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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Post Stall Flow Control Over Swept Wings


    Contributors:
    D. Telionis (author)

    Publication date :

    2001


    Size :

    36 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    CONTROL OF DYNAMIC TIP STALL ON SWEPT WINGS

    Garmann, Daniel J. / Visbal, Miguel | TIBKAT | 2021


    Control of Dynamic Stall on Swept Finite Wings

    Garmann, Daniel J. / Visbal, Miguel R. | AIAA | 2022


    Control of Dynamic Tip Stall on Swept Wings

    Garmann, Daniel J. / Visbal, Miguel | AIAA | 2021


    Linear Modal Instabilities Around Post-Stall Swept and Tapered Wings

    Burtsev, Anton / Theofilis, Vassilis | British Library Conference Proceedings | 2022