM PlOi

Analytical study of thermal barrier coated Hethod of fan sound mode structure determination first-stage blades ID an P100 engine computer program user's manual: Hodal [HASA-CB-135359] B78-17058 calculation program TDBB1BB E1GIIES [BASA-CB-135295] B78-17066 Stress analysis study ID cooled radial inflow Optical measurements of DO and SO sab 2 in the turbine exhaust of an F101-GE-100 engine at simulated [AI4A PAPEB 78-91] A78-22S70 altitudes Turbine engine slip ring technology - A survey [AD-AOQ7882] B78-17068 for aircraft 10BBOPABS [SAE PAPEB 770976] A78-23820 An analysis of the influence of some external Cold-air performance of a tip turbine designed to disturbances on the aerodynamic stability of drive a lift fan. 3: Iffect of simulated fan turbine engine axial flow fans and compressors leakage en turbine perfcrnance B78-17051 [BASA-TP-1109] N78-16001 Method of fan sound mode structure determination Preliainary stndy cf propulsion systems and [BASA-CB-135293] B78-1706Q airplane mng parameters for a OS Kavy subsonic Method of fan sound mode structure detertinaticn VSTOl aircraft ccmputer program user's manual: Microphone [HASA-TB-73652] B78-17Cai location program An analysis of the influence cf scne External [BASA-CB-135291] B78-17065 disturbances on the aerodynamic stability of Hethod of fan sound mode structure determnation tarbine engine anal flow fans and conpressors computer program user's manual: nodal B78-1705II calculation program TDBBIBE SBBEIS [HASA-CB-135295] B78-17066 Transient expansion of the compcnents of an air TUBBOGBBBBJTOBS seal on a gas tarbine disc Performance-optimized horizontal-axis wind turbines [SAE PAFEB 77097<1] A78-23818 A78-22232 TDBBIIES T (IB BO JET EIGIHB COHTBOt Optimization stady for high speed radial tnrbine Solution of transient optimization problems by with special reference to design variables using an algorithm based on nonlinear programming [BASA-CB-152091] H78-17063 A78-23909 TDBBOCOBPBESSOBS TOBBOJET EBSIBES A study on the mechanism of compressor surge due The application of dual fuel /JP-LH2/ for to inlet pressure disturbances hypersonic cruise vehicles [AIAA PJPEB 78-216] A78-20769 [4IAA SAPEE 78-119] A78-20705 An analysis of the influence of some external A study on the mechanism of compressor surge due disturbances on the aercdynamc stability of to inlet pressure disturbances turbine engine axial flo« fans and compressors [AIAA PAPEB 78-216] A78-20769 B78-17051 Twenty year evolution of the WB2/WB21 series of TOHBOPAB EB6IBES small tnrbcjet engines Big fans for the airlines [SAE PAPEB 770998] A78-23833 A78-22269 Failure state detection of aircraft engine output Development cf lev pressure ratio vectoring sensors nozzles for V/STC1 aircraft A78-23906 [SAE PAPEB 770988] A78-23825 TOBBOHACHUE BLADES Gas path analysis applied to pre and post overhaul Research on the flatter of axial-tnrtcmachine testing of JT9D turbofan engine blading [SAE PAPEB 770993] A78-23829 [AD-A017086] B78-16021 System identification principles applied to TDBBOIACBIBF.BT. mnltivariahle control synthesis of the F100 Project SODID tnrbofan engine [AD-A017076] K78-16056 A78-23889 TOBBOPBOE EBGISES Frequency domain compensation of a DIBGEB turbofan Advanced turboprop propulsion system reliability engine model and maintenance cost A78-23890 [SAE PAPEB 771009] 478-23811 The application of the Bcnth approximation method Approaches to improving aircraft efficiency to torbofan engine models [AIJA FAPEB 78-305] 478-21007 A78-23891 TDBBDLBBCE Minimum-time acceleration of aircraft tnrbofan Project SCOID engines [AD-4017076] H78-16C56 A78-23892 TDBBDLEBCE EIFECTS Optimal controls for an advanced tnrbofan engine Effect of vind turbulence and shear on landing A78-23893 performance of jet transports Design of tnrbofan engine controls using output [AIAA PAPEB 78-219] 478-20771 feedback regulator theory Atmospheric turbulence loads on aircraft A78-23907 478-23019 Failure detection and correction for tuibofan Theory of two freguency ranges of unstable engines oscillations of turbulent combustion in a A78-23918 jet-engine chamber. I - Formulation of the Statistical evaluation cf the effect of a jet stability problem, the characteristic equation reverser on the parameters of a tnrbofan engine A78-21253 in the direct thrust regime TOBB01BBT BOOIDABI LAIBB A78-21275 Turbulent boundary layer on a moving surface Conceptual design cf single turbofan engine A78-20850 powered light aircraft Calculation of general three-dimensional turbulent [BASA-CB-151972] H78-160II5 boundary layers TF-30-E-7 installed trim correction A78-23188 [AD-AOI17023] B78-16058 Turbulent airfoils for general aviation Variable thrust nozzle for guiet turbofan engine A78-21361 and method cf operating same Effects of acoustic and vortical disturbances on [BASA-CASE-LE1-12317-1 ] H78-17055 the turbulent boundary layer at free-stream Hach Method of fan sound mode structure determination number 0.5 [BASA-CB-135293] B78-1706II [AD-A017921] B78-17026 Hethod of fan sound node structure determination TDBBOLBBT FlOi computer program user's manual: nicrophone Beliable lifting surface solutions for unsteady flow location program [AIAi FAPEB 78-228] A78-2C757 [BASA-CB-135291] B78-17065 Electrical fluctuations in turbulent electrogasdynamic flows A78-2236H

A-39 TOBBOIBNT JETS SUBJECT I1DBX

Heasurements of unsteady vortex flow fields Measurements of unsteady vortex flow fields [AIAA PAPFE 78-18] A78-22551 [AIAA PAPEB 78-18] A78-22551 Sirframe noise, the lover noise limit for aircraft Analysis of unsteady viscous flow past an airfoil. [DGIE PAPIE 77-052] A78-21111 II - numerical formulation and results On some structure-turbulence interaction problems A78-23185 S78-15996 Numerical solution for some problems concerning TOBBULEHT JBTS unsteady motion of airfoils Recent advances concerning an understanding of B78-15995 sound transnission through engine nozzles and jets Contributions to steady and unsteady aerodynamics [DGLB P'PEE 77-018] 478-211037 [D1B-FE-77-31] N78-17001 TOBBU1EB* SAKES Unsteady pressure distribution measurements at tvo The flov about a slender propeller-driven body in trapezoidal wings with unit aspect ratio a temperature stratified fluid N78-17020 [AIAA PAPEB 78-209] A78-20716 A numerical method for calculating the unsteady Prelininary comparison of model and prototype »akes aerodynamic pressure distribution on building Bake effects on atmospheric harmonically oscillating vings vith control boundary layer surfaces in subsonic flov. Theory and results [AIAi PAPEB 78-251] A78-20771 for compressible flov, part 2 Hake vortex measurements cf bodies at high angle [ESA-TT-130] N78-17029 of attack USEB BiHUALS (COBPOTEB PBOGBABS) (AIAA PAPEE 78-23] A78-22555 Stress history simulation. Volume 2: A users Measured wake-vortex characteristics of aircraft manual for a computer program to modify stress in ground effect history simulations crack propagation in [AIAA PAPEB 78-109] A78-22578 fighter aircraft The role cf atmospheric shear, turbulence and a [AD-A012785] N78-17011 ground plane on the dissipation of aircraft flethod of fan sound mode structure determination vortex wakes computer program user's manual: Hicrophone [AIAA PAPEB 78-110] A78-22579 location program Wake turbulence - Gone with the wind airport [BASA-CE-135291] H78-17065 advisory system for aircraft generated vortices Bethod of fan sound mode structure determination A78-213U7 computer program user's manual: nodal Unsteady hovering wake parameters identified from calculation program dynamic nodel tests [BASA-CB-135295] N78-17066 1178-16992 OSBB BEQUIBEHENTS TSO DIBENSI01AI P10B VSIOL - Can Bavy needs be met Large amplitude shock vave motion in tvo [AIAA PAPEB 78-322] A78-21016 dimensional transonic channel flows [AIAA PAPEE 78-217] A78-20770 T«c new correlation dependencies for parameters of flow en a plane delta wing V/STOL AIBCBAFT A78-20933 A combined potential and viscous flov solution for Entropy layer in two-dmensional flows V/STOL engine inlets hypersonic ideal gas flew behind shcck wave [AIAA PAPEE 78-112] A78-20702 A78-21132 Impact of engine cycle parameters on V/STOL Type A Tvo-diaensicnal separated wake modeling and its configuration and commonality use to predict maximum section lift coefficient [SAE PAPEB 770980] A78-23821 [AIAA PAPEE 78-156] A78-22590 Sensitivity studies for several high performance Analysis cf unsteady visccus flew past an airfoil. VSTOL concepts II - NuEerical fcrnulaticn and results [SAE PAPEB 770982] A78-23622 A78-23185 Development of the propulsion simulator - A test Two-dimensicnal wind tunnel test cf an oscillating tool applicable to V/STOL configurations rotor airfoil, volume 2 tabulated test results [SAE PAPEB 770981] A78-23823 [HASA-CB-2915] N78-16998 The impact of emerging technologies on tactical V/STC1 airplane design and utility u [SAE PAPEB 770985] A78-23821 Development cf lov pressure ratio vectoring OB-60A HELICOPTEB nozzles for V/STOL aircraft Army OTTAS program DB-60A helicopter for [SAI PAPEB 770988] A78-23825 Utility Tactical Transport Aircraft System A clutch for V/STOL [SAE PAPEB 770952] A78-23803 [SAE PAPEB 770989] A7S-23826 OLTB»BIGH FBEOOENCIBS VSTOL - Can Bavy needs be met Automated DBF freguency assignment system for FAA [AIAA EAPF.B 78-322] A78-21016 air traffic contiol communications Preliminary study of propulsion systems and [AD-A0178117] B78-17C31 airplane wing parameters for a US Navy subsonic UNIFOBB FLOW V/SIOL aircraft The low-speed air tunnel cf the Institute cf [HASA-TB-73652] B78-17011 Bydromecbanics at the University of Karlsruhe Aerospatiale is ready to develop a ccnvertiplane A78-23297 with tethering rotors UNITED STATES OF AIBBICA [BASA-TB-75038] N78-17012 Aircraft wake vortices: A state-of-the-art review Low speed test of a high-bypass-ratio propulsion of the United States B and D program system with an asymmetric inlet designed for a [AD-A012112] B78-16025 tilt-nacelle V/STOI airplane UNSTEADY FIOR [NASA-CB-152072] B78-17062 Calculation of unsteady transonic flews using the VABISELB CICJ.E EI6IIES integral equation metfacd Advanced supersonic transport propulsion systems [AIAA PAPEE 78-13] A78-20632 [SAE PAPEB 771010] A78-23812 Steady and unsteady transonic flow A review of NASA's propulsion programs for aviation [AIAA PAPEE 78-160] A78-20713 [NASA-TB-73831] H78-16055 Hjqh-freqnency approximation for a nonlifting thin VABIABLE IBBUST airfoil in subsonic flow Variable thrust nozzle for guiet tnrbofan engine [AIAA PAPEB 78-226] A78-20755 and method of operating same Sellable lifting surface solutions for unsteady flow [NASA-CASE-LES-12317-1] N78-17055 TAIAA PUPEE 78-228] A78-20757 VECTOBS (BATBEBATICS) Construction of a lathematical model of a jet A generalized vortex lattice method for subsonic engine for analyzing transient flews and supersonic flov applications A78-20971 [BASA-CB-2865] N78-16002 Perturbing forces in the hydrodynamic interaction of thin-tlade cascades in a potential flow A78-21219

