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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

Ashkenas, H. & Sherman, F. S. 1966 Rarefied Gas Dynamics Suppl. 2 (3), 84.
Gorgui, M. A. 1971 Aero. Quart. 22, 327.
Hall, J. G. 1963 Cornell Aero. Lab. Rep. CAL 128.
Hayes, W. D. & Probstein, R. F. 1966 Hypersonic Flow Theory. Academic.
Kármán, T. Von & Moore, N. B. 1932 Trans. A.S.M.E. 54, 303.
Krasnov, N. F. 1970 Aerodynamics of Bodies of Revolution. American Elsevier.
Liepmann, H. W. & Roshko, A. 1957 Elements of Gasdynamics. Wiley.
Van Dyke, M. D. 1951 J. Aero. Sci. 18, 161.