The Effect of a Normal Shock on the Aeroelastic Stability of a Panel

[+] Author and Article Information
M. H. Williams

School of Aeronautics and Astronautics, Purdue University, West Lafayette, Ind. 47907

J. Appl. Mech 50(2), 275-282 (Jun 01, 1983) (8 pages) doi:10.1115/1.3167032 History: Received September 01, 1980; Revised March 01, 1982; Online July 21, 2009


The effect of a standing shock wave on the static and dynamic aeroelastic stability of a flexible panel is investigated using a linear structural and aerodynamic theoretical model. It is found that the shock is generally stabilizing. The lowest critical dynamic pressures are associated with shock positions downstream from the panel, where the panel is uninfluenced by the shock.

Copyright © 1983 by ASME
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