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.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Lift Enhancement by Plasma Actuators at Low Reynolds Numbers


    Contributors:

    Published in:

    Journal of Aircraft ; 50 , 1 ; 12-19


    Publication date :

    2012-12-25


    Size :

    8 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    Lift Enhancement by Plasma Actuators at Low Reynolds Numbers

    Vorobiev, Alexander / Rennie, Mark / Jumper, Eric | AIAA | 2010


    Lift Enhancement at Low Reynolds Numbers Using Pop-Up Feathers

    Schluter, J. / American Institute of Aeronautics and Asronautics | British Library Conference Proceedings | 2009