Hostname: page-component-78c5997874-lj6df Total loading time: 0 Render date: 2024-11-05T07:21:33.813Z Has data issue: false hasContentIssue false

Inviscid Hypersonic Source Flow, over Slender Power-Law Bodies

Published online by Cambridge University Press:  07 June 2016

M Yasuhara
Affiliation:
Department of Aeronautical Engineering, Nagoya University
S Watanabe
Affiliation:
Department of Aeronautical Engineering, Nagoya University
Get access

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
Copyright
Copyright © Royal Aeronautical Society. 1975

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

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