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On the incipient separation of a turbulent hypersonic boundary layer

Published online by Cambridge University Press:  04 July 2016

H. Babinsky  and
J. A. Edwards
H. Babinsky
Affiliation:
College of AeronauticsCranfield UniversityCranfield, UK
J. A. Edwards
Affiliation:
W7 DivisionDRA Fort HalsteadSevenoaks, UK
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Abstract

Experiments are performed on the effects of a turbulent boundary layer on surface pressure and heat transfer, using a cylindrical model fitted with a variety of flares at Mach 5. The flow over compression corners of up to 20° (below the expected incipient separation value) is examined. Liquid crystal thermography indicates an unexpected peak in heat flux close to the corner. It is suggested that this is due to a small scale separation occurring earlier, i.e. at smaller corner angles, than previously observed. An estimate of the size of such a separation bubble is made and it is suggested that this is a predominantly laminar phenomenon.

Type
Research Article
Information
The Aeronautical Journal , Volume 100 , Issue 996 , July 1996 , pp. 209 - 214
Copyright
Copyright © Royal Aeronautical Society 1996 

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Footnotes

†

Currently at the Engineering Department, Cambridge University, UK.

References

1. Needham, D.A. and Stollery, J.L. Hypersonic studies of incipient separation and separated flows, ARC 27752, 1966.Google Scholar
2. Coleman, G.T. and Stollery, J.L. Incipient separation of axially symmetric hypersonic turbulent boundary layers, AIAA J, 1974, 12, (1), pp 119–120.Google Scholar
3. Hankey, W.L. and Holden, M.S. Two-dimensional shock wave boundary layer interactions in high speed flows, AGARDOgraph 203.Google Scholar
4. Babinsky, H. A Study of Roughness in Turbulent Hypersonic Boundary Layers, PhD Thesis, College of Aeronautics, Cranfield University, 1994.Google Scholar
5. Babinsky, H. and Edwards, J.A. The application and analysis of liquid crystal thermographs in short duration hypersonic flow, AIAA 93-0182, 1993.Google Scholar
6. Babinsky, H. and Edwards, J.A. Automatic liquid crystal thermog- raphy for transient heat transfer measurements in hypersonic flow, to appear in Exp in Fluids, 1996.Google Scholar
7. Quirk, J.J. An Adaptive Grid Algorithm for Computational Shock Hydrodynamics, RhD Thesis, College of Aeronautics, Cranfield University, 1991.Google Scholar
8. Mathews, D.C., Childs, M.E. and Paynter, G.C. Use of Coles’ universal wake function for compressible turbulent boundary layers, JAircr, 1970,7,(2).Google Scholar