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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

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