A-10 SUBJECT 1BDII

VBBICOLAB TB8CKS VOBIBI SBEETS Some applications of a test track for aerodynamic The analysis of wing-body combinations at moderate testing angles cf attack [AIAA PAPEB 78-167] 478-20719 [AIAA IAPEB 78-62] A78-20663 Helicopter Ground Bobility System (BGBS) concept Calculation of nonlinear aerodynamic fornnlation and selection characteristics of wing of complex planform [AD-AO

i-01 REAB TESTS SUBJECT IHDBI

REAB TESTS Beynolds number criticality in dynamic tests Friction and wear cf sintered fibermetal abradable [AIAA PAPEB 78-166] A78-20718 seal materials An investigation of strut-wall intersection losses A78-23151 [AI8A PAPBB 78-205] A78-20713 RBATBEB DATA BECOBDEBS Measurements of noise produced by flow past Automated meteorological data from commercial lifting surfaces aircraft via satellite: Present experience and [AIAA EAPEB 78-239] A78-20762 future nrplicaticns Preliminary comparison of model and prototype wakes [BASA-TB-73750] 818-17558 building wake effects on atmospheric HEDGE FLOH boundary layer Nearly Hedge-shaped antisymmetric wing in [AIAA PAPEB 78-2511] A78-2077H supersonic flou Pressure distribution over sharp-nosed cones 878-22080 situated at angles of attack from 0 to 10 HEIGHT BEDOCTIOS degrees in supersonic flow Relating take off gross Height and DISSICD A78-20889 requirements for geonetricallj optimized aircraft Approximate wind-tunnel simulation of the dynamics fAIAA PAPEE 78-98] A78-20681 of a system composed of a body with a trailing A fcrmulaticn cf the problem cf the Einiffum-drag cable vinq A78-20902 A78-20867 Determination of airfoil lift from pressure An evaluation of weight optimization of aircraft measurement at the test section walls in a radioelectronic equipment subsonic wind-tunnel A78-226116 A78-20973 The weight of fuel tanks in aircraft Computational wing optimization and wind tunnel A78-22818 test of seHi-span model Sensitivity studies for several high performance [AIAA PAPBS 78-102] A78-22575 VST01 ccncepts The lew-speed air tunnel of the Institute of fSAE PAPEB 770982] A78-23822 Hydromechanics at the University of Karlsruhe RBI6HTLBSSBESS A78-23297 Application of skin technology to turbine blades An investigation into the effects of shear on the zero gravity manufacture flow past bluff bodies [AIAA PAPIB 78-285] A78-20792 [AIAA PAPEB 78-331] A78-2<4025 BELDED JOJITS Profile design for an advanced-technology airfoil Development cf random fatigue data for adhesively for general aviation aircraft bonded and weldbcnded structures subjected to [DG1B EAPEB 77-027] A78-21418 dynamic excitation aircraft structures Six degrees of freedom system for store separation [ASHE PAEIB 77-RVHAT-1] A78-23373 studies in OBEBA wind-tunnels HIHD EFFECTS [ONEBA, TP FO. 1977-100] A78-21160 Effect of wind turbulence and shear on landing Bind-tunnel investigation of aerodynamic performance of jet transports performance, steady amd vibratory loads, surface [AIAA PAPEB 78-219] A78-20771 temperatures, and acoustic characteristics of a Atmospheric turbulence leads on aircraft large-scale twin-engine upper-surface blown A78-23CI49 jet-flap configuration A severe downslope windstorm and aircraft [NASA-TB-D-8235] S78-15999 turbulence event induced by a mountain wave Two-dimensional wind tunnel test of an oscillating A78-2U356 rotor airfoil, volume 1 RIND HEASOBEBBHT [NASA-CB-29KI] B78-16003 Hake turbulence - Gone with the wind airport Two-dimensional wind tunnel test of an oscillating advisory system for aircraft generated vortices rotor airfoil, volume 2 tabulated test results A78-2H317 [NASA-CB-2915] N78-16S98 BIND SBEAB RIBD TUBBBL SA1IS The role cf atmospheric shear, turbulence and a Experimental observations of wall interference at ground plane on the dissipation of aircraft transonic speeds vortex wakes [AIAA PAPEB 78-161] A78-20716 [AIAA PAPEB 78-110] A78-22579 Determination of airfoil lift fron pressure Tie low-level Hind Shear Alert Program measurement at the test section walls in a A78-21316 subsonic wind-tunnel The endangerment of flight safety due tc wind shear A78-20973 CDGLB PAPEB 77-062] A78-21118 HID TOHIELS Piloted flight simulator study of low-level wind A method for the construction of flow nozzles and shear, phase 1 wind tunnel contraction sections [AD-A0117985] H78-17078 A78-21635 • IND TDNBEI APPABATDS Two-dimensional wind tunnel test of an oscillating laser-velocimeter surveys of merging vortices in a rotor airfoil, volume 1 wind tunnel [NASA-CB-2911] N78-16003 [AIAA PAIEB 78-107] A78-20687 RIBD VELOCITY BBASDBEBEBT BISD TDBHB1 BODE1S A digital continuously updated two minute mean Solving the problem of numerical construction of a windspeed indicator for use at airports model of similar rigidity to the initial B78-17598 structure as a problem cf qoadratic programming A current weather information display system for A78-20864 use at airports Wind tunnel model study of the hot exhaust plume 1178-17600 from the CcnpresEor Research Facility at II1DPOREBED GBBEBATOBS Bright-Patterson Air Force Base, Ohio Performance-optimized horizontal-axis wind turbines [AD-A017205] B78-16072 A78-22232 Design study of a centerplate mount for wind RIBG CAHBIB tunnel models Computational wing optimization and wind tonnel CAD-A017201] 878-16073 test of semi-span model WIND TOBBEl TESTS [AIAA PAPEB 78-102] A78-22575 Computational transonic airfoil design in free air RIBG FLAPS and a wind tunnel Analysis of heat transfer in a simulated [AIAA PAPEB 78-103] A78-20685 wing-elevon cove in hypersonic flow Laser-velocimeter surveys of merging vortices ID a [AIAA PAPEE 78-10] A78-22556 wind tunnel RIBG IOADHG [AIAA PAPEB 78-107] A78-20687 The application of dual fuel /JP-LB2/ for Experimental investigation of support interference hyperscnic cruise vehicles on an ogive cylinder at high incidence [AIAA EAPEB 78-119] J78-20705 [AIAA PAEEB 78-165] A78-20717 Sellable lifting surface solutions for unsteady flow [AIAA PAPEB 78-228] A78-20757

A-12 SUBJECT IHDEI ZIBC01IOB OIIDBS

Turbulent boundary layer CD a aoving surface 1IBG TIC TOETICES A78-20850 The effect of dhitcomb winglets and other vingtip Rational arrangement of the structural and modifications on wake vortices load-beating elements of the King mth allowance B78-16988 for certain aerodynamic requirements IIBC TIPS A78-20980 Sang with fork tips as means of increasing cost BIHG OSCILIATICBS effectiveness of transport aircraft The effect of angle of attack on the aercdamping [DGIB EAPEB 77-017] A78-2Q010 of wing-profile vibrations The significance of wing end configuration in A78-20252 airfoil design for civil aviation aircraft Numerical solution for seme problems concerning [DGLB fAPEB 77-030] A78-21M21 unsteady ictioo of airfcils CIRGZD 7BBICIBS H78-15995 Bormal-force and pitching-moment coefficients of The practical application of a finite difference wing-body combinations at very high angles cf set hod for analyzing transonic flow over attack oscillating airfcils and wings [AIAA SAPEB 78-63] A78-20661 [BASA-CE-2933] N78-16999 SIBG1ETS The stall problem The significance of ving end configuration in H78-17006 airfoil design for civil aviation aircraft A numerical lethod for calculating the unsteady [DGIE PAPEE 77-030] S78-2I1121 aerodynamic pressure distribution on Aircraft performance improvement through harmonically oscillating wings with ccntrol retrofitting of mnglets surfaces m subsonic flow. Theory and results [DGIB PAPEB 77-031] A78-21U22 for compressible flew, part 2 The effect of Bhitcomb winglets and other vingtip [ESA-TT-

A-Q3 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl 96) MAY 1978

Typical Personal Author Index Listing

PERSONALflUTHOR I BBASLET, B. D.~ An exploratory investigation of the effects of a ASDEBS, 15.-P. thin plastic fill cover on the profile drag of Flovfield and pressure field of a model propeller it an aircraft ving panel A78-2UU51 [RASA-TH-7H073] R78-10023 ABDBESS, D. B. Analytical study of thermal barrier coated 1 first-stage blades in an FIDO engine 1 [RASA-CB-135359] H78-170S8 TITLE REPORT ABDBBI, I. V. NUMBER Flutter tests of the mated 7U7 Shuttle Carrier Aircraft-Orbiter [SAE PAPEB 770971] A78-23816 AHGELIII, J.-J. Listings in this index are arranged alphabetically by personal author The title The OREBA position on the use of feed-back control of the document provides the user with a brief description of the subject matter against flutter due to external ving-mounted stores The report number helps to indicate the type of document cited (e g NASA [OREBA, TP RO. 1977-101] A78-20

B-1 BAKBB, B. 8. PBBSOBAl AOTHOB IHDEI

BAKBB, H. B. BISHOP, B. B. A generalized vortex lattice method for subsonic Engine development toward lower energy consumption and snpersonic flow applications and reduced environmental impact [8ASA-CB-2865] 1178-16002 [AIAA PAPEB 78-307] A78-21008 BAtLBADS, H. F. BUCK, B. F. Computational wing optinization and wind tunnel Effect of wind turbulence and shear on landing test of semi-span model performance of jet transports tAIAA PAPEB 78-102] A78-22575 [AIAA EAPEB 78-219] A78-20771 BABBBB, T. J. BOBOVICB, A. B. An investigation of strut-wall intersection losses Experimental investigation of asymmetric Laval [AIAA PAEEB 78-205] A78-20743 nozzles BASHES, F. S. A78-22361 Design of noninteracting flight control systems in BOBBBBI, B. the presence of large parameter variations Integrated flight control system for future rHASA-CE-155589] H78-16061 transport aircraft BABBOIS, I. [DGLB EAPEB 77-035] A78-21125 The strength of structures and the applications of BOLTZ, F. 1. the fracture mechanics Aerodynamic characteristics of an 1-8 aircraft A78-23571 configuration with a variable camber wing at Stresses and displacenents doe to load transfer by Bach numbers from 1.5 to 2.0 fasteners in stroctoral assemblies [HASA-TH-73271] K78-16062 A78-23575 BOFPB, C. S. BASD, B. C. Computational transonic flow about realistic An aerofoil vith control surface in incompressible aircraft configurations viscous flow [AIAA PAPEB 78-101] A78-22576 A78-23050 BOBST, B. V. BAOEB. J- Design and analysis of propellers for low Beynolds Use of the finite element method in fracture number application to mini-BPV's mechanics [SAE PAPEB 770999] A78-23831 [DGLB FAPEB 77-055] A78-21113 BOTTBBI, B. P. BAOH, J. A. Air Force research and development activities Advanced turboprop propulsion system reliability related to aircraft fire protection and maintenance cost [AIAA PAPEB 78-269] A78-20782 [SAE EAFEB 771009] A78-238U1 BBEAHT, I. BAIA, B. e., JB. A stody on the capacity of runway systems Investigation of new techniques for aircraft A78-21371 navigation using the omega navigation BBEGLIO, B. A., JB. [NASA-CB-115303] H78-17037 Development of cost estimating relationships for BAZZBIN, A. C. aircraft jet core-engine overhaul costs Calculation of the mean flew characteristics at [AD-AOU7667] 878-17067 the inlet to the air intake located under a BBEIfBACB, E. delta ning Significance of structural nonlinearities from the A78-20895 structural dynamics and aeroelasticity point of Two ne» correlation dependencies for parameters of view flow on a plane delta wing H78-17005 A78-20933 Effects of structural non-linearities on aircraft BECHEBT, D. vibration and flutter Bedncing aircraft noise through retrofitting [AGABD-B-665] H78-17076 [DGLB PAPEB 77-017] A78-21436 BBOCKS, I. Becent advances concerning an understanding of Concerning the relationship between element sound transmission through engine nozzles and jets stability and system stability in wing-truss [DGLB PAPEB 77-048] A78-21137 structure made from elastic and elasto-plastic BEHSCB, B. B. materials Effect of wind turbulence and shear on landing A78-21971 performance of jet transports BBOIABD, F. [AIAA PAEEE 78-2

B-2 PEBS01AL AOIBOB UDEI CBIHBBI16, I. a.

