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Wind Tunnel Wall Interference in V/STOL and High Lift Testing

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Wind Tunnel Wall Interference in V/STOL and High Lift Testing Wind Tunnel Wall Interference in V/STOL and High Lift Testing A SeZected, AItnotuted BibZiogi-u$v5y Marie H. Tuttle, Raymond E. Mineck, and Karen L. Cole DECEiMBER 1086 NASA Technical Memorandum 89066 Wind Tunnel Wall Interference in V/STOL and High Lift Testing A SeZected, Annotuted BibZiogrupby Marie H. Tuttle Vigyan Research Associates Hampton, Virginia Raymond E. Mineck and Karen L. Cole Langley Researcb Center Hampton, Virginia National Aeronautics and Space Administration Scientific and Technical Information Branch 1986 CONTENTS INTRODUCTION ................................................................................................. 1 ORDERING INFORMATION ............................................................................. 2 BIBLIOGRAPHY .................................................................................................. 3 APPENDIX ............................................................................................................ 37 AUTHOR INDEX ................................................................................................. 43 SUBJECT INDEX ................................................................................................. 45 SOURCE INDEX .................................................................................................. 47 iii INTRODUCTION This bibliography lists 260 publications that may be of interest to persons involved in correcting aerodynamic data, from high lift or V/STOL (Vertical/Short Take-off and Landing) type configurations, for the interference arising from the wind tunnel test section walls. The term b‘walls’* is used for the wind tunnel test section boundaries which may be open or closed on one or more sides. For the purpose of this bibliography, the term “high lift” is used in connection with testing at high angles of attack or at lift coefficients higher than could be obtained from a single element airfoil. These high lift coefficients may be generated mechanically by devices such as flaps, or aerodynamically by interaction of the free stream with the flow from a propulsive device. Aerodynamically generated high lift coefficients are usually associated with V/STOL concepts. This bibliography attempts to provide references which may be useful in correcting high lift data from wind tunnel to free air conditions. High lift or V/STOL testing often involves the simulation of the effect of ground proximity. References have been included which deal with the simulation of ground effect, since this could be viewed as having interference from three tunnel walls. It should be noted that the references could also prove useful in designing tests from the standpoint of model size and ground effect simulation, or to determine the available testing envelope with consideration of the problem of flow breakdown. This publication is one of a series of bibliographies dealing with wall interference. The reduction or elimination of wall interference through the use of adaptive walls is covered in NASA TM-87639 (August 1986). The general subject of wind tunnel wall interference is to be covered in a two part bibliography. The arrangement of the citations is chronological by date of publication in the case of reports or books, and by date of presentation in the case of papers. Included are some documents of historical interest in the development of high lift testing techniques and wall interference correction methods. Subject, corporate source, and author indices, by citation numbers, have been provided to assist the users. The subject index, especially, should be used only for quick reference since it is not intended to be complete. The appendix includes citations of some books and documents which may not deal directly with high lift or V/STOL wall interference, but include additional information which may be helpful. Documents cited in the appendix are identified by numbers having an “A” prefix, and are included in the indices. In most cases, abstracts used are from the NASA announcement bulletins “Scientific and Technical Aerospace Reports” (STAR) and “International Aerospace Abstracts” (IAA). In some cases, authors’ abstracts were used. License was taken to modify or shorten abstracts, using parts pertinent to the subject of the bibliography. If it is known that a paper has appeared in several forms, mention is made of this fact. Accession numbers, report numbers, and other identifying information is included in the citations in order to facilitate the filling of requests for specific items. When requesting material from your library or other source, it is advisable to include the complete citation; the abstract may be omitted. Ordering