Numerical investigation of the effect of dielectric barrier discharge plasma actuator-induced momentum jet parameters on flow control of an oscillating wind turbine airfoil

Wind turbine blades that undergo pitch-oscillating motion exhibit dynamic stall behavior, deteriorating their aerodynamic performance. In this regard, dielectric barrier discharge (DBD) plasma actuators are promising tools for controlling flow by inducing momentum jet flow. Four key parameters typically determine the jet: length, power, angle, and injection location. This paper presents a numerical study investigates effect of these on control around an SG6042 wind airfoil at Reynolds number Rec=1.35×105. For sake, considers various numbers actuators, force directions, installation locations. utilizes two-dimensional, unsteady Reynolds-averaged Navier–Stokes equations with γ–Reθ transition model. The results demonstrate significant effects control. As location single-DBD moves closer to leading edge, its effectiveness low-pressure vortex growth increases, resulting in smaller lower drag coefficient. Furthermore, increase power length leads effective Vortices airfoil's suction surface recognized as influential factors result, co-flow actuator significantly improves performance region. Flow is augmented when installed near-surface angle. edge case achieves best instance, occurs approximately 5% later than clean configuration.