Supereleient method of designing a helicopter CBOBU, B. fuselage An optical fibre, multi-terminal data system for 878-17013 aircraft BDBBS, J. V. 878-168(9 Constant speed generating systems CHOBABOV, ?. I. [SAE P'PEB 771001] 478-23835 Taking into account the effect of elasticity of BOBHSIDE. 8. D. the structure on the longitudinal*short-period Surface current and charge density induced on motion of an aircraft aircraft 478-20882 478-21990 CBOBCHI11, i. T. BDBTB, K. Future aviation turbine fuels ConcerniDcj the relationship between element [AIAi P4PEB 78-268] 478-20781 stability and system stability in wing-truss CIElilt, Z. B. structure made froa elastic and elasto-plastic Analysis of unsteady viscous flov past an airfoil. materials II - numerical formulation and results 478-21971 478-23185 BDTBIKO, T. A. CIEPLOCH, C. C. Experimental investigation of the characteristics Preliminary QCSEE program - Test results of siall-sized nozzles [S4B P4PEE 771008] 478-23840 1178-21090 CIFFOIB, D. L. Heasnred nake-vortex characteristics of aircraft in ground effect [4144 F4PEB 78-109] 478-22578 CAUSE, A. J. C1ABR. J. A singular perturbation analysis cf optimal Initial collision avoidance algorithms for the aerodynamic and thrust magnitude control beacon-cased collision avoidance system 478-23900 [AD-40Q72511] B78-16031 Singular perturbation analysis of optimal flight CL4BK, H. profiles for transport aircraft Rake turbulence - Gone with the vind 478-23901 478-2<13<»7 CAHP, 0. B. CL4DS, B. I. Preliminary comparison of model and prototype wakes The effect of ambient conditions on the emissions [AIAA PSPEB 78-251] A78-20771 of an idling gas turbine CASPIEID, B. B. [4144 TAPES 78-3] A78-22551 Variable speed constant freguency /VSCF/ aircraft CLODFBLTEB, B. G. electrical power Air Force research and development activities [SAE PAfEB 771002] A78-23836 related to aircraft fire protection CAPBILOPO, J, P. [4144 FAPEH 78-269] 478-20782 'New look* in assurance technology - 'The Hornet1 COLE, J. D. [AIAA PAPEB 78-323] 478-24017 Computational transonic airfoil design in free air CABLSON, C..E. and a Hind tunnel Holographic inspection of jet engine composite fan [4141 PAPEB 78-103] 478-20685 blades COLLET, P. [SAE PAPEB 770975] A78-23819 4 study on the capacity of runway systems CAEB, L. 8. 478-2*3714 Dynamic stall experiments on the NACA 0012 airfoil COLL1IS, J. B. ?. [HASA-TP-1100] N78-17000 Testing a modern strike aircraft navigation system CABTA, F. 478-22852 Project SCOID COBDEI1, B. B. [AD-A017076] H78-16056 4irline delay trends, 1971-1975. 4 study of block CASTELLAII, ». time delays, ground and airborne, for scheduled An introduction to the problem of dynamic air carriers structural damping [4D-A039U83] 878-16028 [AGABD-B-663] N78-17071 COOK, S. I. CASTILLO, J. P. The problem of technology transfer: Beal or Broad-band analysis of VLP/LF aircraft Hire antennas imagined A78-21995 [4D-A042961] 878-17913 CHAD, K. L. COBLBT, B. C. Unsteady aerodynamic forces on harmonically Failure detection and correction for tnrbofan oscillating pointed circular conical shells with engines small aperture angle 478-23918 S78-17007 COBSIGLIA, T. B. CHABLES, J. f. laser-velocimeter surveys of merging vortices in a Instructor pilot's role in simulation training, vind tunnel phase 2 [AI4A E4PEB 78-107] 478-20687 [AD-A017919] H78-17082 COB7IB, I. CHBB, 1. i. Rechanism of wear in helicopter hydraulic systems Transonic computational design modifications of 478-23139 the F-111 1ACT COSTS, J. [AIAA PSPEB 78-106] A78-22577 Six degrees of freedom system for store separation CBBSHOKOV. S, S. studies in 08EB& wind-tunnels Application of the finite element method to the [OHEB4, IP 80. 1977-100] 478-21160 stability analysis of triangular plates in CODLBI, 6. supersonic flow Method of calculating the compressible flow round A78-20866 an aerofoil or a cascade up to the shockfree CHIBOV, V. P. transonic range Experimental investigation of the characteristics 478-23271 of small-sized nozzles CBE1S, S. T. 478-21090 Unsteady hovering wake parameters identified from CBISTIAK07, 9. E. dynamic model tests Determination of the longitudinal lines cf an 878-16992 aircraft fuselage by the special-contour method CBIBBBIHG, 8. B. 478-22610 Simulation tests of flight technical error in CBOPII, I. B. 20/30 area navigation (RS1V) using a multiple Quiet propeller/rotor concept evaluation waypoint BSSV system with and without a flight [AD-4007297] 878-16017 director system [AD-4017216] 878-16029

B-3 CBOOK, «. 6. PBBSOHAL 4DTHOE IBDEI

CBOOK, I. G. DIETZ, ». B., JB. Simulation tests of flight technical error in Ezperinental investigation of support interference 2D/3D area navigation (BHAV) nsing a multiple on an ogive cylinder at high incidence waypoint BSAV system with and without a flight [AIAA PAPEB 78-165] A78-20717 director system DILL, B. D. tAD-AO<»72ft6] S78-16029 Stress history simulation. Volume 2: A users CBOT2BB, P. J. . manual for a computer program to modify stress The tropospberic and stratospheric composition history simulations perturbed by HO/x/ emissions of high-altitude [AD-A012785] B78-17011I aircraft DILLOB, J. L. A78-21003 An aerodynamic analysis of several hypersonic CDHBIHGHiH, T. B. research airplane concepts fron-B = 0.2 to 6.0 Sensor failure detection nsing analytical redundancy [AIAA PAPEB 78-150] A78-20706 A78-23862 DIVJB, P. B., Ill Aerodynamic optimization and analysis as part of the computer-aided design process [AIAi PAPEB 78-97] A78-22572 DADOBE, L. D. DODS, J. B., JB. Two-dimensional wind tunnel test of an oscillating An analysis of the rotor blade stresses cf the rotor airfoil, volume 1 three stage compressor of the Ames Research [NASA-CB-291

EDiiBDS. C. I. i. BIALD, B. Study of beat sink therial protection systens for Aircraft performance improvement through hypersonic research aircraft retrofitting of vinglets [AIAA PIPES 78-38] A78-20618 [DGIB PAPEH 77-031] A78-23122 GEHPAK: An arbitrary aircraft geometry generator BilBG. H. S. [RASA-TF-1022] H78-160H2 Quiet propeller/rotor concept evaluation EDiiBDS, 3. «. [AD-A007297] 1178-16007 Unsteady aerodynamic modeling and active aeroelastic control H78-16061 EFBBH07, H. I. FABBY. H. F. Computation of the base pressure in ejector The effect of Shitconb winglets and other wingtip nozzles of different length with zero modifications on wake vortices coefficient of ejection B78-16988 478-21098 FABBIBGTOI, J. G. EBLBBS, E. E. An optical fibre, multi-terminal data system for The practical application of a finite difference aircraft method for analyzing transonic flow over 878-16809 oscillating airfoils and wings FaBSSBHAB, G. B., JB. [H4SA-CB-2933] H78-16999 An assessment of relevant decision making factors EICBBOBS. B. for organic versus contract maintenance options A method for the construction of flow nozzles and on OSAP flight simulators wind tannel contraction sections [AD-A007136] 1178-16070 A78-21635 FAVIEB, D. EIGBBBAgS, 8. P. An experimental study of three-dimensional Development of the propolsion simnlator - A test characteristics of propeller wakes under tool applicable to V/STOL configurations stalling conditions [SAE PAPEB 770980] A78-23823 A78-21632 ELDBBDGB, D. FETZEB, I. i., JB. Simulation tests of flight technical error in Evaluation of and operational procedures for a 2D/3D area navigation (BBAV) using a multiple helicopter simulation system utilizing an waypoint BNAV system Kith and without a flight integrated electronic instrument display director system [AD-A007166] 1178-16069 CAD-A007206] H78-16029 PIS, D. D. ELLIOT, B. D. IV-15 tilt rotor test - Progress report A generalized vortex lattice method for subsonic [SAE PAPEB 770953] A78-23800 and supersonic flow applications PEi, J. D. [HASA-CB-2865] H78-16002 Optical measurements of DO and NO sub 2 in the ELLIS, D. B. exhaust of an F101-GE-100 engine at simulated Piloted flight simulator study of lov-level wind altitudes shear, phase 2 [AD-A007882] S78-17068 [AD-A007251] H78-16067 FIELDS, I. D. EBALIJHOVA, 6. 1. Configuration development of a supersonic cruise Turbulent boundary layer on a moving surface strike-fighter A78-20850 [AIAA PAPEB 78-108] A78-22587 EPP1EB, B. PILIBOHOS. I. H. Turbulent airfoils for general aviation Calculation of the mean flow characteristics at A78-20360 the inlet to the air intake located under a EBBED, E. delta wing Application of skin technology to turbine blades A78-20895 [A1AA EAPP.E 78-285] A78-20792 FISCBBB, B. EBDEL, K. Basic considerations concerning the possibilities Glass-fiber data bus systems for signal of wing families in civil aviation transmission en board [DGLB PAPEE 77-029] A78-20020 A78-21976 FISCBEB, B. EBEZA, &. G. The integrated shielded propeller as a drive Plow visualization in the region of intersection system for general aviation aircraft of aerodynamic surfaces [DGIB PAPEB 77-005] A78-20030 A78-20951 FISCIBA, C. EBICSSOB, L. E. An investigation into the effects of shear on the Reynolds number criticality in dynamic tests flov past bluff bodies [AIAA PAFEE 78-166] A78-20718 [AIAA PAPEB 78-331] A78-20025 EBBOIESKO, S. D. FISBBACB, 1. B. nodeling the influence of the ground effect on the Preliminary study of propulsion systems and aerodynamic characteristics of a wing ty means airplane wing parameters for a OS Bavy subsonic of a flat screen of finite dimensions V/STOL aircraft A78-22630 [SASA-1H-73652] B78-17001 EBBOLII, 8. E. PITZSIBBOJS, B. 0. Entropy layer in two-dimensional flows Technology readiness for an SSI A78-21132 [AIAA PAPEB 78-356] A78-20031 EBBSBAOS, B. FOBBSCBI1G, B. The low-speed air tunnel of the Institute of Unsteady aerodynamic forces on harmonically Hydromechanics at the Dniversity of Karlsruhe oscillating pointed circular conical shells with A78-23297 snail aperture angle EBOPEEV, A. I. B78-17C07 Calculaticn of the flow cf a rarefied gas past a POLLE, B. I. plate of infinite span Dearly wedge-shaped antisymmetric wing in A78-20857 supersonic flow ESSEI, B. J. A78-22080 Concorde AIDS - Powerplant applications POBESIBB, C. K. [SAP. PAPEB 770995] A78-23831 Numerical simulation of the interaction of jet and EVEBTZ, E. freestream flows in engine exhaust systems Localization and shielding of noise sources [AIAA FAPEB 78-100] A78-22580 generated by the interaction cf free jets with FOBBEST. J. E. flat surfaces Experimental relationships between moduli for soil TDGIP PAPEF 77-009] A78-20038 layers beneath concrete pavements [AD-A006239/0] B78-16068

