Reynolds number effects on vortex breakdown of a blunt-edged delta

Journal of Aircraft

Volumn 33, Issue 4, 1996, Pages 835-837

  Traub, Lance W ^a,b,c   Galls, Samuel F ^a,b,c   Rediniotis, Othon K ^a,b,c  

^a TEXAS A AND M UNIVERSITY   (United States)

^b Mail Box 1513

^c AIAA ^*

Author keywords

[No Author keywords available]

Indexed keywords

AERODYNAMICS; CORRELATION METHODS; FUSELAGES; REYNOLDS NUMBER; TEST FACILITIES; VELOCITY; VORTEX FLOW; WINGS;

BLUNT LEADING EDGE; CROSSFLOW SEPARATION; VORTEX BREAKDOWN;

AEROSPACE ENGINEERING;

EID: 0030191078     PISSN: 00218669     EISSN: 15333868     Source Type: Journal    
DOI: 10.2514/3.47025     Document Type: Article

References (7)

1. Wentz, W. H., and Kohlman, D. L., "Vortex Breakdown on Slender Sharp-Edged Wings," Journal of Aircraft, Vol. 8, No. 3, 1971, pp. 156-161.
2. Straka, W. A., and Hemsch, M. J., "Leading-Edge Vortex Breakdown for Wing Planforms with the Same Slenderness Ratio," Journal of Aircraft, Vol. 31, No. 3, 1994, pp. 688-695.
3. 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 89-0086, Jan. 1989.
4. Straka, W. A., and Hemsch, M. J., "Effect of a Fuselage on Delta Wing Vortex Breakdown," Journal of Aircraft, Vol. 31, No. 4, 1994, pp. 1002-1005.
5. Ericcson, L. E., "Comment on Effect of a Fuselage on Delta Wing Vortex Breakdown," Journal of Aircraft, Vol. 31, No. 4, 1994, pp. 1006, 1007.
6. Rao, D. M., and Johnson, T. D., Jr., "Alleviation of the Subsonic Pitch-Up of Delta Wings," Journal of Aircraft, Vol. 20, No. 6, 1983, pp. 530-535.
7. Erickson, G. E., "Flow Studies of Slender Wing Vortices," AIAA Paper 80-1423, July 1980.