A low-speed wind tunnel study of active flow control for improving aerodynamic performance of delta wings at high angles of attack is presented. A dielectric barrier discharge actuator driven by pulsed nanosecond voltage is used to create periodic perturbations along the leading edge of delta wing. Four wings with sweep back angles of Λ = 30°, 47°, and 60° are tested. Data obtained by means of force measurements show that the effectiveness of the actuation strongly depends on the wing’s sweep angles and the actuation frequency. For Λ = 30°, 47° delta wings, the pulsed actuation could increase the lift at post stall regions. For Λ = 60° delta wing, the pulsed actuation at the leading edge almost has no effect on its aerodynamic performance. At last, the control mechanism is discussed.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Experimental study of flow control on delta wings with different sweep angles using pulsed nanosecond DBD plasma actuators


    Contributors:


    Publication date :

    2015-09-01


    Size :

    9 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English






    2010-4837 Vortical Flow Control over Delta Wings with Different Sweep Back Angles Using DBD Plasma Actuator

    Kwak, D. / Nelson, R. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2010


    Numerical simulation to static ground effect of delta wings with different sweep angles

    Qin, Yunpeng / Liu, Peiqing / Qu, Qiulin et al. | British Library Online Contents | 2016


    Flow developments above 50-deg sweep delta wings with different leading-edge profiles

    Miau, J. J. / Kuo, K. T. / Liu, W. H. et al. | AIAA | 1995