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The Wave Formation and Sonic Boom due to a Delta Wing

Published online by Cambridge University Press:  07 June 2016

K Oswatitsch  and
Y C Sun
K Oswatitsch
Affiliation:
DFVLR-Institut für Theoretische Gasdynamik, Aachen
Y C Sun
Affiliation:
DFVLR-Institut für Theoretische Gasdynamik, Aachen
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Summary

By employment of the analytical method of characteristics and of a limiting procedure suitable for dealing with the trailing edge expansion, the influence of near-field flow on the far-field wave formation has been investigated for an incident flat delta wing with supersonic leading edges. Though confined in its scope to the front shock in the vertical plane of symmetry of the wing and to a homogeneous atmosphere without density and temperature gradients, the present analysis reveals features of flow which are interesting from the standpoint of the general theory of three-dimensional supersonic flow. It is found that the front shock due to a delta wing will as a rule be cancelled at a finite distance from the wing by the plane-wave expansion emanating from the trailing edge. The over-expansion must then give rise to a rear shock separate from the front one. Thus, at least in the plane of symmetry, a sharp-front wave signature can not, in general, be expected from the wing at a distance beyond the terminating point of the front shock. The boom signature then will be qualitatively different from that of a body of revolution. The general non-equivalence of a wing to a body of revolution in this respect should evoke some rethinking about sonic boom prediction and alleviation.

Type
Research Article
Information
Aeronautical Quarterly , Volume 23 , Issue 2 , May 1972 , pp. 87 - 108
Copyright
Copyright © Royal Aeronautical Society. 1972

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