AN EXPERIMENTAL INVESTIGATION OF THE NACA 631-012 AIRFOIL SECTION WITH LEADING-EDGE AND MIDCHORD SUCTION SLOTS

摘要

A previous investigation of boundary-layer control employing a two- dimensional model of the NACA 631-0I2 airfoil section demonstrated the ability of a single suction slot near the leading edge to increase maximum lift. It was believed possible, however that the complete stall may have resulted from leading-edge separation because of the inability of the nose suction to hold the flow on the surface. To investigate the effectiveness" of the nose slot at higher values of lift, a second suction slot was added near the midchord station of the model. This report is concerned with the results obtained with the two slots operating simultaneously.