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A Numerical Method for Calculating the Trailing Vortex System behind a Swept Wing at Low Speed

Published online by Cambridge University Press:  04 July 2016

D. J. Butter  and
G. J. Hancock
D. J. Butter
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

A wing of finite span in flight generates trailing vorticity which “rolls up” into two “discrete” vortices. During the rolling up process the trailing vorticity is displaced vertically downward (assuming that the aircraft is in horizontal flight) under the influence of the wing circulation and the self-induced downwash velocities. In this note a method is presented for the prediction of the spatial distribution of the trailing vorticity during the rolling up process, thus giving the overall downwash field behind the wing.

Information

Type
Technical Notes
Information
The Aeronautical Journal , Volume 75 , Issue 728 , August 1971 , pp. 564 - 568
Copyright
Copyright © Royal Aeronautical Society 1971 

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Footnotes

*

Now at Hawker Siddeley Aviation, Woodford Division

References

1. Silverstein, , et. al. Design charts predicting downwash angles and wake characteristics behind plain and flapped wings. NACA Rept. 648, 1939.Google Scholar
2. Silverstein, , et al. Downwash and wake behind plain and flapped airfoils. NACA Rept. 651, 1939.Google Scholar
3. Kaden, H. Aufwicklung einer unstabilen Unsterigeits-flache. Ingenieur Archir. Bd. 2, 1931.Google Scholar
4. Cone, C. A theoretical investigation of vortex sheet deformation behind a highly loaded wing. NASA TN-D-657, 1960.Google Scholar
5. Rogers, A. W. Application of two dimensional vortex theory to the prediction of flow fields behind wings of wing body combinations at subsonic and supersonic speeds. NACA TN 3227, 1954.Google Scholar
6. Westwater, F. L. The rolling up of the surface of discontinuity behind an aerofoil of finite span. ARC R & M 1692, 1935.Google Scholar
7. Hancock, G. J. On the rolling up of a trailing vortex sheet. The Aeronautical Journal. Vol 74, No 717 pp. 749–752, September 1970.Google Scholar
8. Butter, D. J. The downwash field behind a swept wing at low speeds. MPhil Thesis University of London, 1968.Google Scholar