Experimental investigation of boundary layer separation control for wing using vortex generators

This paper investigates the effect of the chordwise position of microvortex generators and their installation angles on the boundary layer separation control for supercritical wing in the low speed wind tunnel.The results indicate that the principal effect of micro-trapezoid vortex generator is drag saving for boundary layer separation control of supercritical wing.The experimental results also show that the optimum chordwise position was found to be about 4 times micro-vortex generator's height upstream of baseline separation;The optimum installation angle was found to be 35°.