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Lift Produced by a Sonic Boom

Published online by Cambridge University Press:  04 July 2016

A. Sigalla
A. Sigalla*
Affiliation:
The Boeing Company, Airplane Division, Renton, Washington
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Extract

The Technical Note by C. H. E. Warren in the September Journal raises a question on the transfer of lift, of an aeroplane in supersonic flight, to the ground. This problem was considered in reference 2. It was shown that, as expected, the resultant of the pressure field produced by the aeroplane is equal to its lift. This apparent inconsistency with the N-wave pattern, predicted by Whitham stems from the fact that most applications of Whitham's theory are based on asymptotic forms for the velocity perturbations. Thus, the formula for the axial velocity perturbation is obtained by allowing (M2— l)l/2r/y to tend to infinity, where M is the flight Mach number, r the radial distance away from the aeroplane, y=x—(M2 — l)1/2, and x is the distance along the aeroplane flight direction. This approximation is valid in the vicinity of the shock waves emanating from the aeroplane.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 67 , Issue 636 , December 1963 , pp. 796
Copyright
Copyright © Royal Aeronautical Society 1963

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References

1.Warren, C. H. E.A Note on the Sonic Bang Waveform of an Aircraft With Lift. Journal of the Royal Aeronautical Society, Vol. 67, p. 595, September 1963.Google Scholar
2.Sigalla, A. Note on Some Theoretical Aspects of Lift Produced by Sonic Boom. Boeing Document D6-7996, 1961.Google Scholar
3.Whitham, G. B.The Flow Pattern of a Supersonic Projectile. Comm. on P. and A. Math., Vol. V, No. 3, pp. 301–348, August 1952.Google Scholar
4.Walkden, F.The Shock Pattern of a Wing-Body Combination Far from the Flight Path. Aeronautical Quarterly, Vol. IX, Pt. 2, pp. 164–194, May 1958.Google Scholar