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Note on the Wave Drags of Untapered Wings with Streamwise Tips at Zero Lift

Published online by Cambridge University Press:  07 June 2016

A. D. Young
A. D. Young*
Affiliation:
Queen Mary College
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Extract

Detailed calculations based on linearised supersonic flow theory have demonstrated in a number of cases the equivalence between the wave drags of yawed or swept wings of constant section and zero lift and the corresponding values in two-dimensional flow. These results and others are shown to follow readily from a general theorem for which a simple proof is given. Some interesting deductions are illustrated in Fig. 3.

Type
Research Article
Information
Aeronautical Quarterly , Volume 7 , Issue 3 , August 1956 , pp. 240 - 246
Copyright
Copyright © Royal Aeronautical Society. 1956

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References

1. Jones, R. T. Thin Oblique Airfoils at Supersonic Speed. N.A.C.A. T.N. 1107, 1946.Google Scholar
2. Nonweiler, T. Theoretical Supersonic Drag of Non-Lifting, Infinite Span Wings. R. & M. 2795.Google Scholar