Information for the different types of materials is given below: Acquisition Number Type of Material Where Obtained AXX-XXXXX AIAA papers and published American Institute of Aeronautics literature available from and Astronautics Example: AIAA or in journals, Technical Information Serivce N75-25583 conferences, etc., as 555 West 57th Street, 12th Floor indicated New York, NY 10019 NXX-XXXXX Report literature having National Technical Information no distribution limitation Service (NTIS) Example: 5285 Port Royal Road N67-36604 Springfield, VA 22161 xxx-xxxxx Report literature having NASA Scientific and Technical distribution limitation Information Facility (STIF) Example: of some type P. 0. Box 8757 X72-76040 B.W.I. Airport, MD 21240 AD Numbers Report literature with or Defense Technical Information without distribution Center limitation Cameron Station Alexandria, VA 223 14 Order number Theses University Microfilms (when given) A Xerox Company 300 North Zeeb Road Ann Arbor, MI 48106 TL57O.P48 Books Libraries For any other type of material, contact your library or the NASA Scientific and Technical Information Facility (see address above), and include any identifying information give. A "#" after an acquisition number (AXX-XXXXX# or NXX-XXXXX#) indicates that the document is also available in microfiche form. ISSN - is an acronym for International Standard Serial Number, an internationally accepted code for the identification of serial publications; it is precise, concise, unique, and unambiguous. ISBM - is an acronym for International Standard Book Number, a number which is given to every book or edition of a book before publication to identify the publisher, the title, the edition, and volume number. BIBLIOGRAPHY 1 *Wood, R. McK.; and *Harris, R. G.: Some Notes on the Theory 4 *Mendelson, R. A.; and *Polhamus, J. F.: Effect of the Tunnel- of an Airscrew Working in a \Vind Channel. British, Advisory Committee Wall Bonndary Layer on Test Results of a Wing Protruding from a Tunnel for Aeronautics R&M No. 662 (Revised), Feb. 1920,14 pp. Wall. NACA TN-l244,M,8 pp. Langley Research Center library number 4101 No-dimensional span-loading tests were made of a two-foot-chord NACA 91 (rev.) 65,-012 airfoil model in the 2.5-foot by 6-foot test section of the Langley stability tunnel to determine tunnel- wall boundary-layer effects. The tests The momentum theory of R. E. Froude leads to equations which require indicated that a small loss (less than one percent of the load at the center) some modification when the airscrew is working in a tunnel of dimensions in average load may be expected. At the tunnel wall the load may be as comparable with the diameter of the screws. Some correction to the speed much as 10 percent lower than that at the center of the tunnel, and large of the air in a wind channel must be made to obtain the equivalent speed of changes in the tunnel-wall boundary-layer thickness produce small changes advance of the airscrew in free air. Formula for the thrust-momentum in load. At low angles of attack the tunnel-wall boundary layer had little relation, inflow-outflow ratio and contraction ratio of the slipstream are effect on the pitching moment. At high angles of attack, the average deduced. A method of correcting the speed of advance for the effect of pitching moment for the wing may differ from the pitching moment at the channel constraint of flow is obtained based upon the momentum theory, center of the tunnel because of nonuniform stall. which may probably be relied upon so long as the correction required is reasonably small. *NACA, Langley Aeronautical Laboratory, Langley Field, Virginia, U.S.A. *Royal Aircraft Establishment, Farnborough, Hampshire, U.K. 5 *Pankhurst, R. C.; and *Pearcey, H. H.: Camber Derivatives and Two-Dimensional Tunnel Interference at Maximum Lift. British ARC CP 2 *Glauert, H.: Wind Tunnel Interference on Wings, Bodies and 28,1950,s pp. Airscrews. British ARC R&M 1566,m,96pp., 45 refs. Langley Research Center library number N-4974 Langley Research Center library number 1105.5 89 This paper concerns the corrections due to lift effect in tunnel tests of an aerofoil in two-dimensional flow. The circulation around the aerofoil is Note: This report is a separate monograph and is not included in the usually represented by the bound vortex at the centre of pressure, the bound volumes of early British reports. influence of the boundaries of the working section being deduced from the induced field of the appropriate system of images. The chordwise variation A comprehensive survey of the subject of wind tunnel interference on of the upwash (Le., the transverse component of the induced velocity) gives wings, bodies and airscrews is given. The basis of the theoretical treatment rise to an effective curvature of flow, which produced an effective change of of the subject is examined
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