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The Forces on an Aerofoil at Very Low Speeds*

Published online by Cambridge University Press:  28 July 2016

A. Thom  and
P. Swart
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Summary

The forces on an aerofoil have been measured at various angles of incidence for 0.5 < R < 2,000.

Below R = 2 the lift is found to be given approximately by :—

L, = (3/2) µlV sin 2x

and the drag at all angles of incidence tends to:

D = µlV.

An approximate theoretical estimate is also given of the effect of spacing, on the drag of a series of flat plates at R → o.

Type
Research Article
Information
The Aeronautical Journal , Volume 44 , Issue 358 , October 1940 , pp. 761 - 770
Copyright
Copyright © Royal Aeronautical Society 1940

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Footnotes

*

Published by permission of the Aeronautical Research Committee (3045. F. & M. 327). Fluid Motion Panel. Aerodynamics Sub-Committee, “A” Report).

References

Notes

* Proc. Roy. Soc. A., Vol. 140, 1933, on Aerodynamics, Piercy.

** Proc. Roy. Soc. A., Vol. 100, 1922, p. 394.

† e.g., Stokes quoted by Lamb. Hydrodynamics, 5th Edition. §343.

‡ Thorn, R. & M. No. 1604.