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Experiments on the hypersonic turbulent shock-wave/boundary-layer interaction and the effects of surface roughness

Published online by Cambridge University Press:  03 February 2016

S. A. Prince ,
M. Vannahme  and
J. L. Stollery
S. A. Prince
Affiliation:
Centre for Aeronautics, City University, London
M. Vannahme
Affiliation:
College of Aeronautics, Cranfield University, Cranfield, UK
J. L. Stollery
Affiliation:
College of Aeronautics, Cranfield University, Cranfield, UK
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Abstract

An experimental investigation was performed to study the effects of surface roughness on the Mach 8·2 hypersonic turbulent shockwave–boundary-layer interaction characteristics of a deflected control flap configuration. In particular, the surface pressure and heat transfer distribution along a quasi-2D ramp compression corner model was measured for flap angles between 0° and 38°, along with a Schlieren flow visualisation study. It was found that surface roughness, of scale 10% of the hinge-line boundary layer thickness, significantly increased the extent of the interaction, while increasing the magnitude of the peak pressure and heat flux just aft of reattachment. The incipient separation angle for a fully turbulent, Mach 8·2 boundary layer with a hinge line Reynolds number of 1·44 × 106, was estimated at 28-29°, reducing to between 19-22° with the introduction of laminar sub-layer scale surface roughness.

Type
Research Article
Information
The Aeronautical Journal , Volume 109 , Issue 1094 , April 2005 , pp. 177 - 184
Copyright
Copyright © Royal Aeronautical Society 2005 

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