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Aerofoil Theory for Swallow Tail Wings of Small Aspect Ratio*

Published online by Cambridge University Press:  07 June 2016

A. Robinson
A. Robinson*
Affiliation:
University of Toronto
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Summary

A method is developed for the calculation of the aerodynamic forces acting on a “swallow tail” wing (Figs. l(a) and l(b)) of small aspect ratio. For a given incidence, lift and induced drag coefficient are, within the limits of the theory, proportional to aspect ratio and independent of Mach number. The exact solution is derived for the limiting case of small sweepback of the trailing edge. A numerical method is indicated for the more general case.

Type
Research Article
Information
Aeronautical Quarterly , Volume 4 , Issue 1 , February 1954 , pp. 69 - 82
Copyright
Copyright © Royal Aeronautical Society. 1954

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Footnotes

*

Modified version of College of Aeronautics Report No. 41, October 1950. Submitted for publication November 1950. The author is indebted to Mr. G. N. Ward and to members of the Royal Aircraft Establishment for critical comments.

References

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