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A Note on the Vorticity Distribution on the Surface of Slender Delta Wings with Leading Edge Separation

Published online by Cambridge University Press:  04 July 2016

B. J. Elle  and
J. P. Jones
B. J. Elle
Affiliation:
Saab Aircraft Company, Sweden
J. P. Jones
Affiliation:
Department of Aeronautics and Astronautics, University of Southampton
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Extract

A description is given of the distribution of vorticity in the surface of thin wings with large leading edge sweep. Although the delta wing is chosen as the basic plan form the deductions are general and applicable to other types of wing. The conclusions are illustrated with experimental evidence from a water tunnel.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 65 , Issue 603 , March 1961 , pp. 195 - 198
Copyright
Copyright © Royal Aeronautical Society 1961

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References

1.Maskell, E. C. (1955). Flow Separation in Three Dimensions. R.A.E. Report Aero 2565, November 1955.Google Scholar
2.Kuchemann, D. (1953). Types of Flow on Swept Wings with Special Reference to Free Boundaries and Vortex Sheets. Journal of the Royal Aeronautical Society, Vol. 57, No. 515, November 1953.CrossRefGoogle Scholar
3.Fink, P. T. and Taylor, J. (1955). Some Low Speed Experiments with 20° Delta Wings. A.R.C. 17854. September 1955.Google Scholar
4.Mangler, K. W. and Smith, J. H. B. (1957). Calculation of the Flow Past Slender Delta wings with Leading Edge Separation. R.A.E. Report Aero 2593. May 1957.Google Scholar
5.Ornberg, T. (1954). A Note on the Flow Around Delta Wings. K.T.H. Aero T.N. 38, 1954.Google Scholar
6.Elle, B. J. (1958). An Investigation at Low Speed of the Flow Near the Apex of Thin Delta Wings with Sharp Leading Edges. A.R..C. 19,780, January 1958.Google Scholar