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Shock detachment and drag in hypersonic flow over wedges and circular cylinders

Published online by Cambridge University Press:  25 March 2021

H.G. Hornung Open the ORCID record for H.G. Hornung [Opens in a new window]
H.G. Hornung*
Affiliation:
Graduate Aerospace Laboratories, California Institute of Technology, Pasadena, CA91125, USA
*
†Email address for correspondence: hans@caltech.edu
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Abstract

In a recent publication, Hornung et al. (J. Fluid Mech., vol. 871, 2019, pp. 1097–1116) showed that the shock wave stand-off distance and the drag coefficient of a cone in the inviscid hypersonic flow of a perfect gas can be expressed as the product of a function of the inverse normal-shock density ratio $\varepsilon$ and a function of the cone-angle parameter $\eta$, thus reducing the number of independent parameters from three (Mach number, specific heat ratio and angle) to two. Analytical forms of the functions were obtained by performing a large number of Euler computations. In this article, the same approach is applied to a symmetrical flow over a wedge. It is shown that the same simplification applies and corresponding analytical forms of the functions are obtained. The functions of $\varepsilon$ are compared with the newly determined corresponding functions for flow over a circular cylinder.

JFM classification

Compressible Flows: Hypersonic Flow Compressible Flows: Shock waves
Type
JFM Papers
Information
Journal of Fluid Mechanics , Volume 915 , 25 May 2021 , A100
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Copyright
© The Author(s), 2021. Published by Cambridge University Press

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References

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