B-5 FOBSTTH, J. P. PBBSOHAL iOTBOE IHDEI

FOBSITH, J. P. Piloted flight simulator study of low-level wind Helicopter Ground nobility System (HGnS) concept shear, phase 1 formulation and selection [AD-AOI17985] 1178-17078 [AD-A047507] N78-17080 GAVBISEV, V. S. FOBSTTH, B. I. Determination of airfoil lift from pressure Helicopter Ground nobility Systen (HGHS) concept measurement at the test section walls in a formulation and selection subsonic wind-tunnel [AD-AO<|7507] H78-17080 A78-20973 FOSTEB, F. B. GBISSLEB, I. Stress history simulation. Volume 2: A users The interference problem of the oscillating manual for a computer program to modify stress fuselage near ground history simnlaticns 1178-17008 [AD-AO

B-6 PBBSOIJL AOTBOB IHDBI BOBPGBB. G.

GOBSSII, V. B. BABBD, A. Transonic swirling gas flow throngh a nozzle A study on the mechanism of compressor surge due 878-22355 to inlet pressure disturbances GBABAH, I. [AIAA FAPEB 78-246] A78-20769 Fire detection devices Stress analysis study in cooled radial inflow A78-22900 turbine GBAHEE, D. I. [AIAA PAPEB 78-9H] A78-22570 Study of metallic structural design concepts for BABET, B. P. an arrow wing supersonic craise configuration Computational wing optimization and wind tunnel [NASA-CB-2743] B78-16043 test of semi-span model GBEEBBAT, H. K. [AIAA PAPEB 78-102] A78-22575 Relating take off gross weight and mission BAB6ABTBBB. B. requirements for geometrically optimized aircraft Bodifications to FAISTAPP that were required for [AIAA PAPEB 78-98] A78-20684 operation en a 16 K PDP-8e minicomputer GBBEBSELI. B. A. [1TB-ST-899] B78-16392 A-7 A10FT econonic analysis and EBI-ESP test results BASSOS, I. B. H78-16816 A discrete-event digital simulation model of the GBBBOB, B. F-16 fire control computer operational flight Study of a supercritical profile with oscillating program using simscript 2.5 control surface 10 sob- and transonic flows [AD-A048164] H78-17047 [OFEBA, IP HO. 1977-136] A76-24468 BABVILl, 1. B. GBIH, V. I. Service experience of composite parts on the Construction of a mathematical nodel of a jet L-1011 and C-130 engine for analyzing transient flows A78-24548 A78-20971 BARKIBS, i. B. GBOBRAB, J. Where aerospace can serve afresh - Paths to energy Alternative aircraft fuels independence [HASA-TB-73836] B78-17229 A78-23420 GBOSS. I. I. BBAVEIS, S. B. The prediction of tvo-dimensional airfoil stall An experimental study of sound diffraction at an progression airfoil trailing edge [AIAA PAPEI 78-155] A78-20709 A78-2320.7 GOIIAEV. V. V. BBIBBICH, A. B. A study of the influence of slits on the Conceptual design of single tnrbofan engine effectiveness of wing mechanization and controls powered light aircraft in separated flow [BASA-CB-151972] H78-16045 A78-22647 BBBPBl, J. GUHCBBBKO, E. I. Basic considerations concerning the possibilities Steady-state bulk temperature field ID cooled of wing families in civil aviation turbine blades [DGIB PAPEB 77-029] A78-24420 A78-24156 HEBDEBSOU, B. 1. Calculation of the thermal state of turbine blades Two-dimensional separated wake modeling and its with film ceding use to predict maximum section lift coefficient A78-24274 [AIAA PAPEB 78-156] A78-22590 GOHNBBSOB, D. «. EERIE, P. A. Development and test of an inlet and duct to Transonic wing analysis using advanced provide airflow for a wing boundary layer computational methods control system [AIAA PAPEB 78-105] A78-20686 [AIAA PAPEB 78-141] A78-20701 BEBS1BB, T. GBSSTOB, «. Automated DHP freguency assignment system for fAA Big fans fcr the airlines air traffic control communications A78-22269 [AD-A047847] S78-17034 GOPTA. B. R. BBBBIBG, B. I. New freguency domain methods for system Evaluation of a large capacity heat pump concept identification for active cooling of hypersonic aircraft A78-23883 structure GDSBV, 7. B. [BASA-CB-145301] B78-17339 The basic characteristics of the variation of BICKS, B. B. aerodynamic parameters in the transition region Transonic wing analysis using advanced at hypersonic flcn velocities computational methods 878-20900 [AIAA PAPEB 78-105] 878-20686 Characteristics of the jet acceleration of a flow BIDALGO, B. to hypersonic speeds The tropospheric and stratospheric composition A78-20953 perturbed by SO/i/ emissions of high-altitude aircraft A78-21003 H Bill, 1. G., JB. HAAS. J. B. Investigation of VTOL npwash flows formed by two Cold-air performance of a tip turbine designed to impinging jets drive a lift fan. 3: Effect of simulated fan [AD-AOQ7805] 878-17025 leakage on turbine performance HIBSB, J. B. [NASA-TP-1109] S78-16001 The role of atmospheric shear, turbulence and a HADDOCK, J. 1. ground plane on the dissipation of aircraft Aircraft wake vortices: A state-of-the-art review vortex wakes of the United States G and D program [AIAA TAPES 78-110] A78-22579 [BD-A042442] S78-16025 BIBST, B. BAGS, B. E. Airborne navigation systems The challenge of advanced fuel-conservative A78-22347 aircraft - A manufacturer's view BO, T. L. [AIAA PAPEB 78-362] A78-24034 Rear studies on aircraft brake materials HAIDL, G. A78-23433 New methods for flight vibration studies BODGE, J. S. [DGLB PAPEB 77-050] A78-24439 Numerical solution for airfoils near stall in BAIL, I. B.. JB. optimized boundary-fitted curvilinear coordinates Syste« identification principles applied to [AIAA EAPEB 78-284] 878-20791 mnltivariable control synthesis of the P100 BOEFGEB, G. turbofan engine The technical potential of instrument landing A78-23889 systems in the present and in the future [DGIB.PAPEB 77-019] A78-24Q12

B-7 BOEPPSBB, B. PEBSOBAl AUTBOB IBDBI

BOEPPSSB, B. JEBBEY., 6. 0. Future development cf commercial aircraft: Besearch and development of aircraft control Technological challenge - Economic constraints actuation systems. The development of a direct [DGLH PAPEB 77-005] A78-2t

B-8 PEBSOHAL AOIBOB IBDBI IAHSB, J. B.

KBIT, B. KOOB. S. J. Condition monitoring ezperience OD CF6 engines Relating take off gross weight and mission [SAE PAPEB 770991] S78-23830 reguirements for geometrically optimized aircraft KEBTFIELD, J. S. C. [AIAA EAPEB 78-98] A78-20681I The prediction of the performance of low KOBBILOVICB. ?. B. pressure-ratio thrust-augmenter ejectors Experimental investigation of asymmetric Laval [AIAA PAPEE 78-KI5] A78-2070U nozzles KESBOCK, E. 6. A78-22361 Analysis of heat transfer in a simulated KOTBLBIKOV, G. B. sing-eleven cove in hypersonic flow Distribution of reliability characteristics among [AliA PAPEB 78-90] A78-22556 aircraft units to ensure a given flight-safety KBALIL, I. level Optimization stady for high speed radial turbine A78-22639 vith special reference tc design variables KOTTAPAL1I, S. B. B. [NASA-CB-15209«] N78-17063 Drag on an oscillating airfoil in a fluctuating KBABCBB8KO, V. B. free stream Organization of a programmed matrix-operation F78-16994 system in an airborne digital computer KOVAtEV. 1. A. A78-21585 Investigation of the inclination of nozzle blades KHLBBBIKOV, V. S. on the alternating stress level in working Bearrangeient of the flow between a pair of turbine blades bodies, one of which is situated in the other's A78-2H273 wake, in supersonic flow KOZBETIIKOV. ID. T. A78-20913 Analysis of the determination of KBVILOB, E. A. acceptance-inspection parameters for gas-turbine Stress-strain state of simply-supported engines three-layer trapezoidal plates A78-22630 A78-21205 KBABBBB, 0. KIEREBOSCH, B. Advanced guiet propulsion for general aviation Design of a transonically profiled wing [DGLB PAPEB 77-0<44] A78-211I33 [DG1B PAPEE 77-026] A78-21117 KBAOSPE, P. KIHZBT, B. t. The endangerment of flight safety due to wind shear An analysis of the influence of some external [DGLB PAPEB 77-062] A78-2U1Q8 disturbances on the aerodynamic stability of KB&VETS, V. ?. turbine engine axial flow fans and compressors Effect of a conical break of delta-wings on the S78-17051 aerodynamic characteristics KIND, B. J. A78-210811 An analysis method for the viscous flow over KBOC, B. circulation-controlled airfoils Condition monitoring experience on CF6 engines [AIAA PJPEE 78-157] A78-20710 [SAE PAPEB 77099Q] A78-23830 KINSLEY, V. 6. KBDTOV, V. I. The effect of fluid oscillations in a fuel line on The experimental determination of the parameters the pressure head of a pomp operating in a of a mathematical model of an aircraft passenger regime without reverse streams compartment as a control plant with respect to A78-24259 air temperature KlflG, B. F. A78-22652 Airframe noise, the lower noise limit for aircraft KDBLIB, 10. 1. [DGLH PAPEB 77-052] A78-2au<41 Taking into account the effect of elasticity of KINBEI, B. B. the structure on the longitudinal short-period Analysis of unsteady viscous flow past an airfoil. motion of an aircraft II - Numerical formulation and results A78-20882 A78-23185 KDLFA1, B. B. KIABBJH, A. P. Application of laminar flow control to large Evaluation of the extended use of ferrocene for subsonic military transport airplanes test cell smoke abatement engine and [AIAA EAPEB 78-95] A78-22571 environmental test results Beal flow limitations in supersonic airplane design [AD-AOq7659] B78-17C79 [AIAA EAPEB 78-1Q7] A78-22586 KLIBOVA, t. V. KOLIBV, V. D. The basic characteristics of the variation of Fatigue crack growth in a pressure-fuselage panel aerodynamic parameters in the transition region A78-22619 at hypersonic flew velocities KDLIKOV, A. I. A78-20900 Upgrading the carrying capacity of stretched KLDG, B.-6. panels with a stress-raiser rib by the technique Basic considerations concerning the possibilities of strain-compensating holes of wing families in civil aviation A78-20918 fDGlB PAFEB 77-029] A78-24120 KOBTSEVA, I. I. KRIVEL, t. IA. Investigation of the inclination of nozzle blades Simulation of the flight conditions in the on the alternating stress level in working ionosphere turbine blades A78-20915 A78-2I1273 KOFSKEI. B. G. KOBZBALS. P. B. Cold-air performance of a tip turbine designed to Integrity in flight control systems drive a lift fan. 3: Effect of simulated fan A78-23873 leakage on turbine performance KOSBBVEBSXII, S. K. [NASA-TP-11091 B78-16001 Upgrading the carrying capacity of stretched Cold-air performance cf free-power turbine panels with a stress-raiser rib by the technique designed for 112-kilowatt automotive gas-turbine of strain-compensating holes engine. 1: Design Statcr-vane-chord setting A78-20918 angle of 35 deg KOTIBOV, T. P. fNPSA-TP-1007] B78-16053 Upgrading the carrying capacity of stretched KOGAI, B. I. panels with a stress-raiser rib by the technique A formulation of the problem of the minimum-drag of strain-compensating holes wing A78-20918 \78-20867 KOLESRIKOV, A. V. Turbulent boundary layer en a moving surface A78-20850 LARAB, J. E. Subsonic vortex-flow design study for slender wings [AIAA EAPEE 78-154] A78-20708

