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An analysis of the lift on straight, yawed and swept-back wings

Published online by Cambridge University Press:  07 June 2016

J. Lockwood Taylor
J. Lockwood Taylor*
Affiliation:
The Technical University, Istanbul
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Summmary

As is well known, standard lifting-line theory cannot be applied to a wing with sweepback in order to determine the amount and distribution of the lift. Various methods, all fairly laborious, are available, and while they give results which agree fairly well with experiment, they do not show in detail the source of the various differences due to sweep. It is with the object of separating the several effects involved, which can be regarded as distinct for practical purposes, that the present method has been developed. Since one of the items, finite-chord loss, is shared with the straight wing, although not included in simple lifting-line theory, it is calculated first for the straight wing. The wing is represented by its median or camber surface and is assumed nearly flat.

Type
Research Article
Information
Aeronautical Quarterly , Volume 2 , Issue 4 , February 1951 , pp. 293 - 304
Copyright
Copyright © Royal Aeronautical Society. 1951

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References

1. Falkner, V. M. (1943). Aerodynamic Loading on Surfaces of Any Shape. R. & M. 1910, August 1943.Google Scholar
2. Cohen, D. (1945). The Twist of a Surface for a Given Lift. N.A.C.A. Report 826, 1945.Google Scholar
3. Campbell, J. P. (1948). Factors Affecting Lateral Stability. N.A.C.A. University Conference on Aerodynamics, June 1948.Google Scholar
4. Richards, E. J. (1947). Practical Design Problems Arising from Sweepback. Aeronautical Conference London, 1947. Royal Aeronautical Society, 1948.Google Scholar