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Comment on “Delta Wings of Shapes Amenable to Exact Shock-Wave Theory“

Published online by Cambridge University Press:  04 July 2016

A. C. Southgate  and
J. R. Pedersen
A. C. Southgate
Affiliation:
British Aircraft Corporation (Guided Weapons) Ltd.
J. R. Pedersen
Affiliation:
British Aircraft Corporation (Guided Weapons) Ltd.
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Extract

Finite bodies supporting two-dimensional under surface flows behind “contained” plane shock waves of the type discussed by Professor Nonweiler in a recent paper are currently receiving attention from both theoretical and experimental workers. The experimental work already undertaken by the RAE has given hopeful indications that such bodies, characterised by a re-entrant lower surface in cross section, compete closely with more familiar convex bodies in terms of lift/drag ratio, and furthermore preserve the two-dimensional character of the flow away from the design incidence.

The purpose of this note is to point out that:

(a) Delta wings with inverted V or W cross sections are geometrically simple examples of a more general family of possible shapes supporting two-dimensional flow behind a plane shock.

(b) The concept may be extended to bodies supporting two-dimensional flows with multiple shocks (leading to isentropic compression in the limit) or shock-expansion systems.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 67 , Issue 629 , May 1963 , pp. 301
Copyright
Copyright © Royal Aeronautical Society 1963

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References

1.Nonweiler, T.Delta Wings of Shapes Amenable to Exact Shock-Wave Theory. Journal of the Royal Aeronautical Society, Vol. 67, p. 39, January 1963.Google Scholar
2.Squire, L. C. Pressure Distributions and Flow Patterns at M=40 on Some Delta Wings of Inverted V Cross-Section. R.A.E. T.N. Aero. 2838, August 1962.Google Scholar