Experimental investigation of subsonic turbulent separated boundary layers on an airfoil

Detailed measurements of fSowfields associated with Sow speed turbulent boundary layers have been made for the 17% thick GA(W)-1 airfoi! section at nominal angles of attack of 10, 14, and 18 deg; Reynolds number 2.2 x 10; and Mach number 0.13. The data include extensive pressure and velocity surveys of the preand postseparated regions on the airfoii and fhe associated wake. Integrated boundary-Saver characteristics including regions of separation on the airfoil are also presented. The results indicate steep gradients of displacement thickness, momentum thickness, shape factor, and the separation streamline from the point of separation to the trailing edge of the airfoil. The present tests reveal that the region of flow reversal terminates within a suprisingly short distance of less than 20% chord downstream from the trail ing edge for the test range of angle of attack.