An experimental study of active control of fully separated flow over a symmetrical circular-arc wing at high angles of attach was performed. The wing was swept at angles up to 45 degrees. The experiments were carried out in a low- speed, open-circuit wind tunnel. Angles of attack from 10 to 40 degrees were tested. The actuation was provided by the periodic oscillation of a 4-percent- chord flap placed on the suction side of the airfoil and facing the sharp edge. Pressure measurements over the wing show that the control increased the normal force coefficient by up to 50%. But the effectiveness of the method decreased with the angle of sweep. The application of flow control on sharp-edged aircraft wings could lead to improved maneuverability, innovative flight control and aircraft weight reduction.
Post Stall Flow Control Over Swept Wings
2001
36 pages
Report
No indication
English
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