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On the incipient separation of a turbulent hypersonic boundary layer

  • H. Babinsky (a1) and J. A. Edwards (a2)

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.

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References

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1. Needham, D.A. and Stollery, J.L. Hypersonic studies of incipient separation and separated flows, ARC 27752, 1966.
2. Coleman, G.T. and Stollery, J.L. Incipient separation of axially symmetric hypersonic turbulent boundary layers, AIAA J, 1974, 12, (1), pp 119120.
3. Hankey, W.L. and Holden, M.S. Two-dimensional shock wave boundary layer interactions in high speed flows, AGARDOgraph 203.
4. Babinsky, H. A Study of Roughness in Turbulent Hypersonic Boundary Layers, PhD Thesis, College of Aeronautics, Cranfield University, 1994.
5. Babinsky, H. and Edwards, J.A. The application and analysis of liquid crystal thermographs in short duration hypersonic flow, AIAA 93-0182, 1993.
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.
7. Quirk, J.J. An Adaptive Grid Algorithm for Computational Shock Hydrodynamics, RhD Thesis, College of Aeronautics, Cranfield University, 1991.
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).

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On the incipient separation of a turbulent hypersonic boundary layer

  • H. Babinsky (a1) and J. A. Edwards (a2)

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