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.

中文翻译：

---

基于AC DBD等离子驱动的转子翼型动态失速控制

目前，电介质阻挡放电（DBD）等离子致动的控制能力已覆盖直升机后退叶片的流速范围，因此有必要将其扩展到旋翼机翼的动态失速控制中。本文采用DBD等离子致动器来控制振荡的CRA309机翼的动态失速。通过在5.2×105的雷诺数下进行压力测量，验证了交流电（DBD）等离子体等离子体致动减小了振荡翼型的升程磁滞回线面积的有效性。研究过。稳态和非稳态致动均可有效地减小升力系数的磁滞回线面积。动态失速的流量控制效果在很大程度上取决于迎角的历史。与稳态致动相比，非稳态致动在动态失速控制中具有更明显的优势，将电梯滞后回线的面积减少了30％以上。最后讨论了等离子体驱动在向上和向下阶段对翼型流场的影响。