1、NASA Technical Memorandum 406 1 Wind Tunnel Wall Interference (January 1980-May 1988) A Selected, Annotated Bibliogrupby TNCE EFER FOR R ,Or *a I-BoaT- Marie H. Tuttle and Karen I,. Cole AUGUST 1988 LIBRARY COPY. UNGLEY RESEARCH CENTER LISRARY, NASA IAMTO!, Vl!?!%!A NASA Provided by IHSNot for Resal
2、eNo reproduction or networking permitted without license from IHS-,-,-NASA Technical Memorandum 4061 Wind Tunnel Wall Interference (January 1980-May 1988) A Selected, Annotated Bibliography Marie H. Tuttle Vigyan Research Associates, Inc. Hampton, Virginia Karen L. Cole Langley Research Center Hampt
3、on, Virginia National Aeronautics and Space Administration Scientific and Technical Information Division Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CONTENTS INTRODUCTION v ORDERING INFORMATION . vii BIBLIOGRAPHY 1 ADDENDUM 63 APPENDIX . 69 AUTHO
4、R INDEX 74 SUBJECT INDEX . 78 SOURCE INDEX . . 8 1 Sincere thanks go to Dr. Perry A. Newman, of the NASA Langley Theoretical Aerodynamics .Branch, for helpful suggestions during the selection of articles to be included in this bibliography. Provided by IHSNot for ResaleNo reproduction or networking
5、permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-INTRODUCTION This selected bibliography lists 423 entries on the subject of wall interference during testing in wind tunnels. It is the third in a series of biblio
6、graphies on this subject. The first, NASA TM-87639, August 1986, is concerned with the reduction of wall interference by the use of adaptive walls. The second, NASA TM-89066, December 1986, is on wall interference in V/STOL and high lift testing. This, the third in the series, covers the wall interf
7、erence literature published during the period January 1980 - May 1988, generally excluding those topics covered in the first two parts. A small number of relevant documents have been announced since the first two parts of this series were published; citations for some of these documents are included
8、 in the present compilation. As in the earlier bibliographies, the abstracts used are from the NASA announcement publications, “Scientific and Technical Aerospace Reports,“ (STAR), and “International Aerospace Abstracts,“ (IAA). In other cases, abstracts written by the authors are used. License was
9、taken to modify or shorten abstracts, using parts pertinent to the subject of the bibliography. Generally the citations are arranged by dates of publication. However, papers presented at conferences and meetings are arranged by dates of presentation. This arrangement makes a “history“ out of the com
10、pilation, and is often helpful in locating specific documents. Indexes for author, subject, and corporate source, by citation number, are included for the convenience of the user. The information included about the authors is that existing when the papers were written and may not have remained the s
11、ame. If it is known that a paper has appeared in several forms, mention is made of this fact. An Addendum at the end of the citations lists items not received in time to be included in the proper order in the main bibliography. There is also an Appendix which consists of selected books, documents, a
12、nd conference proceedings which may not be directly or entirely on the subject of wall interference, but may provide helpful information. These citations are identified by the “A“ added to their citation numbers. Both the Addendum and the Appendix have been included in the indexes. Identifying infor
13、mation, including accession and report numbers when known, is included in the citations in order to facilitate filling requests for specific items. When requesting material from a library or other source, it is advisable to include the complete citation; the abstract may be omitted. Provided by IHSN
14、ot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ORDERING INFORMATION . The following table lists the various kinds of accession numbers used. It also lists the type of
15、material each indicates and the sources for each type. Accession Number Type of Material Source AXX-XXXXX AIAA papers and published American Institute of Aeronautics literature available from and Astronautics Example: AIAA or in journals, Technical Information Service A75-25583 conferences, etc., as
