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Structure of a Plane Shock Layer

Liepmann, H. W. and Narashima, R. and Chahine, M. T. (1962) Structure of a Plane Shock Layer. Physics of Fluids, 5 (11). pp. 1313-1324. ISSN 1070-6631. doi:10.1063/1.1706527.

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The structure of a plane shock wave is discussed and the expected range of applicability of the Navier‐Stokes equations within the shock layer is outlined. The shock profiles are computed using the Bhatnagar‐Gross‐Krook model of the Boltzmann equation and a uniformly converging iteration scheme starting from the Navier‐Stokes solution. It is shown that the Navier‐Stokes solution remains a good approximation in the high‐pressure region of the shock layer up to approximately the point of maximum stress for all shock strengths. In the low‐pressure region, the correct profiles deviate with increasing shock strength from the Navier‐Stokes solution. The physical significance of the kinetic model used and the relation of the present study to previous theoretical and experimental work is discussed.

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Additional Information:© 1962 The American Institute of Physics. Received 12 July 1962. Helpful discussions with Dr. J. D. Cole during the early part of this work are gratefully acknowledged. The work is the combined result of efforts started from different angles by the authors and made possible by the support of the National Aeronautics and Space Administration (Contract No. NAS7-100, and Research Grant NsG-40-60) and the Office of Naval Research [Contract N-onr 220 (21)].
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Office of Naval ResearchNsG-40-60
Issue or Number:11
Record Number:CaltechAUTHORS:20120921-134953075
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Official Citation:Structure of a Plane Shock Layer H. W. Liepmann, R. Narasimha, and M. T. Chahine, Phys. Fluids 5, 1313 (1962), DOI:10.1063/1.1706527
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:34288
Deposited On:21 Sep 2012 22:57
Last Modified:09 Nov 2021 23:07

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