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Lower Bounds for Sonic Bangs in the Far Field

Published online by Cambridge University Press:  07 June 2016

L. B. Jones
L. B. Jones*
Affiliation:
University of Bradford
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Summary

In this paper lower bounds are obtained for the intensity of the sonic bang resulting from a slender aircraft flying straight and level at supersonic speeds. The lower bounds are obtained for an aircraft subject to various constraints on its total lift, volume, area distribution and centre-of-pressure position. The work described proves the results quoted in an earlier paper, corrects the results given in that paper for the general configuration, and extends the results to cover more constraints, mainly the centre-of-pressure position.

Information

Type
Research Article
Information
Aeronautical Quarterly , Volume 18 , Issue 1 , February 1967 , pp. 1 - 21
Copyright
Copyright © Royal Aeronautical Society. 1967

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References

1. Jones, L. B. Lower bounds for sonic bangs. Journal of the Royal Aeronautical Society, Vol. 65, p. 433, June 1961.Google Scholar
2. Whitham, G. B. The flow pattern of a supersonic projectile. Communications on Pure and Applied Mathematics, Vol. 5, p. 301, 1952.CrossRefGoogle Scholar
3. Walkden, F. The shock pattern of a wing-body combination far from the flight path. Aeronautical Quarterly, Vol. IX, p. 164, May 1958.Google Scholar
4. Randall, D. G. Methods for estimating distributions and intensities of sonic bangs. ARC R & M 3113, August 1957.Google Scholar