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Normal shock wave-turbulent boundary-layer interactions in the presence of streamwise slots and grooves

Published online by Cambridge University Press:  04 July 2016

A. N. Smith ,
H. Babinsky ,
J. L. Fulker  and
P. R. Ashill
A. N. Smith
Affiliation:
Engineering Department, University of Cambridge, UK
H. Babinsky
Affiliation:
Engineering Department, University of Cambridge, UK
J. L. Fulker
Affiliation:
Centre for Aerospace Technology, QinetiQ, Bedford, UK
P. R. Ashill
Affiliation:
Cranfield College of Aeronautics, Bedfordshire, UK
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Abstract

The effect of streamwise slots and grooves on a normal shock wave-turbulent boundary-layer interaction has been investigated experimentally at a Mach number of 1.3. The surface pressure distribution for the controlled interaction in the presence of slots featured a distinct plateau. This was due to a change in shock structure from a typical unseparated normal shock wave-boundary-layer interaction to a large bifurcated lambda type shock pattern. Velocity measurements downstream of the slots revealed a strong spanwise variation of boundary-layer properties, whereas the modified shock structure was found to be relatively two-dimensional. Cross flow measurements indicate that slots introduce streamwise vortices into the flow. When applied to an aerofoil, streamwise slots have the potential to reduce wave drag while incurring only small viscous penalties. In the presence of grooves the interaction was initially found to be significantly different. A bifurcated shock structure was observed but the trailing leg appeared stronger and featured a second lambda foot. Oil flow visualisation also revealed differences in the interactions, with the region of suction and blowing being limited to a smaller extent of the grooved control surface. The amount of crossflow present was reduced compared to the slotted control surface. By varying the internal geometry of the grooves it was found that the interaction could be modified to be similar to that in the presence of slots indicating that a more practical control device can be designed.

Type
Research Article
Information
The Aeronautical Journal , Volume 106 , Issue 1063 , September 2002 , pp. 493 - 500
Copyright
Copyright © Royal Aeronautical Society 2002 

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