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The perturbed region behind a diffracting shock wave

Published online by Cambridge University Press:  28 March 2006

B. W. Skews
B. W. Skews
Affiliation:
Department of Mechanical Engineering, University of the Witwatersrand
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Abstract

The results of an experimental study of the diffraction of shock waves on plane-walled convex corners are given for a Mach number range from 1·0 to 5·0. The behaviour of the disturbances produced in the region perturbed by the corner are discussed. It is shown that the position of the slipstream and tail of the Prandtl-Meyer fan, and the velocities of the contact surface and second shock become independent of corner angle for angles greater than 75°. Comparisons with theoretical predictions of Jones, Martin & Thornhill (1951) and Parks (1952) are included. In most cases fair agreement is obtained.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 29 , Issue 4 , 27 September 1967 , pp. 705 - 719
Copyright
© 1967 Cambridge University Press

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References

Fletcher, C. H., Weimer, D. K. & Bleakney, W. 1950 Phys. Rev. 78, 634.
Griffith, W. & Brickl, D. E. 1953 Phys. Rev. 89, 451.
Jones, D. M., Martin, P. M. E. & Thornhill, C. K. 1951 Proc. Roy. Soc. A, 209, 238.
Lighthill, M. J. 1949 Proc. Roy. Soc. A, 198, 454.
Parks, E. K. 1952 University of Toronto, Institute of Aerophysics, UTIA Rept. no. 18.
Skews, B. W. 1967 J. Fluid Mech. 29, 297.
Whitham, G. B. 1957 J. Fluid Mech. 2, 145.