B-9 LAB. C. E. EEBSOBil AOTBOB IBDEX

LAN, C. Z. 1OIGIEII, J. P. Minimum induced drag configurations with jet Alternative aircraft fuels interaction [NASS-TB-73836] S78-17229 [HASA-CB-155929] B78-17002 IOBEHZ, S. 1. LAHDEB, B. B. An investigation of lightning damage to t Future aviation turbine fuels nonnetallic composite aircraft materials and [AIAA PAPIB 78-268] A78-20781 associated protective systems LAHSIHG, 1. K78-17292 Applications of structural optinization for LODTBAI, J. D. strength and aeroelastic design requirements Impact of engine cycle parameters on 7/S10L Type A [AGABD-B-6611] N78-17018 configuration and commonality LABGE, J. I. [SAE PAPEB 770980] A78-23821 A critique of aircraft airframe cost models LOVE, B. 1. [AD-AO«7181] S78-16018 Method of fan sound mode structure determination LAWACZECK, 0. computer program user's manual: Hicrophone Contributions to steady and unsteady aercdynamics location program [DIE-PB-77-311] H78-17001 [HASA-CP-135291] S78-17065 LEE, E. S. B. Method of fan sound mode structure determination ERF response of aircraft antennas computer program user's manual: nodal A78-21992 calculation program Broad-band analysis of VIF/IF aircraft wire antennas [BASA-CB-135295] S78-17066 A78-21995 10DBIG. G. B. LELIDSBEBKO, S. I. Hind tunnel model study of the hot exhaust plume Determnation of the longitudinal lines cf an from the Compressor Research Facility at aircraft fuselage by the special-contour method iright-Patterson Air Force Base, Ohio A78-22610 [AD-A017205] S78-16072 LEBNEB, E. LOBA, G. S. Applications of structural optinization for An investigation into the nature of aircraft strength and aercelastic design requirements supportability in the CIIC environment [AGABD-B-661] B78-17C48 [AD-A017226] B78-15991 1EDTIB, S. G. 100, T.-S. Pressure distribution over sharp-nosed cones Method of calculating the compressible flow round situated at angles of attack from 0 to 1" an aerofoil or a cascade up to the sbeck free degrees in supersonic flow transonic range A78-20889 A78-23274 1EVI, L. I., JB. LTON, C. A. Steady and unsteady transonic flow Quiet propeller/rotor concept evaluation [AIAA FAIJF 78-160] A78-20713 [AD-A017297] N78-16017 1IKBTEB, V. 1. Electrical fluctuations in turbulent electrogasdynamic flows M A78-2236U BACCf.LI.OB, 8. B. L. LILLY, D. K. Transient expansion of the components of an air A severe dcwnslope windstorm and aircraft seal on a gas turbine disc turbulence event induced by a mountain vave [SAE PAPEE 770971] A78-23818 A78-24356 HACCBEADI, t. B. HBASE, C. B. Flight on 0.33 horsepower - The Gossamer Condor Development cf low pressure ratio vectoring [AIAA EAPEB 78-308] A78-21009 nozzles for V/STCL aircraft BACIOLEK, J. B. [SAE PAPEB 770988] A78-23825 Preliminary design study of an integrated tail lion, n. s. -rotor servo power module large amplitude shock vave notion in two '[AD-A017678] B78-17072 dimensicnal transonic channel flows BACKEBZIE, F. D. [AIAA PAPEE 78-217] A78-20770 Airport surface traffic control visual ground aids 1IPIH, E. K. engineering and development plan Taking structural and technological constraints [AD-A038153] B78-16037 into account in the design of ma*imum-stiffness BAEKAIA, S. load-bearing structures On some structure-turbulence interaction problems A78-20880 B78-15996 Determination of the stress-strain state in the MAKABEIICZ, B. end region of a stress-raiser rib The location of the ground focus line produced by A78-20917 a supersonic aircraft IID, T. K. A78-23H57 EMP response of aircraft antennas H&KAEOVA, B. T. A78-21992 Observational computation in the case of redundant HOTD-JOSBS, D. J. measurements Planning for the neit generation aircraft - An A78-23133 airline view K&LB01H, I. D. [AIAA PAPEB 78-361] A78-21033 Computational transonic airfoil design in free air I.OEBEBT, G. and a wind tunnel Wing with fcrk tips as means of increasing cost [AIAi EAPEB 78-103] A78-20685 effectiveness of transport aircraft BALVEBJ, D. [DGIB PAPEB 77-017] A78-21110 •Bew look' in assurance technology - 'The Hornet' I.OG&H, E., JB. [AIAA JAPEE 78-323] A78-21017 Preliminary comparison of model and prototype wakes flABDLE, B. J. [AIAA PAPEB 78-25(1] A78-2077U Twenty year evolution of the HB2/BB24 series of IOK&I, V. I. small turbojet engines Steady-state bulk temperature field in cooled [SAE PSPEE 770998] A78-23833 turbine blades BAHBSBDT, I. D. 478-21(156 An interaction solution algorithm for viscous Calculation of the thermal state of turbine blades aerodynamic performance prediction with film ceding [AISA EAPEB 78-153] A78-22589 A78-20.271 BABC01I, I. L08GEIBAKEB, I. E. A study of the inviscid flow about conically Frequency domain compensation of a DYHGEK tnrbofan cambered delta wings engine mcdel [AIAA fAPEE 78-58] A78-22561 A78-23890

B-10 PBBSOBAL AOTBOE IBDEI BOBAiSKI, J.

HABBSCA, C. BCTEE, A. C. An experimental study of three-dinensional Piloted flight simulator study of low-level wind characteristics cf propeller wakes under shear, phase 2 stalling conditions [AD-A017251] B78-16067 A78-21632 Piloted flight simulator study of low-level wind BABIB, 1. shear, phase 1 EBP response of aircraft antennas [AD-A017985] H78-17078 A78-21992 BEBDEBBALL, B. B. Bread-band analysis of V1F/1F aircraft wire antennas Further studies of aerodynamic loads at spin entry A78-21995 [AD-A017952] B78-17028 BABK, S. D. HEBBICK, V. E. Characterization of nonGaussian atmospheric Study of the application of an inplicit turbulence for prediction of aircraft response model-following flight controller to lift-fan statistics VIOL aircraft [NASA-CR-2913] H78-16011 [BASA-TP-1010] R78-16063 BABTIB. E. D. BEBBILL, I. C. A split-recoupled-semidirect compatational The application of the Bouth approximation method technique applied to transonic flow over lifting to turbofan engine models airfoils A78-23891 [AIAA PIPES 78-11] A78-22553 Design of turbofan engine controls using output HARTIB, J. A. feedback regulator theory Ramjet propulsion for single-stage-to-ortit vehicles A78-23907 [SAI PAEEE 771011] A78-23813 BBSSITEB, A. F. BABTIB. I. A. large amplitude shock wave motion in two Some applications of a test track for aerodynamic dimensional transonic channel flows testing [AIAA EAPEB 78-2U7] A78-20770 [AIAA PAPEB 78-167] A78-20719 BEIEB, B. C. BABVIB, J. 6. Configuration development of a supersonic cruise Steady and unsteady transonic flow strike-fighter [AIAA PSPEB 78-160] A78-20713 [AIAA PAPEB 78-118] A78-22587 HABYBIAlt, J. HICBEL, D. Lateral stability of a light aircraft during landing Bedncing aircraft noise through retrofitting A78-21020 [DGLH PAPEB 77-017] A78-2H36 RASLOV, E. I. Eecent advances concerning an understanding of Experimental investigation of asymmetric Laval sound transmission through engine nozzles and jets nozzles [DGLB EAPEB 77-018] A78-21P37 A78-22361 HIKBAI10V, A. A. BASIOW, I. A. A study of the influence of slits on the Calculation of the flow past a fuselage of effectiveness of wing mechanization and controls arbitrary configuration at low velocities in separated flow A78-208115 A78-22617 HATBESOS. B. BIKKI1IIE1I, B. P. Stability of helicopter slung leads The analysis of wing-body combinations at moderate [AEI/AEBC-HOTE-361] B78-16010 angles of attack HATS, B. A. [AIAA PAPEB 78-62] A78-20663 Fuels outlook I - Transportation and the D.S. HILLEB, B. P. petroleum resource, an aviation perspective Fuels outlook I - Transportation and the O.S. [AIAA PBPEB 78-357] A78-2I4032 petroleum resource, an aviation perspective BAZOBOV, A. F. [AIAA PAPEB 78-357] A78-21032 Calculation of the laval-nozzle flow by a modified HILLEB, B. I. Lax-Wendroff method of second-order accuracy Arrival inspections/pre-operational inspections A78-20970 (aviation materiel) HCALISTEB, K. I. [AD-A017260] B78-16376 Dynamic stall experiments on the NACA 0012 airfoil HIBAILOS, A. B. [HASA-TP-1100] N78-17COO Interaction of a shock wave with an entropy layer BCABDLE, J. C. 478-20886 Development and test of an inlet and duct to Inviscid supersonic flow about a thin rectangular provide airflow for a wing boundary layer plate control system A78-20906 [AIAA PAPEB 78-1U1] A78-20701 Supersonic flow near a thin trapezoidal wing HCCABTHT, J. A78-20921 Effect of wind turbulence and shear on landing Effect of the thickness of profile and trailing performance cf jet transports edge on the flow field and the aerodynamic [AIAA PAPEE 78-2U9] A78-20771 characteristics of a low-aspect-ratio delta wing BCCBOSKET, 1. J. at B = 3 Dynamic stall experiments en the BACA 0012 airfoil A78-20919 [BASA-TE-1100] N78-17000 BIBABDA, 1. B. BCDOBALD, I. A generalized vortex lattice method for subsonic Noise transmission into a light aircraft and supersonic flow applications [AIAA PAPEF 78-197] A78-20739 [BASA-CB-2865] H78-16002 BCFAEIABD, A. HODLIB6EB, A. Initial collision avoidance algorithms for the Mission management in the airport vicinity beacon-based collision avoidance system [DGLB IAPEB 77-037] A78-21127 [AD-A017251] B78-16C31 HOBAKBOV, I. B. BCGOiAB, J. A. Uniformly precise conformal mapping of the Expansion of flight simulator capability for study exterior of a circle onto the exterior of a wing and solution of aircraft directional control section problems on runways, appendixes A78-22612 [BASA-CR-115281] B78-16066 BOHTA, B. J. BCGBBGOE, B. B. Longitudinal aerodynamic characteristics at Bach Quiet propeller/rotor concept evaluation 0.60 to 2.86 of a fighter configuration with [AE-A017297] B78-16017 strut traced wing BCKIBZIE, L. J., JB. [BASA-TP-1102] B78-16000 EBF noise suppression and aerodynamic penalties BOBAISXI, 3. [AIAA PAPEB 78-200] A78-20763 Systems analysis of safety in aviation. I BCLOCAS, J. I. A78-23170 Prospects for a new generation air transport [AIAA PAPIB 78-363] A78-21035

