Active control of fully-separated flow over symmetric sharp-edged wings at high angles of attack is investigated. Experiments were carried out in a low-speed, open circuit wind tunnel, as well as a Mach 0.2, 6'x6' wind tunnel. Angles of attack from 30 to 210 were tested. Low-power input, unsteady excitation was applied to the leading edge of the wings. The actuation was introduced by the periodic oscillation of a 4-percent-chord flap placed on the suction side of the airfoil and facing the sharp edge. We also carried out experiments with pulsing jets and larger models at Reynolds numbers the order of one million. Our results indicate that blowing practically at the leading edge of a sharp airfoil is as effective as oscillating mini-flaps. Pressure measurements over all models show that the control increases the normal force coefficient by up to 40% to 70%. The application of flow control on sharp-edged aircraft wings could lead to improved maneuverability, short take-off and landing, innovative flight controls and weight reduction.


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    Title :

    Flow Control Over Swept, Sharp-Edged Wings at Low and Moderate Angles of Attack


    Contributors:

    Publication date :

    2003


    Size :

    28 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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