The paper discusses our current effort to develop methods for the correction of transonic wind tunnel boundary interference. A correction procedure is outlined on the basis of computational modeling of the wind tunnel flow field. In order to validate the correction method, four geometrically similar wind tunnel models, of different sizes, were tested in three separate transonic facilities. The results from two of these test are presented. It is also shown that higher order panel methods give useful corrections for subsonic Mach numbers.
Wind tunnel boundary interference prediction and correction
Voraussage und Korrektur der Grenzschichtinterferenz im Windtunnel
AIAA-Papers ; 1-12
1992
12 Seiten, 34 Bilder, 10 Quellen
Aufsatz (Konferenz)
Englisch
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