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An aerofoil with control surface in incompressible viscous flow

Published online by Cambridge University Press:  04 July 2016

B. C. Basu
B. C. Basu*
Affiliation:
Formerly Queen Mary College, University of London, Now Indian Institute of Technology, Kharagpur
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Extract

The calculation of the pressure distribution, overall lift and moment coefficients on a two-dimensional aerofoil at low speeds, including boundary layer effects, is nowadays a fairly standard numerical technique. Experience has shown that as long as the flow remains attached, theory predicts experimental results extremely well for a ‘clean’ aerofoil. The purpose of this note is to point out that the application of the same theory to aerofoils with conventional trailing edge control surfaces leads to results which differ significantly from those measured in experiments.

Type
Technical note
Information
The Aeronautical Journal , Volume 81 , Issue 804 , December 1977 , pp. 554 - 555
Copyright
Copyright © Royal Aeronautical Society 1977 

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References

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