Vortex breakdown location over 65° delta wings empiricism and experiment

Aeronautical Journal

Volumn 108, Issue 1087, 2004, Pages 475-482

  Jobe, C E ^a  

^a AIR FORCE RESEARCH LABORATORY   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

AERODYNAMICS; COMPUTATIONAL METHODS; FIGHTER AIRCRAFT; FLOW CONTROL; LAMINAR FLOW; NAVIER STOKES EQUATIONS; REYNOLDS NUMBER; TURBULENT FLOW; VORTEX FLOW; VORTEX SHEDDING;

DELTA WINGS; VISUAL DATA; VORTEX BREAKDOWN; VORTEX CORE;

DELTA WING AIRCRAFT;

EID: 7544237302     PISSN: 00019240     EISSN: None     Source Type: Journal    
DOI: 10.1017/S0001924000000294     Document Type: Article

References (33)

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.
2. CIPOLLA, K.M. Structure of the Flow Past a Delta Wing with Variations in Roll Angle, May 1996, PhD dissertation, Lehigh University.
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.
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.
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.
6. 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.
7. 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.
8. 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. 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.
9. 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. 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.
10. 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. 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.
11. 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. 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.
12. 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.
13. 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.
14. SKOW, A.M. and ERICKSON, G.E. Modern fighter aircraft design for high-angle-of-attack maneuvering, AGARD-LS-121, High Angie-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.
15. SKOW, A.M. and ERICKSON, G.E. Modern fighter aircraft design for high-angle-of-attack maneuvering, AGARD-LS-121, High Angie-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.
16. 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.
17. TRALB, L.W. Simple prediction method for location of vortex breakdown on delta wings, J Aircr, 1996, 33, (2), pp 452-454.
18. 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.
19. 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.
20. 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.
21. 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.
22. 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.
23. TRAUB, L.W. Prediction of vortex breakdown and longitudinal characteristics of swept slender planforms, J Aircr, May-June 1997, 34, (3), pp 353-359.
24. VERHAAGEN, N.G. Effect of sideslip on the flow over a 65-deg delta wing; preliminary report, December 1997, Deift University of Technology, The Netherlands.
25. 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.
26. CHADERJIAN, N. and SCHIFF, L. Navier-Stokes prediction of a delta wing in roll with vortex breakdown, August 1993, AIAA Paper 93-3495.
27. 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.
28. 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.
29. GURSUL, I. Unsteady flow phenomena over delta wings at high angle-of-attack, 1994, AIAA J, 32, (2), pp 225-231.
30. 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.
31. VISSER, K.D. and NELSON, R.C. Measurements of circulation and voracity in the leading-edge vortex of a delta wing, AIAA J, 1993, 31, (1), pp 104-111.
32. JUMPER, E.J., NELSON, R.C. and CHEUNG, K. A simple criterion for vortex breakdown, January 1993, AIAA-93- 0866.
33. VISSER, K.D. and WASHBURN, A.E. Transition behavior on flat plate delta wings, June 1994, AIAA-94-1850- CP.