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Vortex breakdown location over 65° delta wings empiricism and experiment

Published online by Cambridge University Press:  03 February 2016

C. E. Jobe
C. E. Jobe*
Affiliation:
Air Force Research Laboratory, Wright-Patterson AFB, Ohio, USA
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Abstract

Thirty-eight data sets from static tests of various 65° delta wings in many water and wind tunnels are compared with four empirical vortex breakdown location prediction methods and the results of two Navier-Stokes computations to assess their range of validity in pitch. Vortex breakdown is the sudden expansion and subsequent chaotic evolution of the otherwise orderly, spiraling, leading-edge vortex flow over the upper surface. Large fluctuations occur in vortex breakdown location at static test conditions making accurate experimental determination difficult.

The prediction methods do not account for the seemingly minor geometric details that vary between the models such as thickness, leading-edge bevel angle and radius, trailing-edge bevel angle, sting mounting, instrument housings, etc. These geometric variations significantly affect the position of vortex breakdown and degrade the accuracy of the predictions. The large changes in the flow produced by small geometric changes indicate that an efficient flow control strategy may be possible. Many of the data sets are not corrected for tunnel wall effects, which may account for some of the differences. Data presented herein are as published by the original authors, without additional corrections.

Type
Research Article
Information
The Aeronautical Journal , Volume 108 , Issue 1087 , September 2004 , pp. 475 - 482
Copyright
Copyright © Royal Aeronautical Society 2004 

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References

1. Huang, X.Z. and Hanff, E.S. Unsteady behavior of spiral leading-edge vortex breakdown, July 1996, AIAA Paper 96-3408, also Prediction of normal force on a delta wing rolling at high incidence, Aug 1993, AIAA 93-3686.Google Scholar
2. Cipolla, K.M. Structure of the Flow Past a Delta Wing with Variations in Roll Angle, May 1996, PhD dissertation, Lehigh University.Google Scholar
3. Earnshaw, P.B. Measurements of vortex-breakdown position at low speed on a series of sharp-edged symmetrical models, November 1964, ARC CP No 828.Google Scholar
4. Earnshaw, P.B. and Lawford, J.A. Low-speed wind-tunnel experiments on a series of sharp-edged delta wings, March 1964, ARC R&M No 3424.Google Scholar
5. Guglieri, G. and Quagliotti, F.B. Experimental investigation of vortex dynamics on delta wings, June 1992, AIAA Paper 92-2731. Also see Guglieri, G., Onorato, M. and Quagliotti, F.B. Vortex breakdown study on a 65° delta wing tested in static and dynamic conditions, September 1992, ICAS 92-4.10.2, ICAS Proceedings, pp 2072–2081.Google Scholar
6. Lambourne, N.C. and Bryer, D.W. The bursting of leading-edge vortices — some observations and discussion of the phenomena, April 1961, ARC R&M No. 3282.Google Scholar
7. Lowson, M.V. and Riley, A.J. Vortex breakdown control by delta wing geometry, J Aircr, 1995, 32, (4), pp 832–838. Also see AIAA Paper 94-3487, August 1994.Google Scholar
8. Panton, R.L. Effects of a contoured apex on vortex breakdown, J Aircr, 1993, 27, (3), pp 285–288. Also see AIAA Paper 89-0193, January 1989.Google Scholar
9. Pelletier, A. An Experimental Investigation of Vortex Breakdown on Slender Delta-Wing Planforms, April 1994, MSc thesis, University of Notre Dame. Also see Pelletier, A. and Nelson, R.C. An experimental study of static and dynamic vortex breakdown on slender delta wing planforms, AIAA Paper 94-1879.Google Scholar
10. Skow, A.M. and Erickson, G.E. Modern fighter aircraft design for high-angle-of-attack maneuvering, AGARD-LS-121, High Angle-of-Attack Aerodynamics, December 1982, pp 4–1 to 4–59. Also see Erickson, G.E. Vortex flow correlation, January 1981, AFWAL-TR-80-3143.Google Scholar
11. Thompson, D.H. A water tunnel study of vortex breakdown over wings with highly swept leading edges, May 1975, Note ARL/A 356, Australian Defence Scientific Service.Google Scholar
12. Traub, L.W. Simple prediction method for location of vortex breakdown on delta wings, J Aircr, 1996, 33, (2), pp 452–454.Google Scholar
13. Wentz, W.H. and Kohlman, D.L. Vortex breakdown on slender sharp-edged wings, July 1969, AIAA Paper 69-778. Also see J Aircr, 1971, 8, (3), pp 156–161. See also Wind tunnel investigations of vortex breakdown on slender sharp-edged wings, November 1968, University of Kansas Report FRL 68-013, NASA CR 98737 also N69-14762.Google Scholar
14. Huang, X.Z., Sun, Y.Z. and Hanff, E.S. Further investigations of leading-edge vortex breakdown over delta wings, June 1997, AIAA Paper 97-2263.Google Scholar
15. Huang, X.Z., Sun, Y.Z. and Hanff, E.S. Circulation criterion to predict leading-edge vortex breakdown over delta wings, June 1997, AIAA Paper 97-2265.Google Scholar
16. Traub, L.W. Prediction of vortex breakdown and longitudinal characteristics of swept slender p1anforms, J Aircr, May-June 1997, 34, (3), pp 353–359.Google Scholar
17. Verhaagen, N.G. Effect of sideslip on the flow over a 65-deg delta wing; preliminary report, December 1997, Delft University of Technology, The Netherlands.Google Scholar
18. Addington, G.A. The Role of Flow Field Structure in Determining the Aerodynamic Response of a Delta Wing, April, 1998, PhD dissertation, University of Notre Dame, Notre Dame, Indiana.Google Scholar
19. Chaderjian, N. and Schiff, L. Navier-Stokes prediction of a delta wing in roll with vortex breakdown, August 1993, AIAA Paper 93-3495.Google Scholar
20. Gordnier, R.E. Numerical simulation of a 65 degree delta-wing flow-field, J Aircr, 1997, 34, (4), pp 492–499. Also see AIAA Paper 95-0082, January 1995.Google Scholar
21. Gursul, I. Unsteady flow phenomena over delta wings at high angle-of-attack, 1994, AlAA J, 32, (2), pp 225–231.Google Scholar
22. Hemsch, M.J., and Luckring, J.M. Connection between leading-edge sweep, vortex lift and vortex strength for delta wings, J Aircr, 27, (5), pp 473–475.Google Scholar
23. Visser, K.D. and Nelson, R.C. Measurements of circulation and vorticity in the leading-edge vortex of a delta wing, AIAA J, 1993, 31, (1), pp 104–111.Google Scholar
24. Jumper, E.J., Nelson, R.C. and Cheung, K. A simple criterion for vortex breakdown, January 1993, AIAA-93-0866.Google Scholar
25. Visser, K.D. and Washburn, A.E. Transition behavior on flat plate delta wings, June 1994, AIAA-94-1850-CP.Google Scholar