This paper investigates the control of leading-edge flow separation over an airfoil using a dielectric-barrier discharge plasma actuator. A chord-based Reynolds number and an angle of attack are 2.6 × 10 5 and 18.8 deg, respectively. The flow around the stalled airfoil is computed by using large-eddy simulations. The body-force distribution-based plasma actuator model is adopted and set near the leading edge of the airfoil. Effects of a nondimensional burst frequency with a constant duty cycle on the performance of flow control are studied. It is found that, for the cases of the nondimensional burst frequencies 5, 10, 25, and 50, lift-to-drag ratios increase in comparison with that in the cases of the burst frequencies 1 and 100 and without the control. Controlled flow separates near the 30% chord from the leading edge due to adverse pressure gradient associated with the angle of attack. Mechanisms of suppression of the leading-edge flow separation in those cases are discussed.


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    Title :

    Plasma-Actuator Burst-Mode Frequency Effects on Leading-Edge Flow-Separation Control at Reynolds Number 2.6 × 10 5


    Contributors:
    Aono, Hikaru (author) / Kawai, Soshi (author) / Nonomura, Taku (author) / Sato, Makoto (author) / Fujii, Kozo (author) / Okada, Koichi (author)

    Published in:

    AIAA Journal ; 55 , 11 ; 3789-3806


    Publication date :

    2017-07-18


    Size :

    18 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English