The Effect of Vortex Generators on Shock-Induced Boundary Layer Separation in a Transonic Convex-Corner Flow

Deflected control surfaces can be used as variable camber in different flight conditions, and a convex corner resembles simplified configuration for the upper surface. This experimental study determines presence of passive vortex generators, VGs (counter-rotating vane type), on shock-induced boundary layer separation transonic convex-corner flow. The mean surface pressure distributions h/? = 0.2 0.5 are similar to those no flow control. If 1.0 1.5, there is an increase amplitude upstream corner’s apex, which corresponds greater device drag less downstream expansion. There decrease peak fluctuations value increases, because length frequency shock oscillation. effectiveness also depends freestream Mach number. For M 0.89, extension low-pressure region corner, convection induced streamwise vorticity. with ? preferred if deflected produce lift.