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Effect of yaw on supersonic and hypersonic flow over delta wings

Published online by Cambridge University Press:  04 July 2016

W. H. Hui
W. H. Hui*
Affiliation:
Department of Aeronautics and Astronautics, University of Southampton
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Extract

The problem of a delta wing in a high speed stream has been approached using linearised potential flow theory for low supersonic Mach number, and using thin shock layer theory for hypersonic Mach number. Recently the author has given a new theory of supersonic and hypersonic flows with attached shock wave over the compression surface of an unyawed delta wing. It has the advantage of being unified for both supersonic and hypersonic flows, and it gives almost identical results compared with exact numerical solutions. The purpose of this note is to extend the theory of Ref. 4 to include the effects of yaw.

Information

Type
Technical notes
Information
The Aeronautical Journal , Volume 77 , Issue 750 , June 1973 , pp. 299 - 301
Copyright
Copyright © Royal Aeronautical Society 1977 

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References

1. Jones, R. T. and Cohen, D. High Speed Wing Theory, Princeton University Press, 155–156. 1960.Google Scholar
2. Messiter, A. F. Lift of slender delta wings according to Newtonian theory. AIAA Journal. I, 794–802. 1963.Google Scholar
3. Woods, B. A. Hypersonic flow with attached shock wave over delta wings. Aeronautical Quarterly, Vol 21, 379–399. 1970.Google Scholar
4. Hui, W. H. Supersonic and hypersonic flow with attached shock wave over delta wings. Proc. Royal Soc, London, A, Vol 325, 250–267, 1971.Google Scholar
5. Babaev, D. A. Numerical solution of the problem of supersonic flow past the lower surface of a delta wing. (Transl. from Russian). AIAA Journal, 1, 2224-31. 1963.Google Scholar
6. Lighthiix, M. J. A technique for rendering approximate solutions to physical problems uniformly valid. Philos. Mag, Vol 40, 1179–1201. 1949.Google Scholar
7. Van Dyke, M. D. Perturbation Methods in Fluid Mechanics, Academic Press, 99–100. 1964.Google Scholar