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

Author:

Cassel K. W.,Ruban A. I.,Walker J. D. A.

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.

Publisher

Cambridge University Press (CUP)

Subject

Mechanical Engineering,Mechanics of Materials,Condensed Matter Physics

Reference47 articles.

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4. Kerimbekov R. M. , Ruban A. I. & Walker J. D. A. 1994 Hypersonic boundary-layer separation on a cold wall.J. Fluid Mech. 274,163–195.

5. Smith F. T. 1988 A reversed-flow singularity in interacting boundary layers.Proc. R. SOC. Lond. A420,21–52.

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