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A uniformly valid solution for the hypersonic flow past blunted bodies

Published online by Cambridge University Press:  28 March 2006

W. Schneider
W. Schneider
Affiliation:
Deutsche Versuchsanstalt für Luft- und Raumfahrt, Institut für Theoretische Gasdynamik, Aachen, Germany
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Abstract

The plane and axisymmetric hypersonic flow past blunted bodies is investigated as an inverse problem (shock shape given). The fluid may behave as a real gas in local thermodynamic equilibrium. Viscosity and heat conduction are neglected. An analytical solution uniformly valid in the whole flow field (from the stagnation region up to large distances from the body nose) is given. The solution is based on two main assumptions: (i) the density ratio ε across the shock is very small, (ii) the pressure at a point P of the disturbed flow field is not very small compared with the pressure immediately behind the shock in the intersection point of the shock surface with its normal through P. Terms O(ε) are neglected in comparison with 1, but it is not necessary for the shock layer to be thin. The change of velocity along streamlines is taken into account. In order to calculate the flow quantities one has to evaluate only two integrals (equations (49) and (53) together with the boundary values (5) and (10)). The application of the solution is illustrated and the accuracy is tested in some examples.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 31 , Issue 2 , 29 January 1968 , pp. 397 - 415
Copyright
© 1968 Cambridge University Press

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