Experimental oil-flow and tuft patterns and vapor-screen flow-visualization data were obtained on a cambered wing model at Mach = 1.62 for an angle-of attack range of 0-14 deg. These data were used as flow diagnostic tools along with surface-pressure and force data and full-potential theory calculations. A large separation bubble was found on the lower wing surface at low angle of attack. The high-angle-of-attack flowfield was characterized by a large attached-flow leading-edge expansion followed by a crossflow shock. At alpha = 14 deg the crossflow shock apparently induced discrete regions of streamwise separated flow, which were clearly indicated in the vapor-screen and oil-flow photographs.
Experimental flowfield visualization of a high alpha wing at Mach 1.62
Journal of Aircraft ; 24
1987-05-01
Miscellaneous
No indication
English
Turbulent-heat-transfer measurements at mach number of 1.62
Engineering Index Backfile | 1955
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