Control of turbulent boundary layer on a wing section by combined blowing/suction

详细

The possibility of exerting control over the turbulent boundary layer on NACA 0012 wing section with the aim of improving the wing aerodynamic characteristics in incompressible flow is experimentally examined. Control over the boundary layer was exercised in the range of the angles of attack from −12 to 12° by implementing combined steady-state blowing/suction of air through a finely perforated surface located, respectively, on the windward and leeward side of the wing and presenting part of streamlined surface.