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The Hypersonic Source Flow Past Wedges and Cones

Published online by Cambridge University Press:  07 June 2016

M. A. Gorgui
M. A. Gorgui*
Affiliation:
University of Manchester
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Summary

To study the effects of flow non-uniformities on the hypersonic flow past test bodies, perturbation analysis is applied to the hypersonic source flow past wedges and cones. In both cases it is shown that the effects of the source flow on the shock shape and velocity are small, while effects on the pressure and density are large. Curves are presented for various values of the Mach number from which these effects can be estimated.

Information

Type
Research Article
Information
Aeronautical Quarterly , Volume 22 , Issue 4 , November 1971, pp. 327 - 345
Copyright
Copyright © Royal Aeronautical Society. 1971

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References

1. Lighthill, M. J. The fundamental solution for steady three-dimensional disturbances to a two-dimensional parallel shear flow. Journal of Fluid Mechanics, Vol. 2, p. 113, 1957.CrossRefGoogle Scholar
2. Honda, M. Theory of a thin wing in a shear flow. Proceedings of the Royal Society, Vol. A254, p. 372, 1960.Google Scholar
3. George, A. R. Hypersonic flow over a wedge with upstream non-uniformities and variable wedge angle. Gas Dynamic Laboratory, Princeton University, Report 695, 1964.Google Scholar
4. Hall, J. G. Effects of ambient non-uniformities in flow over hypersonic test bodies. Cornell Aerodynamic Laboratory, Report 128, 1963.Google Scholar
5. Fink, M. R. Source flow effects on viscous and inviscid aerodynamic coefficients in hypervelocity nozzles. United Aircraft Corporation Research Laboratories, Report B1 10045-1, 1963.Google Scholar
6. Savage, S. B. Effects of a source-type hypersonic free stream on the flow field about an axisymmetric cone. Republic Aviation Corporation Report 2243, 1964.Google Scholar
7. Cole, J. D. Newtonian flow theory for slender bodies. Journal of the Aeronautical Sciences, Vol. 24, p. 448, 1957.CrossRefGoogle Scholar
8. Meyer, R. F. The flow about a particular class of plane and axisymmetric ogive in a hypersonic source flow. National Research Council of Canada Report LR-408, 1964.Google Scholar
9. van Dyke, M. D. A study of hypersonic small disturbance theory. NACA TN 3173, 1954.CrossRefGoogle Scholar