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The High Subsonic Flow Around a Two-Dimensional Aerofoil with a Trailing Edge Control Surface

Published online by Cambridge University Press:  07 June 2016

D Nixon
D Nixon*
Affiliation:
Queen Mary College, University of London
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Summary

The effect of the operation of a 15 per cent trailing edge control surface on the flow around a two-dimensional aerofoil in a high subsonic shock-free condition is investigated using the integral equation method developed by Nixon and Hancock. The effect of retaining the non-linearities in the transonic potential equation is to increase considerably the magnitude of the pressures over the front part of the aerofoil in comparison with the pressure found using a modified linearised theory in which significant second-order terms in the boundary conditions are retained. The magnitude of the lift coefficient and the pitching moment coefficient are increased by 10-15 per cent over the values found using the modified linear theory, and by 20 per cent over the values found using standard linear theory. However, the magnitude of the hinge-moment coefficient is decreased by the order of 20 per cent compared with the modified linear values and by 30 per cent when compared to the standard linear values.

Type
Research Article
Information
Aeronautical Quarterly , Volume 24 , Issue 4 , November 1973 , pp. 273 - 283
Copyright
Copyright © Royal Aeronautical Society. 1973

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References

1 Weber, J The calculation of the pressure distribution over the surface of two-dimensional and swept wings with symmetrical aerofoil sections. ARC R&M 2918, 1953.Google Scholar
2 Weber, J The calculation of the pressure distribution on the surface of thick cambered wings and the design of wings with given pressure distributions. ARC R&M 3026, 1957.Google Scholar
3 Nixon, D Hancock, G J High subsonic flow past a steady two-dimensional aerofoil. Queen Mary College Report EP-1000, 1972.Google Scholar
4 Sells, C C L Plane subcritical flow past a lifting aerofoil. RAE Technical Report 67146, 1967.Google Scholar
5 Woods, L C The Theory of Subsonic Plane Flow. Chap 8. Cambridge University Press, 1961.Google Scholar