B-11 HOBISSBT, J. PBBSOBA1 AOTBOB IBDBX

HOBISSET, J. BOSBAOB, I. J. Aerospatiale is read; to develop a convertiplane Cold-air performance of free-power turbine with tethering rotors designed for 112-kilowatt automotive gas-turbine [HASA-TB-75038] B78-17012 engine. 1: Design Stator-vane-chord setting BOBBOB, J. angle of 35 deg Automated DBF frequency assignment system for FAA [BASA-TP-1007] B78-16053 air traffic control communications [AD-A017817] H78-17031I HOSES, I. I. Assessment of the performance of an active ATCBBS OBEBSOH, B. J-. JB. mode for beacon collision avoidance Fracture analysis of aerospace metals [AD-A01767C] H78-16032 A78-2272U HOB, D. F. OHISOB, 3. VSTOL - Can Havy needs be net Flight testing an 8000 psi lightweight Hydraulic [AIAA PAPEB 78-322] A78-2H016 System HOZOIKOV, A. S. [SAE PAPEB 771007] A78-23839 Determination of airfoil lift from pressure OLSEB, B. I. measurement at the test section vails in a 7U7 Shuttle Carrier Aircraft/Space Shuttle Orbiter subsonic wind-tunnel mated ground vibration test - Data via transient A78-20973 excitation and fast Fourier transform analysis [SAE PAPEB 770970] A78-23815 OBELU, A. I. N Simulation of the flight conditions in the HAIK, S. I. ionosphere An analytical model for the study of highly A78-20915 separated flew on Ion speed airfoils OB10FF, K. I. N78-16995 Laser-velocimeter surveys of merging vortices in a NAPPI, A. wind tunnel An introduction to the problem of dynamic [AIAA PAPEB 78-107] A78-20687 structural damping OB107SRAIA, E. KB. [AGABD-B-663] U78-17071 Flow visualization in the region of intersection HABKIS, t. of aerodynamic surfaces Deployment forces in toning systems A78-20951 178-211365 OBB, B. BAUDASCHEB. E. The Single-Site Collision Avoidance System (SS-CAS) The low-speed air tunnel cf the Institute of [AD-AOH5977] B78-16035 Bydromecbanics at the University of Karlsruhe OSIPOV, V. A. A78-23297 Analysis and calculation of plane skew symmetric BESTEB07, E. D. contours of seccnd-order smoothness Statistical evaluation of the effect of a jet A78-22636 reverser on the parameters of a turbofan engine OSTAPEHKO, I. A. in the direct thrust regime Hypersonic flow past a conical wing with detached A78-2H275 shock wave at the leading edges BBDBAUEB, B. A78-22078 Flowfield and pressure field of a model propeller OSTGAABD, B. A. A78-2I1II51 Technical evaluation report on the Avionics HEDIIEB, B. I. Panel/Guidance and Control Panel Joint Symposium Including fleet usage variability in reliability on Avionics/Guidance and Control for Bemotely analyses for both safety and economic limit Piloted Vehicles (BPVs) [AD-AOQ771

B-12 PEBSOIAl AOTBOE IBDEI BODI, 1.

PilTEESOB. J. I. 4erodynamic beating to the hypersonic research aircraft, I-2qc Q [AIAA PAPEE 78-37] A78-20617 OOIBB, B. PATOBSKI. Z. Trends and research opportunities in airbreathing Lateral stability of a light aircraft daring landing propulsion 478-21020 [AIAA IAPEB 78-00] A78-20C52 PECB, B. In-state delivery and reinforcement of rigid airport causeways - Some technical problems and attempts using special coatings BADCHEHKO, 4. I. A78-21375 iiruorthiness criteria for aluminum alloy covering PEDLET. E. nitb uniform corrosion damage Measured wake-vortex characteristics of aircraft 478-22737 in ground effect BADOVCICB. B. A. [4141 P4PE8 78-109] A78-22S78 Arrov viogs for supersonic craise aircraft PEITIU, B. [AIAA fAPEB 78-151] A78-22588 Aircraft attitude measurement using a vector B6BACBAHDBA. S. B. magnetometer On some singular acoustic signatures observed in [SASA-CB-155S65] H78-17C50 the cockpit of a tvin engined jet aircraft PEB1ABD, J. A. [AIAA IAPEE 78-212] A78-20765 An aerodynamic analysis of several hypersonic BABSDBB, J. B. research airplane concepts from H = 0.2 to 6.0 The collision risk [AIAA PAPEf 78-150] A78-20706 A78-22851 PBBEPOKBOV, V. A. BASTOGI. A. R. Calculation of the flow cf a rarefied gas past a Calculation of general three-dimensional turbulent plate of infinite span boundary layers 478-20657 A78-23188 PBBBIBOV, V. D. BEBOHT, J. A formulation of the problem of the minimun-drag An experimental study of three-dimensional ving characteristics of propeller wakes under 478-20867 stalling conditions PETBBS, L., OB. A78-21632 Surface current and charge density induced on BEDIHG, J. P. aircraft Reynolds number criticality in dynamic tests 478-21990 [AIAA PAPEB 78-166] A78-20718 PBTTIGHBI, J. I. BBBPFBB, P. S. TF-30-P-7 installed trim correction Airport surface traffic control TAGS planning UD-A047023] B78-16058 alternatives and cost/benefit analysis PFIZENHAIEB, E. [AD-A037790] B78-16038 Bedncing aircraft noise through retrofitting Preliminary limited surveillance radar (LSR) [DGI.B PAPEE 77-017] A78-21136 cost/benefit analysis Recent advances concerning an understanding of [AD-A006829] 1178-16215 sound transnission through engine nozzles and jets BBTTIE, I. B. [DGLB PAPIB 77-018] 478-24137 The impact of emerging technologies on tactical PICKEM, 6. t. V/STCL airplane design and utility Hethod of fan sound mode structure determination [SAE PAPEB 770985] A78-23821 rNASA-CB-135293] H78-17C61 BBOAOES, 1. 1. Method of fan sound mode structure determination A combined potential and viscous flov solution for computer program user's manual: Microphone V/STOL engine inlets location program [AIAA PAPEB 78-112] A78-20702 [SASA-CB-135291] H78-17065 BIABCBBBKO, V. P. Method of fan sound mode structure determination Successive-approximation calculation of a steady computer program user's iranual: Modal subsonic gas flow about an airfoil lattice calculation program A78-20085 [HASA-CB-135295] S78-17C66 BIABOV, V. V. PIEBZGA, I. J. The basic characteristics of the variation of A solution to the direct problem of an open aerodynamic parameters in the transition region propeller using the streamline curvature method at hypersonic flon velocities [AIAA PAPEB 78-310] A78-21011 A78-20900 PIHCKBBY, S. Z. BIBBBB, B. S. Internal performance predictions for Langley Two point correlations of jet noise scramjet engine module A78-23219 [HASA-TB-I-71038] H78-17057 BICBABDSOI. S. A. P1T1BSB, J. I. An analysis of user acceptance and perceived An aerodynamic analysis of several hypersonic usability of C-111A job guides research airplane concepts from B = 0.2 to 6.0 [AD-A017101] H78-15992 [4144 PAPEB 78-150] A78-20706 BIEGEIS, E. B. FIAKBOV4, I. I. Contributions to steady and unsteady aerodynamics Statistical evaluation of the effect of a jet [B1B-PB-77-31] S78-17000 reverser on the parameters of a torbofan engine BIGGS. 1. I., JB. in the direct thrust regime Aircraft compensator design methods A78-21275 [AD-A017810] H78-17073 PLOTKIS. 4. BISTBB, S. C. Bigh-frequency approximation for a nonlifting thin Spectrum crack growth in adhesively bonded structure airfoil in subsonic flo* [ASBI PAPEB 77-SA/BAT-7] A78-23372 fAIAf P^FEB 78-226] A78-20755 BOBBCE. P. B. POLIABD, G. D. Proposed technical characteristics for the Toiicologic gas evaluation of the utility tactical Discrete Address Beacon System (DAES) transport aircrait systei (OB-60) [AD-A018246] B78-17035 rBD-4017801] H78-17046 BOBEBTS, A. S. POPOf, P. D. Analysis of spread multi-jet VTOL aircraft in hover Calculation of the three-dimensicnal supersonic (SASA-CB-155582] B78-16016 viscous heat-conducting gas flov past blunted BODI, 1. bodies Calculation of general three-dimensional turbulent 478-21096 boundary layers POTREEB, B. B. A78-23188 Censor failure detection using analytical redundancy A78-23862

