A flow control system and method especially well adapted for use on a Coanda surface (18). In one embodiment a plurality of plasma actuators (16a-16d) are disposed over a Coanda surface of a wing of an aircraft. The actuators are selectively energized to either delay the onset of boundary layer flow separation from the Coanda surface, or to promote flow separation. One embodiment discloses using dual mode plasma actuators on a Coanda surface. The system and method is applicable to a wide variety of aerodynamic surfaces where control over the separation of a boundary layer flow over a trailing edge surface is desired.


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    Title :

    Airfoil trailing edge plasma flow control apparatus and method


    Additional title:

    Vorrichtung und Verfahren zur Steuerung der Strömung mittels Plasma an der Hinterkante einer Tragfläche
    Appareil et procédé de contrôle de flux de bord de fuite de surface portante par l'effet d'un plasma


    Contributors:

    Publication date :

    2016-02-24


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



    Divergent-Trailing-Edge Airfoil Flow

    Thompson, B.E. | Online Contents | 1996


    Divergent-trailing-edge airfoil flow

    Thompson, Brian E. / Lotz, Robert D. | AIAA | 1996


    Airfoil trailing-edge flow measurements

    Brooks, T. F. / Marcolini, M. A. / Pope, D. S. | NTRS | 1986


    Airfoil trailing-edge flow measurements

    Brooks, T.F. / Marcolini, M.A. / Pope, D.S. | Tema Archive | 1986


    Airfoil trailing-edge flow measurements

    BROOKS, T. F. / MARCOLINI, M. A. / POPE, D. S. | AIAA | 1986