Wind-tunnel experiments are used to study the effect of momentum coefficient and excitation frequency on flow separation using synthetic jet actuation. Experiments are conducted on a NACA 0025 airfoil at a chord-based Reynolds number of 100,000 and angle of attack of 10 deg. The actuator is located near the leading edge, downstream of the mean separation location. High-frequency excitation is able to reattach the flow and eliminate the large-scale vortex shedding in the wake, leading to a decrease in drag of approximately 45%. Low-frequency excitation is employed to target the instabilities associated with the separated shear layer and vortex shedding in the wake. Excitation of the wake instability also causes the flow to reattach; however, it leads to organization of the large-scale vortex shedding. By forcing the boundary layer at the frequency of the shear-layer instability, the threshold momentum required to reattach the flow is an order of magnitude smaller as compared with high-frequency excitation, and the large-scale vortex shedding is suppressed.


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    Titel :

    Flow Reattachment Using Synthetic Jet Actuation on a Low-Reynolds-Number Airfoil



    Erschienen in:

    Erscheinungsdatum :

    2015




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :

    Klassifikation :

    BKL:    55.50 Luftfahrzeugtechnik / 55.60 Raumfahrttechnik / 55.60 / 50.93 / 55.50 / 50.93 Weltraumforschung
    Lokalklassifikation TIB:    770/7040



    Flow Reattachment Using Synthetic Jet Actuation on a Low-Reynolds-Number Airfoil

    Feero, Mark A. / Goodfellow, Sebastian D. / Lavoie, Philippe et al. | AIAA | 2014




    Dynamic Airfoil Flow Separation and Reattachment

    Ericsson, L.E. | Online Contents | 1995


    Separation and Reattachment in Transonic Airfoil Flow

    E. STANEWSKY AND B. H. LITTLE | AIAA | 1971