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On the viscous hypersonic blunt body problem

Published online by Cambridge University Press:  28 March 2006

William B. Bush
William B. Bush
Affiliation:
California Institute of Technology, Pasadena, California
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Abstract

The viscous hypersonic flow past an axisymmetric blunt body is analysed based upon the Navier-Stokes equations. It is assumed that the fluid is a perfect gas having constant specific heats, a constant Prandtl number, P, whose numerical value is of order one, and a viscosity coefficient varying as a power, ω, of the absolute temperature. Limiting forms of solutions are studied as the free-stream Mach number, M, and the free-stream Reynolds number based on the body nose radius, R, go to infinity, and ε = (γ − 1)/(γ + 1), where γ is the ratio of the specific heats, and δ = 1/(γ − 1) M2 go to zero.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 20 , Issue 3 , November 1964 , pp. 353 - 367
Copyright
© 1964 Cambridge University Press

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References

Bush, W. B. 1962 J. de Mécanique, 1, 321.
Bush, W. B. 1964 Doctoral Thesis, Calif. Inst. of Technology.
Cheng, H. K. 1961 Proc. 1961 Ht. Trans. and Fluid Mech. Institute. Stanford, California: Stanford University.
Cheng, H. K. 1963 Cornell Aero. Lab. Rep. no. AF-1285-A-10.
Chester, W. 1956 J. Fluid Mech. 1, 490.
Freeman, N. C. 1956 J. Fluid Mech. 1, 366.
Hayes, W. D. & Probstein, R. F. 1959 Hypersonic Flow Theory. New York: Academic Press.
Van Dyke, M. D. 1958 J. Aero. Sci. 25, 485.