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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.

Information

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

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