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A note on the application of the supersonic area rule to the determination of the wave drag of rectangular wings

Published online by Cambridge University Press:  28 March 2006

R. C. Lock
R. C. Lock
Affiliation:
Aerodynamics Division, National Physical Laboratory, Teddington
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Abstract

A proof is given that, in spite of certain singularities in the oblique area distributions, the supersonic area rule can be used to determine correctly the wave drag, according to linearized theory, of thin symmetrical rectangular wings at zero incidence. The proof could be extended to cover the case of swept wings with supersonic edges, for which similar singularities also exist.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 2 , Issue 6 , August 1957 , pp. 575 - 582
Copyright
© 1957 Cambridge University Press

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References

Harmon, S. M. 1947 Theoretical supersonic wave drag of untapered sweptback and rectangular wings at zero lift, Nat. Adv. Comm. Aero., Wash., Tech. Note no. 1449.Google Scholar
Heaslet, M. A., Lomax, H. & Spreiter, J. R. 1952 Linearised compressible flow theory for sonic flight speeds, Nat. Adv. Comm. Aero., Wash., Rep. no. 956.Google Scholar
Jones, R. T. 1953 Theory of wing-body drag at supersonic speeds, Nat. Adv. Comm. Aero., Wash., Res. Mem. no. A53H18a. (Also as Aero. Res. Counc., Lond., unpub. rep. no. 16603.)Google Scholar