B-13 BOGBBS, D. 8. PEBSOBAL AOTBOB IBDEI

BOGEBS, D. W. SCBHIDT, E. The effect of ambient conditions on the emissions Unsteady pressure distribution measurements at two of an idling gas turbine trapezoidal winqs with unit aspect ratio [AIAA PAPEE 78-3] 878-22551 H78-17020 BOGOZIH, ID. A. SCBOCBBAB. I. Modeling the influence of the gronnd effect on the The Single-Site Collision Avoidance System (SS-CAS) aerodynamic characteristics of a ving by means [AD-AOU5977] S78-16035 of a flat screen of finite dimensions SCBDLZ. 6. A78-22631 Influence of gust aodelling on the identification BOLIIHS, J. of the derivatives of the longitudinal motion of Experimental relationships between modali for soil an aircraft layers beneath concrete pavements [BAE-LIE-f BANS-19UI1] B78-17071 [AD-A016239/0] H78-16C68 SCBOBAKEB, B. I. BU6IBHIOS, 1. V. Toxicologic gas evaluation of the utility tactical The dissection of an aircraft loads spectrum transport aircraft system (OH-60) produced fcy peak-connting accelerometers [&D-A017801] B78-170Q6 ClTB-ST-951] H78-16391 SCBRABBAII, 1. BUSHAI1O, A. B. Dse of the finite element method in fracture Electrical flnctnations in tnrhnlent mechanics electrogasdynamic flows [DGIB PAPEE 77-055] S78-21113 A78-22361 SCBIEITZEB, K. BOSSEll, B. B. Application of skin technology to turbine blades Design study of a centerplate mount for wind [AIAA PAPEB 78-285] A78-20792 tunnel ncdels SCBIEBS, J. C. CAD-A017201] B78-16073 General aviation avionics statistics: 1971 BYLOV, 10. P. [AD-A04520S] 1178-16050 Experimental investigation of the characteristics SBBASTIAI, J. D. of snail-sized nozzles The practical application of a finite difference A78-2 090 method for analyzing transonic flow over BZECZIBSKI, B. oscillating airfoils and wings Airports for short takeoff and landing [NASA-CB-2933] S78-16999 A78-23171 SEEGBII1EB, B. L. Steady and unsteady transonic flow [AIAA FAPEE 78-160] S78-20713 SEBEBBIISRII. IA. B. SMB. H. t. Approximate method of calculating the lifting Freguency domain compensation of a DYNGEN tnrbofan force and the longitudinal moment of an airfoil engine model section at low velocities with allowance for A78-23890 viscosity SALZBABB, A. B. A78-20819 Airborne electronic warfare in the modern military SETCIR, R. B. force in analytical study of thermal barrier coated [AIAA PAPEB 78-320] A78-21018 first stage blades in a JT9D engine SABABI, S. S. [HASA-CB-135360] B78-16051 An improved method cf calculating the tip vortex SHAGABT, A. A. geometry for hovering rotors Approximate method of calculating subsonic H78-15997 compressible flows past a lifting wing profile SAHPATH, S. A78-20883 A numerical study of incompressible viscous flow SBAHADI, P. A. around airfoils Quiet propeller/rotor concept evaluation B78-16996 [AD-AOH7297] B78-16C17 SABDDBA, S. T. SBAIKBOTDIROV. Z. G. Mechanism of wear in helicopter hydraulic systems Thrust characteristics of thrust vector control A78-231I39 systems with blowing injection of chemically SAD BIGOE1, 1. nonreactive gases Antimisting fuel kinematics related to aircraft A78-2U25U crash landings SHABKAB, V. CAIAA PAPEB 78-270] A78-20783 Computational transonic airfoil design in free air SAHDEBS, D. t. and a wind tunnel An examination of selected digital flight generators [AIAA PAPEB 78-103] A78-20685 [AD-A017815] H78-17081 SBCHEBBAKOV, A. T. SABGIOBGIO, G. The experimental deternination of the parameters longitudinal aerodynamic characteristics at Bach of a mathematical model of an aircraft passenger 0.60 to 2.86 of a fighter configuration with compartment as a control plant with respect to strut braced wing air temperature [HASA-TP-1102] B78-16000 A78-22652 SABTIBI, P., SBCBOKIB, A. T. An introduction to the problem of dynamic Calculation of the thermal state of turbine blades structural damping with film ccoling [iGABD-B-663] H78-1707U A78-2127U SAPIBO, D. H. SBEOBAH, I. Aircraft electrical equipment Stress analysis study in cooled radial inflow A78-21175 turbine SABAEDD1A, H. B. [AIAA PAPEB 78-91] A78-22570 Effect of wind turbulence and shear on landing SBIEHBOB, L. I. performance of jet transports Friction and wear of sintered fibermetal abradable tAIAA P6PIB 78-219] A78-20771 seal materials SABEB. V. E. A78-23151 Perturbing forces in the hydrodynamic interaction SBISBKOV, A. A. of thin-blade cascades in a potential flow Experimental investigation of asymmetric Laval A78-21219 nozzles SCBAFIB, B. B. A78-22361 Frequency domain compensation of a DYBGER turbofan SHTEIBBEBG, B. I. engine model The effect of blunting the leading edge of a delta A78-23890 wing on its aerodynamic characteristics during SCHEtZ, J. A. supersonic flight The flow about a slender propeller-driven tody in A78-20920 a temperature stratified fluid TAIAA PAPEB 78-209] A78-207«e PBBSOBJL AOtBOB IBDBI STOIBB, B. I.

SBOLGIH, V. I. SPAB6. B. A., Ill Electrical fluctuations in turbulent Failure detection and correction for turbofan electrogasdycanic flews engines 178-22361 J78-2391S SBOBG. T. t. SPABGIEB, S. B. Numerical solution for some problems concerning Further studies of aerodynamic loads at spin entry unsteady jotion cf airfcils [AD-A0117952] B78-17028 K78-15995 SPEBCBB, I. 1. SBTBTS, 4. I. Assessment of the performance of an active ATCBES Effect of a conical break cf delta-wings on the mode for beacon collision avoidance aerodynamic characteristics [AD-A017670] B78-16032 A78-21080 SPBEHGEB, B. SICLABI, I. J. Application of skin technology to torbine blades A study of the inviscid flew about conically [AIAA PAPEB 78-285] A78-20792 cambered delta wings SPBIBGSTOB, F. S. FAIAA PAPEB 78-58] A78-22S61 Experimental relationships between aoduli for soil SIGSL1A, 1. layers beneath concrete pavements Real flow Imitations it supersonic airplane design [4D-A0116239/0] B78-16068 [AIAJ PAPEB 78-117] A78-22586 SEIDBAB, B. SIBKIB, E. i. Eobustness of linear quadratic state feedback Statistical evaluation of the effect of a jet designs in the presence of system uncertainty reverser on the parameters of a turbofan engine A78-23917 in the direct thrust regime SBI?iSTA»A, 6. P. A78-2Q275 A digital continuously updated two minute mean SIBAZETDISOV, t. K. vindspeed indicator for use at airports Dynamic model of a systen of scientific research B78-17598 and industrial plants A current weather information display system for A78-226B5 use at airports SISIO. F. B78-17600 Research on the flutter of axial-torboaachine STACK, S. B. blading GEBP&K: An arbitrary aircraft geometry generator [AD-AO<17C86] H78-16021 [B&SA-1P-1022] 1178-16042 SliTBB. E. L. SIABB, B. F. Optimal controls fcr an advanced tnrbcfan engine Experimental observations of wall interference at A78-23893 transonic speeds StAVIABOV, S. B. [ilAA EAPEB 78-160] A78-20716 Telocity profiles in the laval nozzle throat for STASCBRE. J. uniform compressible swirling flov Kechanism of wear in helicopter hydraulic systems A78-20905 A78-23039 SUSHI, B. J. STAOD1CHEB, B. Aerodynamic heating to the hypersonic research Bings with controlled separation aircraft. X-20C [DGLB PAPEB 77-028] A78-2U019 [AIAA PAPIS 78-37] A78-206H7 STBFABOV, B. I. StI?IBSKT, C. J. Fatigue of AHg6H sheet with Sprut 5H and VAX Approaches to improving aircraft efficiency coatings in the linear and plane states of [AIAA PAPEB 78-305] A78-2U007 stress under high-frequency loads StOBODIABIDK, I. I. A78-22108 The start-up of a gas turbine engine using STBIBBBB6, B. compressed air tangentially fed onto the blades Automated meteorological data from commercial of the basic turbine aircraft via satellite: Present experience and A78-20119 future implications SHALL, B. J. [BASA-TH-73750] B78-17558 GEHPAK: An arbitrary aircraft geometry generator STBI1IBGBE, B. [BASA-TP-1022] H78-16002 New methods for flight vibration studies SBITB, C. T. CDGLB PAPEB 77-050] A78-20039 An evaluation of the capability of the logistics STBBS, J. t. composite model to project the monthly aircraft The challenge of advanced fuel-conservative sortie effectiveness of an P-15 ving aircraft - A manufacturer's view [AD-A007227] B78-15993 [AIAA EAPEE 78-362] A78-2M030 SBITB, B. I. STEBABT, I. t. Engine development toward lover energy consumption A review of BASA's propulsion programs for civil and reduced environmental impact aviation [AIAA PAPEB 78-307] A78-20008 [AIAA PAPEB 78-«3] A78-20651 SniTH, B. G., JE. A review of BASA's propulsion programs for aviation Advanced supersonic transport propulsion systems [BASA-TH-73831] H78-16055 [Si* PAEJB 771010] A78-23802 ST1EE, B. A. SBOLICZ, t. Sn investigation into the nature of aircraft Systems analysis of safety in aviation. I snpportability in the CILC environment A78-231170 [AD-A017226] H78-15991 SBTTB, B. SIOCKBAI, B. 0. Special problems in the development of the A combined potential and viscous flow solution for propulsion system for an over-the-wing engine V/STCL engine inlets configuration [AIAA PAPEE 78-102] A78-20702 [DG1E PJPEB 77-006] A78-20035 STOLE, P. C. SBTDEB. I. S. Advanced turboprop propulsion system reliability Conceptual design of single turbofan engine and maintenance cost powered light aircraft [SAE PAPEB 771009] A78-23801 [NtSA-CE-151972] N78-16005 STOBE, 1. L. SOPBIB, T. 6. Bumerical solution for airfoils near stall in nethod of fan sound mode structure determination optimized boundary-fitted curvilinear coordinates [BASA-CB-135293] B78-17060 [AIAA PAPEB 78-280] A78-2C791 SODTBAH, J. t. STOBB, B. B. Feasibility study of an Integrated Program for Service experience of composite parts on the Aerospace vehicle Design (IPAD). Volume S: L-1011 and C-130 Catalog of IFAD technical program elements A78-2Q508 [H4SA-CB-132395] H78-16015 STOBEB, B. I. SPABEB. T. An analytical study of thermal barrier coated Spectrum crack growth in adhesively bonded structure first stage blades in a JT9D engine [ASBE PAtEF 77-8A/BHT-7] A78-23372 [BASA-CB-135360] B78-16050

