Dynamic stall control over a rotor airfoil based on AC DBD plasma actuation

Advances in Aerodynamics

Guoqiang Li¹  Yong Huang¹  Yongdong Yang¹  Hesen Yang²  Guangyin Zhao³ 

[1] Low Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, 621000, Mianyang, China;Science and Technology on Plasma Dynamics Laboratory, Air Force Engineering University, 710038, Xi’an, China;State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, 621000, Mianyang, China;Low Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, 621000, Mianyang, China;

关键词: Plasma actuation;    Flow separation;    Dynamic stall;    Hysteresis;    Dielectric barrier discharge;   

DOI  :  10.1186/s42774-021-00061-2

来源: Springer

【 摘 要 】

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.

【 授权许可】

CC BY