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Aerodynamics for Engineers

Aerodynamics for Engineers 1 Theoretical consideration of aerofoils of limited span led, in Article III, to a need for some assumption as to liftgrading along the span, to give the spangrading of circulation. Fig. 1 shows at a the experimental distribution of lift along a rectangular aerofoil of 76 per cent camber and aspect ratio 6, at an angle of incidence of 6 deg. At b elliptic loading is shown, which, from several points of view, may be regarded as ideal for the same lift coefficient. Assumption of the latter form permits of greatly simplified treatment. Even compared with rectangular aerofoil distribution, the assumption gives differences of little importance in many practical calculations, while these are still less with aeroplane wings, owing to the washout usually introduced at their rounded wingtips. The following is, therefore, restricted to elliptic loading, but sufficient generality of presentation is preserved to allow, if desired, other forms to be substituted. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Aerodynamics for Engineers

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb029358
Publisher site
See Article on Publisher Site

Abstract

1 Theoretical consideration of aerofoils of limited span led, in Article III, to a need for some assumption as to liftgrading along the span, to give the spangrading of circulation. Fig. 1 shows at a the experimental distribution of lift along a rectangular aerofoil of 76 per cent camber and aspect ratio 6, at an angle of incidence of 6 deg. At b elliptic loading is shown, which, from several points of view, may be regarded as ideal for the same lift coefficient. Assumption of the latter form permits of greatly simplified treatment. Even compared with rectangular aerofoil distribution, the assumption gives differences of little importance in many practical calculations, while these are still less with aeroplane wings, owing to the washout usually introduced at their rounded wingtips. The following is, therefore, restricted to elliptic loading, but sufficient generality of presentation is preserved to allow, if desired, other forms to be substituted.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Jan 1, 1931

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