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Aerofoil nose shapes delaying leading-edge separation

Published online by Cambridge University Press:  04 July 2016

E. O. Tuck  and
A. Dostovalova
E. O. Tuck
Affiliation:
University of Adelaide, Australia
A. Dostovalova
Affiliation:
University of Adelaide, Australia
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Abstract

If an aerofoil of chord c has a parabolic nose with radius of curvature r, and is placed at angle-of-attack α to a stream, the laminar boundary layer on its upper surface remains unseparated for α<0.8l8. In the present paper we consider some smooth local modifications to the leading edge. Symmetric modifications of the nature of local sharpening of the nose can improve this result to at least α<0.897. Further improvements are possible for unsymmetrical (e.g. drooped) noses, and an example of a ‘drooped’ nose with α<0.912 is shown.

Type
Research Article
Information
The Aeronautical Journal , Volume 104 , Issue 1039 , September 2000 , pp. 433 - 437
Copyright
Copyright © Royal Aeronautical Society 1979 

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References

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