Lift characteristics of a supercritical airfoil with controlled separation in a subsonic flow

The results of experimental investigations into supercritical airfoil aerodynamics are presented. The airfoil has cross-sectional bulkheads of different heights fitted to the airfoil. The bulkheads were mounted for an active control of flow separation. The tests were carried out at the free-stream speed V[infinity] = 47 m/s within the range of angles of attack alpha= 0 ... 10 degrees. The pressure distribution around the airfoil and airfoil aerodynamic normal force, lift and drag coefficients were found. The bulkheads fitted in the airfoil leading edge neighbourhood have proved to be effective means allowing for the control of flow separation and lift of supercritical airfoils.