Dynamic stall is observed in numerous applications, including sharply maneuvering fixed-wing aircraft, biomimetics, wind turbines, and most notably, rotorcraft. The associated unsteady loading can lead to aerodynamic flutter and mechanical failure in the system. The present work explores the ability of nanosecond pulse-driven dielectric barrier discharge plasma actuators to control dynamic stall over a NACA 0015 airfoil. The Reynolds number, reduced frequency, and excitation Strouhal number were varied over large ranges: R e = 167 , 000 500 , 000 , k = 0.025 0.075 , and S t e = 0 10 , respectively. Surface pressure measurements were taken for each combination of Reynolds number, reduced frequency, and excitation Strouhal number. Phase-locked particle image velocimetry measurements were acquired for select cases. It was observed that the trends of effect of S t e were similar for all combinations of Reynolds number and reduced frequency, and three major conclusions were drawn. First, it was observed that low Strouhal number excitation ( S t e < 0.5 ) results in oscillatory aerodynamic loading in the stalled stage of dynamic stall. This oscillatory behavior was gradually reduced as S t e increased and was not observed beyond S t e > 2 . Second, all excitation resulted in earlier flow reattachment. Last, it was shown that excitation, especially at high S t e , resulted in reduced aerodynamic hysteresis and dynamic stall vortex strength. The decrease in the strength of the dynamic stall vortex is achieved by the formation of large-scale structures induced by the excitation that bleed the leading-edge vorticity before the ejection of the dynamic stall vortex. At sufficiently high excitation Strouhal numbers ( S t e 10 ), the dynamic stall vortex was completely suppressed.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Control of Dynamic Stall over a NACA 0015 Airfoil Using Plasma Actuators


    Contributors:

    Published in:

    AIAA Journal ; 56 , 1 ; 78-89


    Publication date :

    2018-01-01




    Type of media :

    Conference paper , Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




    Parametric Investigation of Stall Cell Formation on a NACA 0015 Airfoil

    Dell’Orso, Haley / Amitay, Michael | AIAA | 2018


    CONTROL OF DYNAMIC STALL OVER A NACA 0012 AIRFOIL USING NS-DBD PLASMA ACTUATORS

    Whiting, Nicole L. / Castaneda, David / Webb, Nathan J. et al. | TIBKAT | 2020


    Control of Dynamic Stall over a NACA 0012 Airfoil Using NS-DBD Plasma Actuators

    Whiting, Nicole L. / Castaneda, David / Webb, Nathan J. et al. | AIAA | 2020


    Flow Separation Control over a NACA 0015 Airfoil Using Nanosecond-Pulsed Plasma Actuator

    Zheng, Jianguo / Cui, Y. D. / Zhao, Zijie et al. | AIAA | 2018


    Vortex Developments Over NACA 0015 Airfoil with Trailing Edge Jet

    Okong'o, N. / Finaish, F. / Society of Automotive Engineers | British Library Conference Proceedings | 1994