Use of vortex generators to control internal supersonic flow separation

The capability of various boundary-layer manipulations to delay separation in a supersonic internal flow was investigated. An asymmetric two-dimensional convergent-divergent channel with a planar surface at one side and a bump having a cylindrical contour with a diameter of 500 mm was used. The experiments were conducted in the transonic wind tunnel discharging into a downstream container evacuated before the test. The normalized pressure distributions along the nozzle surface were shown for four settings of the adjusting valve of the tunnel.