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The initial roll-up of a thick, two-dimensional wake behind a wing of finite span

Published online by Cambridge University Press:  04 July 2016

H. Portnoy*
Affiliation:
Department of Aeronautical Engineering, Technion-lsrael Institute of Technology, Haifa

Extract

Many investigators have studied the rolling-up of the vortex wake behind a wing of finite span. The earliest step in this study was the work of Kaden who found an analytical solution for the rolling-up with time of a semi-infinite, straight, two-dimensional vortex sheet. This solution must represent the situation very close to the edges of a finite-span vortex sheet of zero thickness, in two or three dimensions, during the initial stage of the rolling-up process. An important result following from Kaden’s work is that, from the very onset of rolling-up, due to the infinite velocity at the sheet edge, a spiral of near-axi-symmetric form, with an infinite number of turns, is established at the edge. This is a consequence of the assumption of zero thickness for the sheet.

Type
Technical note
Copyright
Copyright © Royal Aeronautical Society 1976 

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References

1. Kaden, H. Aufwicklung eines unstabilen Unstetigkeitsfläche. Ing. Archiv., Vol 2, pp 140168, May 1931. (English translation RAE Library Translation No 403).Google Scholar
2. Westwater, F. L. The rolling up of the surface of discontinuity behind an aerofoil of finite span. British ARC R and M 1692, 1935.Google Scholar
3. Clements, R. R. and Mauix, D. J. The rolling-up of a trailing vortex sheet. The Aeronautical Journal, Vol 77, No 745, pp 4651, January 1973.Google Scholar
4. Moore, D. W. A numerical study of the roll-up of a finite vortex sheet. J. Fluid Mech., Vol 63, Part 2, pp 225235, 1974.Google Scholar
5. Hackett, J. F. and Evans, M. R. Vortex wakes behind high lift wings. Journal of Aircraft, Vol 8, No 5, pp 334340, 1971.Google Scholar
6. Hancock, G. J. and Butter, D. J. A numerical method for calculating the trailing vortex system behind a swept wing at low speed. The Aeronautical Journal, Vol 75, No 728, pp 564568, 1971.Google Scholar
7. Rom, J., Zorea, C. and Gordon, R. On the calculation of non-linear aerodynamic characteristics and the near vortex wake. The 9th Congress of the ICAS, Haifa, Israel. ICAS paper No 74-27, August 1974.Google Scholar
8. Labrujere, Th., E. A numerical method for the determination of the vortex sheet location behind a wing in incompressible flow. NLR TR 7209 lu, July 1972.Google Scholar
9. Maskew, B. The calculation of potential flow aerodynamics characteristics of combined lifting surfaces with relaxed wakes. Hawker Siddeley Aviation Ltd., (Brough), Aerodynamic Design Dept. Note YAD 3192, September 1973.Google Scholar
10. Betz, A. Verhalten von Wirbelsystemen, ZAMM, Vol 12, pp 164-174, June 1932. (Also NACA TM 713, June 1933).Google Scholar
11. Jordan, P. F. Structure of Betz vortex cores. Journal of Aircraft, Vol 10, pp 691693, November 1973.Google Scholar
12. Mason, W. H. and Marchman, J. F. III, Far-field structure of aircraft wake turbulence. Journal of Aircraft, Vol 10, pp 8692, February 1973.Google Scholar
13. Cliffone, D. L. and Orloff, K. L. Far-field wake-vortex characteristics of wings. Journal of Aircraft, Vol 12, pp 464470, May 1975.Google Scholar