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Lift-Curve Slope and Induced Drag Factors of Large Aspect Ratio Straight-Tapered Wings

Published online by Cambridge University Press:  04 July 2016

T. R. F. Nonweiler*
Affiliation:
Queen's University, Belfast

Extract

The difficulties of computing a solution to the Prandtl lifting line equation for large values of A/a0 are well-known, at least to any investigators who have tried. In attempting to deduce the loading over straight-tapered wings, like those used on sailplanes, the author has used an iterative method by which the nth. approximation to the downwash is obtained by a numerical integration based on the (n–l)th. approximation to the distribution of circulation. The main difficulty here is essentially one of making a good initial guess of circulation for the first approximation to the downwash.

Type
Technical Notes
Copyright
Copyright © Royal Aeronautical Society 1960

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