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Hypersonic Flow Over Conical Wing-Body Combinations

Published online by Cambridge University Press:  07 June 2016

R. Hillier
R. Hillier*
Affiliation:
(Department of Aeronautics, Imperial College, London)
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Summary

This paper shows how thin shock layer theory may be applied to wing-body combinations and also to yawed wings of caret and diamond section. The common feature of these cases is the interaction of the crossflow with the body slope discontinuity and the manner in which the resulting disturbances propagate through the shock layer. Practical computation of surface pressures is straightforward and comparison with experiment appears to be fairly good for the limited results available.

Type
Research Article
Information
Aeronautical Quarterly , Volume 29 , Issue 4 , November 1978 , pp. 285 - 304
Copyright
Copyright © Royal Aeronautical Society. 1978

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References

1 Hillier, R. PhD dissertation, University of Cambridge, 1970.Google Scholar
2 Harmer, C. DIC dissertation, University of London, 1975.Google Scholar
3 Messiter, A.F. Lift of slender delta wings according to Newtonian theory. AIAA Journal, Vol. 1, p.794, 1963.CrossRefGoogle Scholar
4 Hayes, W.D. and Probstein, R.F. Hypersonic Flow Theory, Academic Press, New York, 1966.Google Scholar
5 Hillier, R. and Woods, B.A. A note on the thin shock layer approximation. Aeronautical Quarterly, Vol. XXVIII, p.85, 1977.CrossRefGoogle Scholar
6 Roe, P.L. A simple treatment of the attached shock layer on a delta wing. RAE Tech. Report 70246, 1970.Google Scholar
7 Squire, L.C. Calculated pressure distributions and shock shapes on thick conical wings at high supersonic speeds. Aeronautical Quarterly, Vol. XIII, p.185, 1967.CrossRefGoogle Scholar
8 Hillier, R. The effects of yaw on conical wings at high supersonic speeds. Aeronautical Quarterly, Vol. XXI, p.199, 1970.CrossRefGoogle Scholar
9 Shanbhag, V.V. Numerical studies on hypersonic delta wings with detached shock waves. ARC CP No. 1277.Google Scholar
10 Woods, B.A. and McIntosh, C.B.G. Hypersonic flow with attached shock waves over plane delta wings. Journal of Fluid Mechanics, Vol. 79, Part 2, p.361, 1977.CrossRefGoogle Scholar
11 Woods, B.A. Hypersonic flow with attached shock waves over delta wings of convex section. Private communication.Google Scholar
12 Rogers, E.W.E., Attridge, J.L., Macdonald, A.G.J. and Callinan, J. Experiments at M˚ = 4.03 on two families of pressure-plotting wing-and-half-cone combinations. R&M No. 3473, 1967.Google Scholar
13 Squire, L.C. Some extensions of thin shock layer theory. Aeronautical Quarterly, Vol. XXV, p.1, 1974.CrossRefGoogle Scholar