Leading edge transition on a 76 degree swept cylinder at Mach 1.6
暂无分享,去创建一个
Stephen W. D. Wolf | James A. Laub | D. I. A. Poll | Colin P. Coleman | Colin Coleman | D. Poll | S. Wolf | J. Laub
[1] D. Poll,et al. Boundary layer transition on the windward face of Space Shuttle during re-entry , 1985 .
[2] I. E. Beckwith,et al. Transition on swept leading edges at Mach 3.5 , 1987 .
[3] Stephen W. D. Wolf,et al. Flow characteristics of the NASA-Ames laminar supersonic wind tunnel for Mach 1.6 operation , 1994 .
[4] D. Poll,et al. The development of intermittent turbulence on a swept attachment line including the effects of compressibility , 1983 .
[5] D. Poll,et al. Transition in the Infinite Swept Attachment Line Boundary Layer , 1979 .
[6] Stephen W. D. Wolf,et al. Low-disturbance flow measurements in the NASA-Ames Laminar Flow Supersonic Wind Tunnel , 1996 .
[7] M. Holden,et al. Attachment line transition studies on swept cylindrical leading edges at Mach numbers from 10 to 12 , 1995 .
[8] Egon Stanewsky,et al. Boundary-layer transition on swept cylinders at hypersonic speeds , 1996 .
[9] I. E. Beckwith,et al. Effects of wind-tunnel noise on swept-cylinder transition at Mach 3.5 , 1986 .