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The Drag Due to Lift of Plane Wings at Subsonic Speeds*

Published online by Cambridge University Press:  04 July 2016

D. Gardner  and
J. Weir
D. Gardner
Affiliation:
British Aircraft Corporation, Warton
J. Weir
Affiliation:
British Aircraft Corporation, Warton
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Summary

This note outlines a method for the prediction of drag due to lift of plane wings at Mach numbers below drag divergence and Reynolds numbers above 106. The method is based on the correlation of a number of wind tunnel measurements in terms of the effect of viscosity on lift curve slope. A comparison is made of the accuracy of estimating the induced drag factor, k, using this method, with the method of ret. 1, and it is shown that considerable improvement has been made, and that, in general, the predicted value of k is within 10% of experiment.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 70 , Issue 665 , May 1966 , pp. 595 - 599
Copyright
Copyright © Royal Aeronautical Society 1966

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Footnotes

*

This note is an abridged version of ref. 42 which was written in fulfilment of Ministry of Aviation Contrast No. KU/4/025/CB53a.

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