抄録
Experiments were conducted to investigate effects of vortex generators on flow separation for a cranked-arrow wing at a low speed wind tunnel. A kind of delta-shaped vortex generator was applied to control the boundary layer separation flow near the hinge line of the deflected leading-edge flap. Effects on aerodynamic performance were estimated according to the force measurement data and flow patterns were observed by oilflow visualization technique. It was found that the drag coefficient was reduced and the lift-to-drag ratio was improved as the vortex generator was suitably equipped on the hinge line of the leading-edge flap. It was observed that swirling longitude vortices were generated from the leading-edge of the vortex generator, and thus suppressed the boundary layer flow separation.
