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The Effect of Sweep on Conditions at Separation in Turbulent Boundary-Layer/Shock-Wave Interaction

Published online by Cambridge University Press:  07 June 2016

D F Myring
D F Myring*
Affiliation:
University of Salford
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Summary

An approximate analysis of conditions at separation produced by turbulent boundary-layer/shock-wave interaction is presented for swept, cylindrically symmetric flows. An integral boundary-layer prediction method is used, incorporating Johnston crossflow profiles. The results indicate a marked reduction in pressure rise required to produce separation as sweep is increased. At low Reynolds numbers the skin friction at separation is inferred to be small, whereas at higher Reynolds numbers the presence of a vigorous streamwise flow may be detected. In the limiting case of zero sweep, or two-dimensional flow, predictions using the approximate analysis are shown to compare well with experimental results of pressure rise to separation.

Type
Research Article
Information
Aeronautical Quarterly , Volume 28 , Issue 2 , May 1977 , pp. 111 - 122
Copyright
Copyright © Royal Aeronautical Society. 1977

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References

1 Myring, D F Pressure rise to separation in cylindrically symmetric shock-wave/turbulent-boundary-layer interaction. AGARD Conference Proceedings 168, 1975.Google Scholar
2 Myring, D F An integral prediction method for three-dimensional turbulent boundary layers in incompressible flow. RAE TR 70147, 1970.Google Scholar
3 Myring, D F Boundary layers in supersonic flow and the effects of shock wave interaction. PhD thesis, University of London, 1967.Google Scholar
4 Green, J E The prediction of turbulent boundary-layer development in compressible flow. Journal of Fluid Mechanics, Vol 31, pp 753–778, 1968.Google Scholar
5 Johnston, J P Three-dimensional turbulent boundary layer. Massachusetts Institute of Technology, MIT Gas Turbine Laboratory Report 39, 1957.Google Scholar
6 Myring, D F The interaction of a turbulent boundary layer and a shock at hypersonic Mach numbers. AGARD Conference Proceedings 30, 1968.Google Scholar
7 McCabe, A The three-dimensional interaction of a shock wave with a turbulent boundary layer. Aeronautical Quarterly, Vol XVII, p 231, August 1966.Google Scholar
8 Stanbrook, A An experimental study of the glancing interaction between a shock wave and a turbulent boundary layer. ARC Current Paper 555, 1960.Google Scholar
9 Goldberg, T J Three-dimensional separation for interaction of shock waves with turbulent boundary layers. Technical Note, AIAA Journal, Vol 11, pp 1573–1575, 1973.Google Scholar
10 Korkegi, R H A simple correlation for incipient turbulent boundary-layer separation due to a skewed shock wave. Technical Note, AIAA Journal, Vol 11, pp 1578–1579, 1973.Google Scholar
11 Sterrett, J R Emery, J C Extension of boundary-layer separation criteria to a Mach number of 6.5 by utilising flat plates with forward-facing steps. NASA TN 618, 1960.Google Scholar
12 Bogdonoff, S M A study of shock-wave/boundary-layer interaction. Princeton University Aeronautical Engineering Department Report 222, 1953.Google Scholar
13 Seddon, J The flow produced by interaction of a turbulent boundary layer with a normal shock wave of strength sufficient to cause separation. R & M 3502, 1960.Google Scholar
14 Gadd, G E Holder, D W Regan, J D An experimental investigation of the interaction between shock waves and boundary layers. Proc Roy Soc, Series A, Vol 226, pp 227–253, 1954.Google Scholar
15 Chapman, D F Kuehn, D M Larson, H K Investigation of separated flows in supersonic and subsonic streams with emphasis on the effects of transition. NACA TN 3869, 1957.Google Scholar