16、 555 West 57th Street, 12th Floor indicated New York, NY 100 19 NXX-XXXXX Report literature having National Technical Information no distribution limitation Service (NTIS) Example: 5285 Port Royal Road N67-37604 Springfield, VA 22 16 1 XXX-XXXXX Report literature having NASA Scientific and Technical
17、 some type of distribution Information Facility (STIF) Example: limitation P. 0. Box 8757 X72-76040 B.W.I. Airport, MD 21240 AD Numbers Report literature with or without Defense Technical Information distribution limitation Center Example: Cameron Station AD-A162351 Alexandria, VA 223 14 order numbe
18、r Theses (when given) Library of Congress Books, conference numbers proceedings, etc. University Microfilms A Xerox Company 300 North Zeeb Road Ann Arbor, MI 48106 Libraries Example: TL570.P48 For any other type of material, contact your library or the NASA Scientific and Technical Information Facil
19、ity (see address above), and include any information given. A “#“ after an acquisition number 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;
20、 it is precise, concise, unique, and unambiguous. ISBN 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. vii Provided by IHSNot for ResaleNo reprodu
21、ction or networking permitted without license from IHS-,-,-BIBLIOGRAPHY 1 *Hinson, B. L.; and *Burdges, K. P.: An Evaluation of Three-Dimensional Transonic Codes Using New Correlation -Tailored Test Data. Presented at the AIAA 18th Aerospace Sciences Meeting, Pasadena, Calif., Jan. 14-16. 1980, 13 p
22、p. Also, Journal of Aircraft, vol. 18, no. 10, Oct. 1981, pp. 855-861, 15 refs. AIAA Paper 80-0003 A80-22728# Note: For a later form of this paper see 72. A comprehensive research program was conducted for the specific purpose of acquiring test data which could serve as a standard for three-dimensio
23、nal transonic method evaluation. High-quality test data were obtained for three advanced technology wings by using a unique test apparatus and by devoting careful attention to details of the experiment. Semi-span wing models were tested alone and as wing-body configurations. The test apparatus inclu
24、ded provisions for removal of the wind tunnel boundary layer to ensure good semi-span reflection-plane characteristics. Extensive far-field pressure measurements were used to assess and correct for transonic wind tunnel wall interference. The test data were then used in preliminary evaluations of th
25、ree selected transonic computational methods. *Lockheed-Georgia Co., Marietta, GA 30060, USA 2 *Mugherty, N. S., Jr.; and *Fisher, D. F.: Boundary- Layer Transition on a 10-deg. Cone - Wind Tunnel Flight Correlation. Presented at the AIAA 18th Aerospace Sciences Meeting, Pasadena, Calif., Jan. 14-16
26、. 198Q, 17 pp. AIAA Paper 80-0154 A80-22737# Boundary-layer transition location measurements were made on a 10-degree sharp cone in 23 wind tunnels of the US and Europe and in flight. The data were acquired at subsonic, transonic, and supersonic Mach numbers over a range of unit Reynolds numbers to
27、obtain an improved understanding of wind tunnel flow quality influence. Cone surface microphone measurements showed Tollmien-Schlichting waves present. Transition location defined by pitot probe measurements showed transition Reynolds number to be correlatable to cone surface disturbance amplitude w
28、ithin + or - 20 percent for the majority of tunnel and flight data. ARO, Inc., Arnold Air Force Station, TN 37389. USA *NASA, Flight Research Center, Edwards, CA 93523, USA USAF-NASA supported research 3 *Karlsson, K. R.; and * *Geller, E. W.; *Johnson, M. L.; and *Jameson, A.: A Computer Code to Mo
29、del Swept Wings in an Adaptive Wall Transonic Wind Tunnel. Presented at the AIAA 18th Aerospace Sciences Meeting, Pasadena, Calif., Jan 14-16, m, 7 pp. Also, Journal of Aircraft, vol, 18, Sept. 1981, pp. 707- 711. AIAA Paper 80-0156 A80- 19287# A computer program has been developed to calculate invi
30、scid transonic flow over a swept wing in a wind tunnel with specified normal flow at the walls. An approximately orthogonal computational grid which conforms to the wing and the tunnel walls was developed for application of the Jameson-Caughey finite volume algorithm. The code solves the full potent
31、ial equations in fully conservative form using line relaxation. This program is to be used in place of the wind tunnel for preliminary studies of the adaptive wall concept for three dimensional configurations. It can also be used to assess the magnitude of wall interference in a conventional tunnel.
