Abstract
A low-speed wind-tunnel investigation was undertaken to evaluate the ability of a small leading-edge flap attached to the pressure surface of a Clark Y airfoil to improve low-Reynolds-number performance. Different flap geometries and designs were evaluated. Testing encompassed the measurement of lift and drag, surface pressures, and surface-flow topology rendered using titanium dioxide. Tests were undertaken at Reynolds numbers of 75,000 and 150,000. The results show that the flaps shift the zero-lift angle of attack in the positive direction, with the lift decrement stemming from reduced lower-surface pressure. The flaps proved to be beneficial only at high angles of attack, where they cause a sustained lift plateau and eliminate hysteresis.
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