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RESEARCH PAPERS

On the Calculation of Unsteady Nonlinear Three-Dimensional Supersonic Flow Past Wings

[+] Author and Article Information
J. J. Kacprzynski, H. Ashley

Department of Aeronautics and Astronautics, Stanford University, Stanford, Calif.

R. Sankaranarayanan

Hindustan Aircraft Post, India

J. Basic Eng 90(4), 581-594 (Dec 01, 1968) (14 pages) doi:10.1115/1.3605199 History: Received February 08, 1968; Online November 03, 2011

Abstract

A comprehensive study is made of factors influencing the accuracy of predicted thickness effects on the flow due to oscillatory motion of a sweptback wing in supersonic flight. For a delta planform with its leading edge swept at or near the Mach angle, the streamlines and velocity pattern due to thickness are found to be highly three-dimensional. Based on this observation, improvements are suggested to previous approximate second-order theories for the unsteady loading. Numerical examples are presented for a 45 deg della which indicate a substantial difference between the linearized and nonlinear pressure distributions. Although a greater volume of computation is needed to guarantee adequate accuracy, practical means are described for the complete numerical solution of problems of this type.

Copyright © 1968 by ASME
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