B-15 STBEB1, H. EBBSOFAL AOTBOB IHDEI

STEEBl, B. TBBEB, P. Glass-fiber data bus systems for signal Hinimum-time acceleration of aircraft tnrbofan transmission en toard engines A78-21976 A78-23892 STBOBKIB, V. 1. Seluticn of transient optimization problems by Investigation of the inclination of nozzle blades using an algorithm based on nonlinear programming on the alternating stress level in working A78-23909 turbine tlades TESKB, H. B. A78-2H273 The role of atmospheric shear, turbulence and a STDLOV, Y. P. ground plane on the dissipation of aircraft Boundary layers in dissipative media vortex wakes 478-22091 [AIAA FAPBB 78-110] A78-22579 SOBBSBABIJB, B. K. THEBS, J. The effect of ambient conditions en the emissions Study of a supercritical profile with oscillating of an idling gas turbine control surface in sub- and transonic flows [AIAfl PAPEB 78-3] A78-22551 [OBEEA, TP HO. 1977-136] A78-24168 SOGIYABA, T. THIBEBT, J.-J. A study on the mechanisn cf compressor surge due A new airfoil family for rotor blades to inlet pressure disturbances [ONEBA, TP NO. 1977-113] A78-2ltU63 CAIAA PAPEB 78-2U6] A78-20769 TBOBAS, I. B. SDLTASOV, A. E. A clutch for V/STOL Airworthiness criteria for aluminum alley covering [SAE PAPEB 770989] A78-23826 with uniform corrosion damage TIBOCO, E. B. A78-22737 Transonic computational design modifications of SDBKA, G. E. the F-111 TACT Conversion of an automotive engine for aircraft [AIAA PAPEB 78-106] A78-22577 application TODA, B. [AIAA PAPEB 78-309] A78-21010 Bobnstness of linear quadratic state feedback SOBHBBFOBD, J. I. designs in the presence of system uncertainty Variable speed constant frequency /VSCF/ aircraft A78-23917 electrical pover TOBASZEiICZ, J. [SAE PAPEB 771002] A78-23836 Application of light-emitting diodes /LEDs/ in SOTTOH, B. C. aircraft analog indicators The inpact of emerging technologies on tactical A78-23059 V/ST01 airplane design aid utility TOBSHIB, V. K. tSAE PAPEB 770985] A78-23824 Organization of a programmed matrix-operation SWEAH, I. t., 33. system in an airborne digital computer The flow about a slender propeller-driven bcdy in A78-2tS85 a temperature stratified fluid TBACBOK, V. S. [AIAA PAPEB 78-209] A78-20716 Elastic deformations of rapidly-rotating prismatic SYBBB6, J. mirrors low speed test of a high-bypass-ratio propulsion A78-21374 system with an asymmetric inlet designed for a TBABOVICH, V. A. tilt-nacelle V/STOL airplane Solving the problem of numerical construction of a [NASA-CB-152072] N78-17062 model of similar rigidity to the initial SYSTEB, T. B. structure as a problem of quadratic programming An analysis of user acceptance and perceived A78-20864 usability of C-111A job guides TDBB, D. G. [AD-A0471111] H78-15992 Specifications for IDAHST software [AD-AO»7163] H78-1601I9 TOBHEB, B. J. Study of metallic structural design concepts for TABAFOFF, I. an arrow wing supersonic cruise configuration A study on the mechaniSD of compressor surge due [HASA-CB-27113] N78-16013 to inlet pressure disturbances fAIAA PAPEF 78-2(16] A78-20769 Stress analysis study in ccoled radial inflow u turbine OCBIIAHA, B. [AIAA PAPEB 78-911] A78-22570 The analysis of wing-body combinations at moderate Optimization stady for high speed radial turbine angles cf attack with special reference to design variables [AIAA PAPEB 78-62] A78-20663 [BASA-CB-152091] H78-17C63 TAGIBCY, B. K. Computation of the base pressure in elector V nozzles of different length with zero TACHAI, J. D. coefficient cf ejecticn Application of laminar flow control to large A78-21098 subsonic military transport airplanes Til. T. C. [AIAA FAPEB 78-95] A78-22571 Theoretical aspects of droiedaryfoil VABL, I. 1. [AD-A007150] H78-16023 Study of heat sink thermal protection systems for TAETiGLIOIE, J. J. hypersonic research aircraft An analysis of the aircraft trailing vortex system [AIAA PAPEB 78-38] A78-206<48 [AIAA PAFIB 78-312] A78-21013 VAICSITIS, B. TATIOB, C. D. noise transmission into a light aircraft External interaction of the nuclear EBP with [AIAA IAPEB 78-197] A78-20739 aircraft and missiles VAILIABT, B. A78-21989 Prediction of the ascending speeds of- gliders in TATIOB, C. H. thermal convection over a plain Temperature distributions and thermal stresses in A78-23398 a graded zircoria/metal gas path seal system for VALIABV, V. I. aircraft gas turbine engines Approximate wind-tunnel simulation of the dynamics [AIAA PAPEB 78-93] A78-20683 of a system composed of a body with a trailing TAYLOB, J. cable Atmospheric turbulence loads on aircraft A78-20902 A78-230I19 VATAZBIH, 1. B. TATLOS, B. 1. Electrical fluctuations in turbulent Applications of structural optimization for electrogasdynamic flows strength and aercelastic design requirements A78-2236H [AGABD-B-66Q] H78-17018

B-16 PEBSOBAL JDTBOB IJDBI SBIGHT, B. B.

r, B. B. BA7EBS, S. t. Technical evaluation report on the Flight Besearch requirements to improve safety of civil Mechanics Panel Symposium on rotorcraft Design helicopters [AGABD-AB-114] H78-17049 [BASA-CB-14S620] B78-16026 VEBOGOPAl, G. IEATBEBI11, 1. B. A digital continuously updated two minute mean the practical application of a finite difference vindspeed indicator for use at airports method for analyzing transonic flow over B78-17598 oscillating airfoils and wings A current leather information display system for [BASA-CB-2933] B78-16999 use at airports iEBEB, B. 3. N78-17600 A review of BASA's propulsion programs for civil VBSTIAF, A. V. aviation Stress-strain state of simply-supported [AIAA EAEEB 78-43] A78-20651 three-layer trapezoidal plates A review of BASA's propulsion programs for aviation A78-21205 [BASA-1H-73831] B78-16055 VIKTOBOV, B. V. IEIDIEB, 3. F. Ose of the singular perturbation method to The application of dual fuel /JP-IH2/ for investigate automatic control systems hypersonic cruise vehicles A78-20802 [AIAA FAPEB 78-149] A78-2070S VISOGBADOV, B. S. SEISE, K. Thrust characteristics of thrust vector control From analog to digital control systems - Improved systems iiith bloving injection of chemically performance by means of advanced technology nonreactive gases [DGLB EAFEB 77-036] A78-24426 A78-21254 RELCB, 3. D. VOIHIB, i. S. Proposed technical characteristics for the Outline of aeroelastic phenomena Discrete Address Beacon System (DABS) H78-17003 [AD-A048246] H78-17035 700BBBES, C. G. IE11S, B. 1. Conceptual design of single turbofan engine Hethod of fan sound mode structure determination powered light aircraft computer program user's manual: Microphone [NASA-CB-151972] B78-16045 location program VOBOHI1I, V. 6. [HASJ-CB-135290] H78-17065 The experimental determination of the parameters flethod of fan sound node structure determination of a mathematical model ef an aircraft passenger computer program user's manual: Modal compartment as a control plant with respect to calculation program air temperature [NASA-CB-135295] H78-17066 A78-22652 SELLS, B. 1. VBOBSEII, G. V. Hethod of fan sound mode structure determination Ose of a fast Fourier transformation and the Monte [BASA-CB-135293] H78-1706I! Carlo method to calculate repeatibilitj of load SELLS, I. B. and fatigue damage of aircraft structural Detection of sensor failure and output elements under vibration excited by external reconstruction for aircraft engine controls stationary random loads [AIAA IAEEB 78-

B-17 «n, J. SBBSOHAL ABIBOB ISCBI

HO. J. H. The analysis of wing-body combinations at moderate angles cf attack [AIAA PAPEE 18-62] 418-20663

TAO, S. Filament-winding fabricaticn of CCSEE configuration fan blades [HASA-CE-135332] H78-16C52 YAIES, J. E. Viscons than airfoil theory and the Kotta condition fAIAJ PAPEE 78-152] A78-20707 TBABBI, A. H. A combined potential and viscous flow solntion for VSTCL engine inlets [AIAA PAPEB 78-1

ZABDIA, 6. I. Economical method for calculating unsteady temperature fields in thin-«alled aircraft structures A78-20903 ZB1EV, T. P. Analysis and calculation cf plane skew symmetric contours of second-order smoothness A78-22636 ZHESTKOV, B. E. Simulation of the flight conditions in the ionosphere B78-20915 ZIHHEB, B. The significance of ving end configuration in airfoil design for civil aviation aircraft [DGIE PAPIE 77-030] A78-2U1121 ZLOCKA, B. Lateral stability of a light aircraft during landing A78-21020 ZOCCOtI, H. J. Advanced scavenge systems for an integrated engine inlet particle separator [AD-A017872] S78-17069 ZOLA, C. L. Preliminary study cf propulsion systems and airplane wing parameters for a US Navy subsonic V/STCL aircraft [BASA-TB-73652] H78-17C41

B-18 CONTRACT NUMBER INDEX

AERONAUTICAL ENGINEERING /A Continuing Bibliography fSuppI 96) MAY 1978

typical v^oniract raumoer maex Listing BSF EB6-73-03855-A01 A78-23185 SSF EBG-75-22322 BASR-2183 H78-11061 A78-23890 BSF GK-15251 A78-21635 HSF GK-12991 A78-2Q025 CONTRACT NASA ACCESSION BSG-1139 878-17002 NUMBER NUMBER BSG-1213 B78-16061 BSG-1318 A78-22556 HSG-30H5 A78-22551 RSG-3flq8 A78-23890 Listings in this index are arranged alphanumencally by contract number B0019-76-C-0135 Under each contract number the accession numbers denoting documents A78-20770 that have been produced as a result of research done under that contract B00011-71I-C-0311 are arranged in ascending order with the IAA accession numbers appearing S78-17028 first The accession number denotes the number by which the citation is B00011-75-C-11113 identified in either the IAA or STAR section 878-16056 B00011-76-C-0120 178-23883 fF-AIOSB-71-2659 F33615-77-C-3126 H00011-76-C-0540 H78-2U022 A78-22561 B78-16021 AF-AFOSB-7U-2675 FQU620-6-C-OOI4IJ B00011-76-C-0576 '78-20756 178-20685 A78-20707 AF-AIOSB-75-2808E F«llt620-73-C-OOil1 S00600-76-C-1H91 78-23219 A78-20757 A78-20710 DA PEOJ. 1F2-62209-AH-76 pa9620-76-C-0037 H61339-76-C-0031 N78-17080 A78-23900 878-17082 DAAG29-77-G-0'08 FH9620-77-C-0023 PBOJ. SQDID 878-16056 •78-20663 H78-160P8 BF11IH1801 B78-17028 DUJ01-73-C-0781 BASA OBDEB A-36079-E (IS) BB02302001 B78-16023 A78-23139 878-17931 SBI PBOJ. 1361 DA4J02-C-0031 NASW-2790 H78-16051 878-17078 178-23831 B78-17053 BI-77-3683-1 878-16059 DAAJ02-75-C-0026 BASS-2792 B78-17012 505-05 878-16001 N78-17069 8ASH-3075 S78-17915 505-05-11-08 B78-17057 DA4J02-76-C-0037 RAS1-11««1 B78-16015 505-10-32 B78-16063 N78-17080 HAS1-11707 N78-160U6 505-10-11-01 878-15999 DAAJ02-76-C-0056 BAS1-12185 A78-20762 505-11-21-03 878-16000 B78-17072 BAS1-12287 B78-160a3 505-11-31-02 B78-16012 DFV1B-01-Q7-276-ZK-SNS-SIN NAS1-12972 S78-16002 505-11-11 H78-16062 A78-20792 BAS1-13621 B78-16026 DOT-FA69BS-162 BAS1-13795 878-16003 B78-16031 B78-16998 N78-16032 BAS1-13981 878-16066 DOT-FA70SAI-175 HAS1-1H005 878-17037 B78-17031 BAS1-1

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. 20546 13 Type of Report and Period Covered 12 Sponsoring Agency Name and Address

14 Sponsoring Agency Code

15 Supplementary Notes

16 Abstract

This bibliography lists 448 reports, articles, and other documents introduced into the NASA scientific and technical information system in April 1978.

17 Key Words (Suggested by Author(s)) Aerodynamics 18 Distribution Statement Aeronautical Engineering Aeronaut ics Unclassified - Unlimited Bibliography

19 Security Oassif (of this report) 20 Security Classif (of this page) 21 No of Pages 22 Price' Unclass if ied Unclass ified 132 $4.75 HC

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NASA CONTINUING BIBLIOGRAPHY SERIES

NUMBER TITLE FREQUENCY

NASA SP-7011 AEROSPACE MEDICINE AND BIOLOGY Monthly Aviation medicine; space medicine, and space biology

NASA SP-7037 AERONAUTICAL ENGINEERING Monthly Engineering, design, and operation of aircraft and aircraft components

NASA SP-7039 NASA PATENT ABSTRACTS BIBLIOGRAPHY Semiannually NASA patents and applications for patent

NASA SP-7041 EARTH RESOURCES Quarterly Remote sensing of earth resources by aircraft and spacecraft

NASA SP-7043 ENERGY Quarterly Energy sources, solar energy, energy conversion, transport, and storage

NASA SP-7500 MANAGEMENT Annually Program, contract, and personnel management, and management techniques

Details on the availability of these publications may be obtained from:

SCIENTIFIC AND TECHNICAL INFORMATION OFFICE

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

Washington, D.C. 20546