This paper reports the results of experiments in which flush-mounted pulsed-direct-current plasma actuator arrays were used to achieve skin-friction drag reduction on a NACA 63012A airfoil at a zero attack angle over the Mach number range of 0.3 M 0.5 corresponding to a chord Reynolds number range of 4.2 × 10 6 R e c 7 × 10 6 . The objective of the experiments was to document both the level of drag reduction and the net power savings achievable over this Mach number range. The arrays were designed to produce a spanwise array of opposed wall jets confined to the turbulent boundary-layer buffer region. These served to intervene in the autonomous near-wall mechanism that produces buffer-layer streamwise vorticity and is largely responsible for high levels of friction drag. It was demonstrated that the actuator array produces unprecedented levels of friction drag reduction with significant net power savings. Perhaps most interesting was the observation that the actuator authority has to be reduced for increased Mach numbers in order to keep the wall jets confined to the turbulent boundary-layer buffer region. This gave rise to a net power savings that scaled as M 3.5 . Unlike many previous experiments with plasma actuators, these results show that this form of flow control would not be authority limited in actual flight applications.


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    Titel :

    Airfoil Friction Drag Reduction with Net Power Savings Using Pulsed-Direct-Current Plasma Actuation


    Beteiligte:
    Thomas, Flint O. (Autor:in) / Corke, Thomas C. (Autor:in) / Duong, Alan H. (Autor:in)

    Erschienen in:

    AIAA Journal ; 61 , 9 ; 4045-4055


    Erscheinungsdatum :

    2023-06-09


    Format / Umfang :

    11 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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