Investigations on a Supercritical Airfoil with Boundary Layer Suction Through a Perforated Strip in the Shock Region

摘要

The effect of local boundary layer suction through a perforated strip on the flow development and aerodynamic characteristics of a transonic airfoil was investigated in a 1m x 1m transonic wind tunnel. In comparison with reference measurements on the same model with a solid surface, the results show that, aside from the improvements due to suction, the flow development in the nonsuction case is most favorably affected by the arrangement of the perforation and cavity, caused by the strong adverse pressure gradients occurring at higher angles of attack; the shock location as well as the flow field downstream of the shock are affected. Thus, considerable gain in maximum lift and drag reductions can be achieved.