This paper describes an experimental investigation into the use of trailing-edge-mounted plasma actuators for lift enhancement at low Reynolds numbers. The measurements were performed using a 0.2 m chord NACA 0009 airfoil with a plasma actuator mounted at x / c = 0.75 , and over the Reynolds-number range R e 70 , 000 400 , 000 . Force-balance data are presented that show that the effect of the actuator varies significantly with wind speed and angle of attack, and that, at some test conditions, the actuator produces a reduction in the airfoil lift. Detailed surface-pressure and Laser-Doppler-Velocimetry measurements show that the precise actuator effect depends upon how the actuator flowfield interacts with the trailing-edge boundary layer at the particular conditions of the test, and that the observed variation in actuator effect is a consequence of the different trailing-edge boundary-layer flows that can occur at low Reynolds numbers.


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    Titel :

    Lift Enhancement by Plasma Actuators at Low Reynolds Numbers


    Beteiligte:

    Erschienen in:

    Journal of Aircraft ; 50 , 1 ; 12-19


    Erscheinungsdatum :

    01.01.2013




    Medientyp :

    Aufsatz (Konferenz) , Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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