An experimental study of active control of fully separated flow over a symmetrical circular-arc airfoil at high angles of attack was performed. The experiments were carried out in a low-speed, open-circuit wind tunnel with the airfoil at angles of attack from 10 to 40 deg. Low-power input, unsteady excitation was applied to the leading or trailing edge. The actuation was provided by the periodic oscillation of a 4% chord flap placed on the suction side of the airfoil and facing the sharp edge. Pressure measurements over the airfoil show that flow control increased the normal force coefficient by up to 70%. The application of flow control on sharp-edged aircraft wings could lead to improved maneuverability, innovative flight control, and weight reduction.


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    Title :

    Flow control of a sharp-edged airfoil


    Additional title:

    Beeinflussung der abgelösten Strömung um ein scharfkantiges Kreisbogenprofil


    Contributors:

    Published in:

    AIAA Journal ; 43 , 4 ; 716-726


    Publication date :

    2005


    Size :

    11 Seiten, 21 Bilder, 1 Tabelle, 16 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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    AIAA 2001-0119 Flow Control of a Sharp-Edged Airfoil

    Miranda, S. / Telionis, D. / Zeiger, M. et al. | British Library Conference Proceedings | 2001



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