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Lift augmentation on a moderately swept wing by spanwise blowing

Published online by Cambridge University Press:  04 July 2016

Kenneth P. Clarke
Kenneth P. Clarke*
Affiliation:
Cranfield Institute of Technology*
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Extract

At present it is still very difficult to predict for a given incidence, sweep-angle, leading-edge shape and Reynolds Number, whether the flow around a wing will remain attached or separate either from the upper surface as a bubble or from the leading edge as a vortex sheet which rolls up above the wing. Various attempts have been made to remove this uncertainty and it was suggested by Küchemann that it should be possible to design wings which combine coiled vortex sheets, originating from the inner part of the leading edge, with attached flow over the leading edge of the outer part of the wing. In this way some of the properties of slender wings could be combined with some properties of swept wings. His original model consisted of a swept-wing planform modified by inboard leading-edge wing strakes, the purpose of the latter being to provide the inboard vortex sheets. A similar idea has now been used in the wing design of the YF-16 lightweight fighter.

Type
Technical note
Information
The Aeronautical Journal , Volume 80 , Issue 790 , October 1976 , pp. 447 - 451
Copyright
Copyright © Royal Aeronautical Society 1976 

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Footnotes

*

Now at the Empire Test Pilots’ School, Aeroplane and Armament Experimental Establishment, Boscombe Down.

References

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2. Clarke, K. P. Lift augmentation on a moderately sweptwing by spanwise blowing. Cranfield Institute of Technology MSc thesis, September 1975.Google Scholar
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