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Thin aerofoils with high-incidence flaps or blunt trailing edges

Published online by Cambridge University Press:  04 July 2016

J. A. Moriarty and
E. O. Tuck
J. A. Moriarty
Affiliation:
Applied Mathematics Department, University of Adelaide, Australia
E. O. Tuck
Affiliation:
Applied Mathematics Department, University of Adelaide, Australia
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Summary

The method of matched asymptotic expansions is used to calculate the lift for a class of thin aerofoils with highincidence flaps or blunt trailing edges. The analysis is based on smallness of the ratio between the flap length (or trailingedge thickness) and the chord of the main foil. Results are compared with exact solutions for bent plates and for triangular and quadrilateral bodies. A procedure for extension to general trailing-edge configurations, including detached flaps, is outlined.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 93 , Issue 923 , March 1989, pp. 93 - 99
Copyright
Copyright © Royal Aeronautical Society 1989 

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Footnotes

p1

Present address: Department of Mechanical Engineering, University of Delaware, Newark, Delaware 19716, USA.

References

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3. Moriarty, J. A. A non-linear theory for thin aerofoils with nonthin trailing edges. MSc Thesis, University of Adelaide, 1988.Google Scholar
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5. Tuck, E. O. Thin airfoils with small trailing edge flaps at arbitrary angles. J Aust Math Soc, B (Appl Math), 1987, 29, (2), 144–158.Google Scholar