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An assessment of the 2D vortex method in aircraft wake simulation

Published online by Cambridge University Press:  04 July 2016

W. R. Graham
W. R. Graham*
Affiliation:
Department of Engineering, University of Cambridge, UK
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Abstract

Recent interest in aircraft vortex wakes has highlighted the need to identify appropriate algorithms for their simulation. The problem is not well-suited to grid-based techniques, due to the large domain and the need to avoid introducing artificial viscosity. A promising alternative is offered by Lagrangian formulations. This work aims to assess the usefulness of one such approach - the 2D vortex method -via comparison with experimental results. One in-house and two external (from DLR and ONERA) data sets are used. The results show generally good agreement in vortex locations and size, with the calculation performing best when initialised downstream of the strongly-three-dimensional trailing edge region. The neglect of viscosity can lead to some asymmetry in the vortex cores, but, even here, excellent agreement can be obtained when the field is integrated to give circulation (as a function of radius). The 2D vortex method is thus an accurate and efficient tool for wake vortex prediction.

Type
Research Article
Information
The Aeronautical Journal , Volume 105 , Issue 1054 , December 2001 , pp. 653 - 666
Copyright
Copyright © Royal Aeronautical Society 2001 

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References

1. Lanchester, F.W. Aerial Flight 1918, 1, Aerodynamics, 4th Edition, Constable, London, ch. 4.Google Scholar
2. Rossow, V.J. Lift-generated vortex wakes of subsonic transport aircraft. Prog Aero Sci, 1999, 35. pp 507–660.Google Scholar
3. Spalart, P.R. Airplane trailing vortices. Ann Rev Fluid Mech, 1998, 30, pp 107–138.Google Scholar
4. Stumpf, E., Rudnik, R. and Ronzheimer, A. Euler computation of the nearfield wake vortex of an aircraft in take-off configaration. Aerospace Science and Technology J. 2000, 4, pp 535–543.Google Scholar
5. Betz, A. Verhalten von Wirbelsystem. ZAMM, Bel.XII (3), 1932, pp 164–174.Google Scholar
6. Donaldson, C.DU P., Snedecker, R.S. and Sullivan, R.D. Calculation of aircraft wake velocity profiles and comparison with experimental measurements, J Aircraft. 11, (9), pp 547–555.Google Scholar
7. Krasny, R. Computation of vortex sheet roll-up in the Trefftz plane. J Fluid Mech, 184, pp 123–155.Google Scholar
8. Leonard, A. Vortex methods for flow simulation, J Comp Phys, 1980, 37, pp 289–335.Google Scholar
9. Glauert, H. The Elements of Aerofoil and Airscrew Theory, 2nd Edition, Cambridge University Press, 1947, ch. 10.Google Scholar
10. Batchelor, G.K. Axial flow in trailing line vortices, J Fluid Mech, 1964, 20, pp 645–658.Google Scholar
11. Batchelor, G.K. An Introduction to Fluid Dynamics, Cambridge University Press, 1967.Google Scholar
12. Spalart, P.R. Vortex methods for separated flows, NASA TM100068, 1988, ch 9.Google Scholar
13. Jacquin, L., Fabre, D., Geffroy, P. and Coustols, E. The properties of a transport aircraft wake in the extended near field - an experimental study, A1AA 2001-1038.Google Scholar
14. Stuff, R., Dieterle, L., Schneider, G.R., Dewhirst, T. and Vollmers, H. Experimental study of wake vortex formation behind a transport aircraft in landing configuration, 2D - PIV measurements at 3·3% and 47·2% of wing span behind the wing tip, DLR Göttingen Technical Note: Eurowake - TN, 1999.Google Scholar
15. Graham, W.R. Experimental assessment of the extended Betz method for wake vortex prediction, in the characterisation and modification of wakes from lifting vehicles in fluids, AGARD CP584, 1996, pp 9-1 to 9-12.Google Scholar
16. Chu, J.K., Rios-Chiquette, E., Sarokia, S. and Bernstein, L. The Chu-tube: a velocimeter for use in highly-sheared, three-dimensional, steady flows, Aeronaut J, March 1987, 91, (903), pp 142–149.Google Scholar
17. Melander, M.V., Zabusky, N.J. and McWilliams, J.C. Symmetric vortex merger in two dimensions: causes and conditions, J Fluid Mech, 1988, 195. pp 303–340.Google Scholar
18. Dritschel, D.G. A general theory for two-dimensional vortex interactions, J Fluid Mech, 1995, 293, pp 269–303.Google Scholar