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Interaction of a Shock Wave with a Turbulent Boundary Layer Disturbed by Injection

Published online by Cambridge University Press:  07 June 2016

L.C. Squire  and
M.J. Smith
L.C. Squire
Affiliation:
Cambridge University Engineering Department
M.J. Smith
Affiliation:
Cambridge University Engineering Department
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Summary:

An experimental investigation has been made to study the interaction between an incident oblique shock wave and a turbulent boundary layer on a solid surface downstream of a porous surface with air injection through the porous surface. The results are clearly of direct interest to the design of cooled turbine blades. However, the boundary-layer profiles in the absence of the shock are similar to those in a boundary layer subjected to an adverse pressure gradient so that the results at the interaction also give some indication of the effects of an isentropic compression upstream of a shock/boundary-layer interaction. The experiments show the surprising result that the shock strength to produce incipient Separation is virtually independent of the shape of the boundary-layer profile upstream of the interaction, although the scale of the interaction increases with increase in the injection rate.

Type
Research Article
Information
Aeronautical Quarterly , Volume 31 , Issue 2 , May 1980 , pp. 85 - 112
Copyright
Copyright © Royal Aeronautical Society. 1980

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References

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