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Base pressure in laminar supersonic flow

Published online by Cambridge University Press:  29 March 2006

A. F. Messiter ,
G. R. Hough  and
A. Feo
A. F. Messiter
Affiliation:
Department of Aerospace Engineering, University of Michigan, Ann Arbor
G. R. Hough
Affiliation:
N.A.S.A. Ames Research Center, Moffett Field, California
A. Feo
Affiliation:
Instituto Nacional de Tecnica Aeroespacial, Esteban Terradas, Madrid
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Abstract

An asymptotic description is proposed for supersonic laminar flow over a wedge or a backward-facing step, for large Reynolds number and for a base or step height which is small compared with the boundary-layer length. The analysis is carried out for adiabatic wall conditions and a viscosity coefficient proportional to temperature. In a particular limit corresponding to a very thick boundary layer, a similarity law is obtained for the base pressure $\overline{p}_b$. For a thinner boundary layer an asymptotic form for $\overline{p}_b$ is obtained which shows the dependence on the parameters explicitly and which permits good agreement with experiment. This latter result is based on an inviscid-flow approximation for the corner expansion and for reattachment, with viscous forces important primarily in a thin sublayer about the dividing streamline. A prediction of the pressure distribution at reattachment is given and the result is compared with experimental pressure distributions.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 60 , Issue 3 , 18 September 1973 , pp. 605 - 624
Copyright
© 1973 Cambridge University Press

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