Surface flow patterns on an ogive-cylinder at incidence

1992 
dies for Two-Dimensional Wedges and Curved Surfaces at Mach Numbers of 4.8 to 6.2," NASA TN D-1014, Feb. 1962. Todisco, A., and Reeves, B. L., 'Turbulent Boundary-Layer Separation and Reattachment at Supersonic and Hypersonic Speeds," Proceedings of Viscous Interaction Phenomena in Supersonic and Hypersonic Flow, USAF Symposium, Aerospace Research Labs., Dayton, OH, May 1969, p. 139. Disimile, P. J., and Scaggs, N. E., "The Effect of Separation on Turbulent Boundary Layer Characteristics Over a Smooth Surface at Mach 6.0," AIAA Paper 90-3028, Portland, OR, Aug. 1990. Roshko, A., and Thomke, G. J., "Flare-Induced Interaction Lengths in Supersonic, Turbulent Boundary Layers," AIAA Journal, Vol. 14, No. 7, 1976, pp. 873-879. Disimile, P. J., and Scaggs, N. E., "High Reynolds Number Wedge-Induced Separation Lengths at Mach 6," AIAA Journal, Vol. 27, No. 12, 1989, pp. 1827-1828. Selig, M. S., Andreopoulos, J., Muck, K. C., Dussauge, J. P., and Smits, A. J., "Turbulence Structure in a Shock Wave/Turbulent Boundary-Layer Interaction," AIAA Journal, Vol. 27, No. 7, 1989, pp. 862-869.
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