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An experimental study of the interaction of an unsteady shock with a turbulent boundary layer at Mach numbers of 1.3 and 1.5

Published online by Cambridge University Press:  04 July 2016

J. A. Edwards  and
L. C. Squire
J. A. Edwards
Affiliation:
Rolls-Royce Research Fellow, Wolfson College, Cambridge University
L. C. Squire
Affiliation:
Reader in Engineering, Cambridge University Engineering Department
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Abstract

In this paper the results are given of an experimental investigation into the flow development and the surface pressures in an unsteady shock boundary layer interaction at Mach numbers of 1.3 and 1.5. The experiment is one in which a naturally grown turbulent boundary layer on the tunnel walls is disturbed by a normal shock wave spanning the test section of the tunnel. The shock wave is oscillated by a periodic pressure disturbance in the tunnel diffuser far downstream of the interaction. Both instantaneous (spatially averaged) and time averaged results for the surface pressures are presented. These results are used to study the flow development and phase changes through the interaction over a frequency range from 34 to 167 Hz. This frequency range was chosen to cover the range of parameters likely to occur in conditions corresponding to stall flutter in the compressor fans of large bypass engines.

Type
Research Article
Information
The Aeronautical Journal , Volume 97 , Issue 970 , December 1993 , pp. 337 - 348
Copyright
Copyright © Royal Aeronautical Society 1993 

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Footnotes

†

Currently DRA W7 Division, Fort Halstead and visiting fellow, College of Aeronautics, Cranfield.

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