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Linearized theory of axisymmetric hypersonic source flow past bodies of revolution

Published online by Cambridge University Press:  29 March 2006

M. Yasuhara ,
H. Mitome  and
F. Nakao
M. Yasuhara
Affiliation:
Department of Aeronautical Engineering, Nagoya University, Nagoya, Japan
H. Mitome
Affiliation:
Department of Aeronautical Engineering, Nagoya University, Nagoya, Japan
F. Nakao
Affiliation:
Department of Aeronautical Engineering, Nagoya University, Nagoya, Japan
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Abstract

The linearized theory of axisymmetric hypersonic source flow past a slender pointed body is treated by using linearized potential theory, assuming that the hypersonic parameter is less than unity. The governing equation in the transformed co-ordinates with the ratio of specific heats γ = 1.5 shows a modified form relative to the equation for parallel flow, whereas that with γ = 2 shows essentially the same form. Some numerical calculations for a cone and a cone-cylinder are presented, and the surface pressure distributions obtained for both γ = 1.5 and 2 show that there is a considerable pressure-distribution difference between source flow and parallel flow. The pressure on a cone in hypersonic source flow approaches zero downstream, while, if the cone has a cylindrical afterbody, the pressure recovers to the free-stream value quickly. This suggests that the static pressure probe for supersonic parallel flow is useful also in source flow.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 73 , Issue 1 , 13 January 1976 , pp. 139 - 151
Copyright
© 1976 Cambridge University Press

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References

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