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

Abstract

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