Hostname: page-component-89b8bd64d-sd5qd Total loading time: 0 Render date: 2026-05-09T14:18:09.128Z Has data issue: false hasContentIssue false
  • English
  • Français

Supersonic Bangs

Part I

Published online by Cambridge University Press:  07 June 2016

P. Sambasiva Rao
P. Sambasiva Rao*
Affiliation:
Department of Mathematics, The University, Manchester
Get access

Summary

In this paper a non-linear theory of the supersonic bangs from an accelerating body is worked out, using an extension of Whitham’s method. The strength of the bow shock is determined, and it is shown that the effect of acceleration on the pressure rise is appreciable at large distances from the nose for Mach numbers near unity. The results are compared with those of linear theory; the estimate for the pressure rise is found to be about a half of the linear value. The results also include an expression for the curvature of an attached shock at the nose, and a formula for the decay of a shock after it is detached from a decelerating body.

Information

Type
Research Article
Information
Aeronautical Quarterly , Volume 7 , Issue 1 , February 1956 , pp. 21 - 44
Copyright
Copyright © Royal Aeronautical Society. 1956

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Article purchase

Temporarily unavailable

References

1. Whitham, G. B. The Flow Pattern of a Supersonic Projectile. Communications on Pure and Applied Mathematics, Vol. 5, pp. 301-48. August 1952.CrossRefGoogle Scholar
2. Yates, A. H. Those Supersonic Bangs. Flight, 3rd October, 1952.Google Scholar
3. Warren, C. H. E. Sonic Bangs: A Qualitative Explanation. R.A.E. T.N. Aero. 2192, 1952.Google Scholar
4. Gold, T., The Double Bang of Supersonic Aircraft. Nature, 8th November, 1952.Google Scholar
5. Lilley, G. M., Westley, R., Yates, A. H. and Busing, J. R. Some Aspects of Noise from Supersonic Aircraft. Journal of the Royal Aeronautical Society, June 1953.Google Scholar
6. Whitham, G. B. The Behaviour of Supersonic Flow Past a Body of Revolution, Far from the Axis. Proc. Roy. Soc, A, Vol. 201, pp. 89–109, 1950.Google Scholar
7. Warren, C. H. E. An Addendum and Corrigenda to Technical Note Aero. 2192, R.A.E. Technical Note Aero. 2192a, 1952.Google Scholar
8. Cabannes, H. Influence des Accelerations sur la Courbure des Chocs. La Recherche Aeronautique, No. 39, pp. 3–13, May-June 1954.Google Scholar
9. Whitham, G. B. The Propagation of Spherical Blast. Proc. Roy. Soc, A, Vol. 203, pp. 571–581, 1950.Google Scholar