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An instability in supersonic boundary-layer flow over a compression ramp

Published online by Cambridge University Press:  26 April 2006

K. W. Cassel,
A. I. Ruban and
J. D. A. Walker
K. W. Cassel
Affiliation:
Department of Mechanical Engineering and Mechanics, Lehigh University, Bethlehem, PA 18015, USA
A. I. Ruban
Affiliation:
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky, Moscow Region, Russia
J. D. A. Walker
Affiliation:
Department of Mechanical Engineering and Mechanics, Lehigh University, Bethlehem, PA 18015, USA
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Abstract

Separation of a supersonic boundary layer (or equivalently a hypersonic boundary layer in a region of weak global interaction) near a compression ramp is considered for moderate wall temperatures. For small ramp angles, the flow in the vicinity of the ramp is described by the classical supersonic triple-deck structure governing a local viscous-inviscid interaction. The boundary layer is known to exhibit recirculating flow near the corner once the ramp angle exceeds a certain critical value. Here it is shown that above a second and larger critical ramp angle, the boundary-layer flow develops an instability. The instability appears to be associated with the occurrence of inflection points in the streamwise velocity profiles within the recirculation region and develops as a wave packet which remains stationary near the corner and grows in amplitude with time.

Information

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 300 , 10 October 1995, pp. 265 - 285
Copyright
© 1995 Cambridge University Press

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