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.


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    Titel :

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


    Beteiligte:
    Zhao, Guang-yin (Autor:in) / Li, Ying-hong (Autor:in) / Hua, Wei-zhuo (Autor:in) / Liang, Hua (Autor:in) / Han, Meng-hu (Autor:in) / Niu, Zhong-guo (Autor:in)


    Erscheinungsdatum :

    01.09.2015


    Format / Umfang :

    9 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch






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