Dynamic Stall Control Over a Rotor Airfoil Based on AC DBD Plasma Actuation

Abstract

At present, the control capability of dielectric barrier discharge (DBD) plasma actuation covers the flow velocity range of helicopter’s retreating blades, so it is necessary to extend it to the dynamic stall control of rotor airfoils. A DBD plasma actuator was adopted to control the dynamic stall of an oscillating CRA309 airfoil in this paper. The effectiveness of alternating current (AC) DBD plasma actuation on reducing the area of lift hysteresis loop of the oscillating airfoil was verified through pressure measurements at a Reynolds number of 5.2×105. The influence of actuation parameters on the airfoil’s lift and moment coefficients was studied. Both steady and unsteady actuation could effectively reduce the hysteresis loop area of the lift coefficients. The flow control effect of dynamic stall was strongly dependent on the history of angle of attack. Compared with the steady actuation, unsteady actuation had more obvious advantages in dynamic stall control, with reducing the area of lift hysteresis loop by more than 30%. The effects of plasma actuation on the airfoil’s flow field at both upward and downward stages were discussed at last.

Study on the Active Control of the Dynamic Stall of Rotor Airfoils Based on Plasma Excitation

“…They deduced that the lift coefficient increased by 7.1%, and the aerodynamic hysteresis area decreased by almost 4%. Shi et al [20] studied the impacts of different motion and plasma excitation parameters on dynamic stall control. They deduced that the pitch oscillation frequency and excitation frequency are critical factors affecting the control effectiveness.…”