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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

1. Basu, B. C. A numerical solution for a steady two-dimensional aerofoil with control surface in incompressible flow. QMC EP-1017, June 1976.Google Scholar
2. Powell, B J. The calculation of the pressure distribution on a thick cambered aerofoil at subsonic speeds, including the effects of the boundary layer. ARC CP No 1005, June 1967.Google Scholar
3. Thwaites, B. Approximate calculations of the laminar boundary layer. Aeronautical Quarterly, Vol 1. p 245, 1949.Google Scholar
4. Horton, H. Entrainment in equilibrium and non-equilibrium turbulentboundarylayers.HSAHatfield/Research/1094, August 1969.Google Scholar
5. Brebner, G. G. and Bagley, J. A. Pressure and boundary layer measurements on a two-dimensional wing at low speed. ARC R&M 2886, 1952.Google Scholar
6. Wight, K. C. Measurements of two-dimensional derivatives on a wing-aileron-tab system with a 1541 section aerofoil. Part 1: Direct aileron derivatives. ARC R&M 2934, 1952.Google Scholar
7. Garner, H. C. Charts for low speed characteristics of two-dimensional trailing edge flaps. ARC R&M 3174, 1960.Google Scholar
8. Cook, T. A. The effect of ridge excrescence and trailing edge control gaps on two-dimensional aerofoil characteristics. ARC R&M 3698, 1972.Google Scholar