32、 *Flow Research Company, 21414 68th Ave. South, Kent, WA 9803 1, USA *New York Univ., New York, NY 10012, USA Contract F40600-79-C-001 5 *Mabey, D. G.: Resonance Frequencies of Ventilated Wind Tunnels. AIAA Journal, vol. 18, no. 1, Jan, I98Q, pp. 7-8. (Synoptic). Note: For backup document with the s
33、ame title see British ARC- RIM-3841, (N79-30245#), Apr. 1978. Experiments suggest that the theory widely used to predict the transverse resonance frequencies in slotted tunnels is in error in the 0-0.5 Mach number range. One reason for the error is that the theory is based on an unrepresentative wal
34、l boundary condition. Moreover, the theory implies that the plenum chamber depth is generally less than twice the tunnel height. An improved theory is developed which shows that the resonance frequencies of ventilated tunnels are influenced by the depth of the plenum chamber for Mach numbers up to a
35、bout M=0.6. Although the theory is approximate, it agrees well with experiments for slotted and perforated walls (with both normal and 60 deg inclined holes) in a small pilot wind tunnei (100 x 100 mm). The earlier theory was only valid for slotted working sections. The results are consistent with o
36、ther experiments, which show that plenum chamber design can influence the flow unsteadiness within the working section of a ventilated tunnel. *Royal Aircraft Establishment, Bedford MK41 6AE, UK 6 *Stahara, S. S.; and *Spreiter, J. R.: A Transonic Wind Tunnel Interference Assessment: Axisymmetric Fl
37、ows. AIAA Journal, vol., 18, no. 1, pp. 63-71, hn. 1980. Note: This paper (AIAA Paper 79-0203) was presented at the AIAA 17th Aerospace Sciences Meeting in New Orleans, La Jan. 15-17. 1979. 9 pp. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-A wind
38、 tunnel interference assessment concept that presents a rational predictive means of wall interference analysis is evaluated. The procedure consists of employing as an outer boundary condition an experimentally measured pressure distribution along a convenient control surface located inward from the
39、 actual tunnel walls. Attention has been focused on axisymmetric flows in the transonic regime, where tunnel interference is high and where the experimentally measured conditions on the control surface are of mixed subsonic/supersonic type. Based on the transonic small- disturbance equation, results
40、 for surface and near-flow field pressure distributions are presented for a variety of different slender-body shapes. These calculations indicate both the accuracy of the procedure as well as its ease of implementation. The procedure relates directly to the correctable-interference wind- tunnel conc
41、ept recently suggested. *Nielsen Engineering and Research, Inc., Mountain View, CA 94042, USA *Stanford University, Pa10 Alto, CA 94305-2186, USA Contracts F44620-75-C-0047 and DAAG 29-77-C-0038 7 *Rodriguez, 0.; and Gryson, P.: Experimental Study of Sonic Flow Around a Profile in the Presence of Pe
42、rmeable Walls. (Etude Experimentale DEcoulement Sonique Autour dun Profil en Presence de Parois Permeables.) Rept. no. IMFL-80-06; IMFL- 8121-8231, Feb. 5. 198Q, 59 pp., in French. The flow at free stream Mach I around an airfoil profile in the presence of suction through upper and lower porous wall
43、s was studied in a rectangular wind tunnel. Results were used to validate calculations relative to the simulation of flow in an infinite atmosphere. Results show good agreement between experiment and calculation; this confirms the interest of parietal suction in wind tunnel tests as the boundary lay
44、er is very important to adapted experimental magnitudes. *Institut de Mecanique des Fluides de Lille, France Contracts DRET-78-34.217.00.480.75.01, and DRET-79- 34.301.00.470.75.01 8 *Chan, Y. Y.: Boundary Layer Development on Perforated Walls in Transonic Wind Tunnels. National Research Council of
45、Canada Rept. no. DCAF F002839; LTR-HA-47, Feb. *Destuynder, R.; *Kienappel. K.; and *Roes, R.: Comparative Measurements in Four European Wind Tunnels of the Unsteady Pressures on an Oscillating Model (The NORA Experiments). AGARD Rept. No. 673, Feb. 1988. 48 pp. 49th Structures and Materials Panel M
46、eeting, Porz-Wahn. West Germany. Oct. 1979. Note: See no. 36 for the NORA Experiment in German. The European GARTEUR organization initiated, a few years ago, a cooperative program on the effects of the walls of a wind tunnel on the behavior of dynamic models used for flutter certification of aircraf
47、t. Tests have been completed by the same team. on the same model, in four European wind tunnels and the results, collected in the same form, have been thoroughly analyzed. The report describes the experiments and presents the most important results and practical conclusions. *Royal Aircraft Establis
48、hment, Bedford MK41 6AE. UK *ONERA, 29 ave de la Division Leclerc, 92320, Chatillon, France *DFVLR - Institut fur Aeroelastik, Bunsenstrasse 10, 3400 Goettingen, West Germany *National Aerospace Laboratory-NLR. Anthony Fokkerweg 2. 1059 CM Amsterdam, The Netherlands 10 *Sawada, H.: An Experiment of
49、Lift Interference on 2- Dimensional Wings in a Wind Tunnel With Perforated Walls. In: Japan Society for Aeronautical and Space Sciences. Transactions, vol. 22, Feb. 1980, pp. 191-202, in English. This is a translation of NAL-TR-563, Mar. 1979. An experiment on wall interference due to lift with two- dimensional wings was carried out in th
