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An Exact Theory of a Thin Aerofoil with Large Flap Deflection

Published online by Cambridge University Press:  28 July 2016

J. A. Hay  and
W. J. Eggington
J. A. Hay
Affiliation:
Aerodynamics Department, Vickers-Armstrongs (Aircraft) Ltd.
W. J. Eggington
Affiliation:
now with Saunders-Roe Ltd.
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Extract

The theory of thin aerofoils at small incidence and flap deflection is very well established. For certain purposes it is desirable to know how an aerofoil will behave in potential flow when the flap is deflected through large angles.

To this end, an attempt has been made to develop a theory of thin aerofoils in which the flap deflection angle may be large.

The results obtained are compared with those derived by an alternative method of direct conformal transformation by F. Keune.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 60 , Issue 551 , November 1956 , pp. 753 - 757
Copyright
Copyright © Royal Aeronautical Society 1956

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References

1. Keune, F. (1936). Auftrieb einer geknickten ebenen Platte. Luftfahrtforschung Vol. 13, 1936. (Translated in N.A.C.A. T.M. 1340).Google Scholar
2. Lighthill, M. J. (1945). A New Method of Two- Dimensional Aerodynamic Design. R. and M. No. 2112, (8597) A.R.C. Technical Report, 1945.Google Scholar