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Pressure Distribution Measurements at High Speed and Oblique Incidence of FlowThe present report contains the results of a series of observations obtained for a wing of symmetrical profile for different angles of yaw. The shock tunnel with 0.4m x 0.4m cross section, of the Institute for Gas Dynamics at L.F.A. - Braunchweig was available for this work. The profile used was a 9 percent, thick hyperbolic profile with maximum thickness 40 percent aft, which was calculated by the method of F. Ringleb (2). Since the conformal transformation of this profile is known, the theoretical pressure distribution could be determined exactly for the case of incompressible flow. Then by the use of the Prandtl rule one may extend the comparison of theory and experiment to the case of higher velocity of incident flow.
Document ID
20050010129
Acquisition Source
Langley Research Center
Document Type
Other - NACA Technical Memorandum
Authors
Lippisch, A. (Zentrale fuer Wissenschaftliches Berichtswesen Berlin, Germany)
Beuschausen, W. (Zentrale fuer Wissenschaftliches Berichtswesen Berlin, Germany)
Date Acquired
August 22, 2013
Publication Date
March 1, 1947
Publication Information
Publication: Messerschmitt A.G.
Issue: 1669
Subject Category
Aerodynamics
Report/Patent Number
NACA-TM-1115
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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