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Inviscid Hypersonic Source Flow, over Slender Power-Law Bodies

Published online by Cambridge University Press:  07 June 2016

M Yasuhara  and
S Watanabe
M Yasuhara
Affiliation:
Department of Aeronautical Engineering, Nagoya University
S Watanabe
Affiliation:
Department of Aeronautical Engineering, Nagoya University
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Summary

Hypersonic small-disturbance theory is applied to the source flow over power-law slender bodies with conical or wedge type asymptote. The results for a point source flow with λ=2 over power-law cones of revolution show that the dominating equations in the first and second approximations are essentially the same as the ones for the parallel flow over power-law bodies of revolution. In the special case of a cone, results of a source flow and of a parallel flow are compared and it is shown that the surface pressure in a source flow at the nose is the same as the constant cone pressure in a parallel flow, but systematically decreases in the rear part. This is confirmed by comparison with a shock tunnel experiment.

Type
Research Article
Information
Aeronautical Quarterly , Volume 26 , Issue 3 , August 1975 , pp. 165 - 175
Copyright
Copyright © Royal Aeronautical Society. 1975

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References

1 Ashkenas, H Sherman, F S The structure and utilization of the supersonic free jets in low density wind tunnels. Rarefied Gas Dynamics, Vol 2, p 84, edited by Deleeuw, J H, Academic Press, 1965.Google Scholar
2 Baradell, D L Bertram, M H The blunt flat plate in hypersonic flow. NASA TND-408, 1960.Google Scholar
3 Hall, J G Effects of ambient nonuniformities in flow over hypersonic test bodies. Cornell Aeronautical Laboratory Report 128, 1963.Google Scholar
4 Gorgui, M A The hypersonic source flow past wedges and cones. Aeronautical Quarterly, Vol 22, p 327, November 1971.CrossRefGoogle Scholar
5 Van, M D Dyke A study of hypersonic small-disturbance theory. NACA Report 1194, 1954.Google Scholar
6 Lees, L Kubota, T Inviscid hypersonic flow over blunt-nosed slender bodies. Journal of the Aeronautical Sciences, Vol 24, p 195, 1957.CrossRefGoogle Scholar
7 Yasuhara, M et al Shock tunnel experiments on hypersonic source flow past slender bodies. Submitted to 10th International Shock Tube Symposium, Kyoto, Japan, 1975.Google Scholar
8 Uchida, S Kuwabara, K Furuhashi, K An investigation on the flow through a hypersonic nozzle in a shock-gun tunnel. Memoirs of the Faculty of Engineering, Nagoya University, Vol 22, p 276, 1970.Google Scholar