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Maximum Lift on Slender Wings

Published online by Cambridge University Press:  04 July 2016

D. W. Bridson and
G. J. Hancock
D. W. Bridson
Affiliation:
Department of Aeronautical Engineering, Queen Mary College, University of London
G. J. Hancock
Affiliation:
Department of Aeronautical Engineering, Queen Mary College, University of London
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Extract

Many authors have established that a finite wing in inviscid flow has a theoretical maximum lift coefficient. One formula based on a theoretical model of a rolled-up vortex system aft of an elliptically loaded wing is

where AR is the aspect ratio. Ref. 6 criticises the validity of eqn. (1) but at least eqn. (1) gives the order of magnitude of an inviscid CLmax.

Information

Type
Technical Notes
Information
The Aeronautical Journal , Volume 74 , Issue 716 , August 1970, pp. 671 - 672
Copyright
Copyright © Royal Aeronautical Society 1970 

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References

1. Hembold, H. B. Limitations of Circulation Lift. J Aero Sciences, Vol 24, No 3, March 1957.Google Scholar
2. Ribner, H. S. On the Lift and Induced Drag Associated with Large Downwash Angles. UTIA Tech Note 19, 1958.Google Scholar
3. McCormick, B. W. Limiting Circulatory Lift of a Wing of Finite Aspect Ratio. J Aerospace Sciences, Vol 26, No 4, April 1959.Google Scholar
4. Hancock, G. J. Comments on the Limiting Circulatory Lift of a Wing of Finite Aspect Ratio. J Aerospace Sciences, Vol 27, No 1, January 1960.Google Scholar
5. Davenport, F. J. Limiting Circulatory Lift of a Finite Span Wing. J Aerospace Sciences, Vol 27, No 12, December 1960.Google Scholar
6. Hancock, G. J. On the Rolling op of Trailing Vortices. (To be published in The Aeronautical Journal.)Google Scholar
7. Bridson, D. W. Maximum Lift of Slender Wings. MSc Thesis, University of London 1965.Google Scholar