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Criteria for location of vortex breakdown over delta wings

Published online by Cambridge University Press:  04 July 2016

I. Gursul
I. Gursul*
Affiliation:
Department of Mechanical, Industrial and Nuclear Engineering, University of Cincinnati, USA
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Extract

Vortex breakdown phenomenon remains a challenging aspect of the flow over delta wings at high angle of attack. The observations of vortex breakdown and related interpretations for vortex tube experiments and delta wings are summarised in several review articles. The theoretical models of the phenomena are described in detail in References 1, 2, 3 and 7. These theoretical models are not complete enough to predict breakdown location over delta wings. The purpose of this note is to review several existing criteria and correlations for vortex breakdown over delta wings using a large database. The earliest criteria for delta wings was suggested by Lambourne and Bryer.

Type
Technical Note
Information
The Aeronautical Journal , Volume 99 , Issue 985 , May 1995 , pp. 194 - 196
Copyright
Copyright © Royal Aeronautical Society 1995 

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References

1. Hall, M.G. Vortex breakdown, Annual Review of Fluid Mechanics, 1972, 4, pp 195–218.Google Scholar
2. Leibovich, S. Vortex stability and breakdown: survey and extension, AIAA J, 1984, 22, (9), pp 1192–1206.Google Scholar
3. Escudier, M. Vortex breakdown: observations and explanations, Progress in Aerospace Sciences, 1988, 25, pp 189–229.Google Scholar
4. Wedemeyer, E. Vortex breakdown, high angle-of-attack aerodynamics, AGARD No. 121, 1982.Google Scholar
5. Lee, M. and Ho, C.M. Lift force of delta wings, Applied Mechanics Reviews, 43, (9), September 1990, pp 209–221.Google Scholar
6. Rockwell, D. Three-dimensional flow structure on delta wings at high angle-of-attack: experimental concepts and issues, AIAA-93- 0550, 31st Aerospace Sciences Meeting and Exhibit, 11–14 January 1993, Reno, NV.Google Scholar
7. Brown, G.L. and Lopez, J.M. Axisymmetric vortex breakdown. Part 2. Physical mechanisms, J Fluid Mech, 221, 1990, pp 553–576.Google Scholar
8. Lambourne, N.C. and Bryer, D.W. The bursting of leading edge vortices — some observation and discussion of the phenomenon, Aeronautical Research Council, R & M 3282, 1962.Google Scholar
9. Jumper, E.J., Nelson, R.C. and Cheung, K. A simple criterion for vortex breakdown, AIAA-93-0866, 31st Aerospace Sciences Meeting and Exhibit, 11–14 January 1993, Reno, NV.Google Scholar
10. Wentz, W.H. and Kohlman, D.L. Vortex breakdown on slender sharp-edged wings, J Aircraft, March 1971, 8, (3), pp 156–161.Google Scholar
11. Thompson, D.H. A water tunnel study of vortex breakdown over wings with highly swept leading edges, Australian Research Laboratories, Note ARL/A 356, May 1975.Google Scholar
12. Erickson, G.E. Water-tunnel studies of leading-edge vortices, J Aircraft, 19, (6), June 1982, pp 442–448.Google Scholar
13. Panton, R.L. Effects of a Contoured Apex on Vortex Breakdown, J Aircraft, 27, (3), 1990, pp 285–288.Google Scholar
14. Earnshaw, P.B. Measurements of vortex breakdown position at low speed on a series of sharp edged symmetrical models, Royal Aircraft Establishment, RAE TR No. 64047, November 1964.Google Scholar
15. Thompson, S.A., Batill, S.M. and Nelson, R.C. Separated flowfield on a slender wing undergoing transient pitching motions, J Aircraft, 28, (8), August 1991, pp 489–495.Google Scholar
16. Kegelman, J.T. and Roos, F.W. Effects of leading edge shape and vortex burst on the flowfield of a 70-degree-sweep delta wing, AIAA Paper No. 89–0086, Reno, NV, January 1984.Google Scholar
17. Elle, B.J. An investigation at low speed of the flow near the apex of thin delta wings with sharp leading edges, Aeronautical Research Council, R&M No. 3282, April 1961.Google Scholar
18. Lawford, J.A. and Beauchamp, A.R. Low speed windtunnel measurements on a thin sharp edged delta wing with 70° leading edge sweep, with particular reference to the position of leading edge vortex breakdown, Aeronautical Research Council, R&M No. 3338, November 1961.Google Scholar
19. Payne, F.M., Ng, T.T., Nelson, R.C. and Schiff, L.B. Visualization and wake surveys of vortical flow over a delta wing, AIAA J, 26, (1), January 1988, pp 137–143.Google Scholar
20. Skow, A.M. and Titiriga, A. A survey of analytical and experimental techniques to predict aircraft dynamic characteristics at high angles of attack, AGARD-CP 235, (19), 1978.Google Scholar
21. Werle, H. Sur l'eclatement des tourbillons d'apex d'une aile delta aux fibles vitesses, La Recherche Aeronautique, (74), January-February 1960, pp 23–30.Google Scholar
22. Smith, J.H.B. Improved calculations of leading-edge separation from slender, thin, delta wings, Proc Royal Soc A, 306, 1968, pp 67–90.Google Scholar
23. Gursul, I. Unsteady flow phenomena over delta wings at high angle-of-attack, AIAA J, 32, (2), 1994, pp 225–231.Google Scholar