A Numerical Study of Separating Supersonic Laminar Boundary Layers

[+] Author and Article Information
M. J. Werle

Department of Aerospace Engineering and Applied Mechanics, University of Cincinnati, Cincinnati, Ohio

G. D. Senechal

Department of Engineering Mechanics, Virginia Polytechnic Institute, Blacksburg, Va.

J. Appl. Mech 40(3), 679-684 (Sep 01, 1973) (6 pages) doi:10.1115/1.3423072 History: Received February 01, 1972; Online July 12, 2010


A numerical study has been made of the nature of the solution to the supersonic boundary-layer equations when the flow separates from the surface. To this end, implicit finite-difference solutions to the governing equations were obtained for linearly and quadratically retarded flows over flat plates for a Mach number range of 2–15. Both extremely hot and cold-wall conditions are considered. The resutls of this study give strong evidence that all noninteracting flows are singular at separation.

Copyright © 1973 by ASME
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