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The boundary layer in a shock tube

Published online by Cambridge University Press:  29 March 2006

J. D. A. Walker And  and
S. C. R. Dennis
J. D. A. Walker And
Affiliation:
Department of Mathematics, University College London
S. C. R. Dennis
Affiliation:
Department of Applied Mathematics, University of Western Ontario
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Abstract

The boundary layer that forms on the walls of a shock tube, after the diaphragm which initially separates two gases at different pressures is burst, is investigated. Both the driver and driven gases are assumed to have the same thermal properties and the shock tube wall is maintained at constant temperature. Crocco variables are used and a method is presented for solving the compressible boundary-layer equations within the tube in similarity variables. Three cases, corresponding to different initial pressure ratios of the driver and driven gases, are calculated which are representative of weak and medium-strength shock and expansion waves.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 56 , Issue 1 , 14 November 1972 , pp. 19 - 47
Copyright
© 1972 Cambridge University Press

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