Dynamic stall control over an airfoil by NS-DBD actuation

作     者：He-Sen Yang Guang-Yin Zhao Hua Liang Biao Wei 杨鹤森;赵光银;梁华;魏彪

作者机构：Science and Technology on Plasma Dynamics LaboratoryAir Force Engineering UniversityXi'an 710038China State Key Laboratory of AerodynamicsChina Aerodynamics Research and Development CenterMianyang 621000China 

出 版 物：《Chinese Physics B》 (中国物理B（英文版）)

年 卷 期：2020年第29卷第10期

页      面：370-379页

核心收录：

学科分类：080103[工学-流体力学] 08[工学] 080104[工学-工程力学] 0825[工学-航空宇航科学与技术] 0801[工学-力学（可授工学、理学学位）] 

基　　金：Project supported by the National Natural Science Foundation of China(Grant No.11802341) the Open Fund from State Key Laboratory of Aerodynamics of China(Grant No.SKLA20180207) 

主　　题：flow control dynamic stall dielectric barrier discharge(DBD) nanosecond pulse reduced frequency 

摘      要：The wind tunnel test was conducted with an NACA 0012 airfoil to explore the flow control effects on airfoil dynamic stall by NS-DBD plasma actuation. Firstly, light and deep dynamic stall states were set, based on the static stall characteristics of airfoil at a Reynolds number of 5.8 × 105. Then, the flow control effect of NS-DBD on dynamic stall was studied and the influence law of three typical reduced frequencies (k = 0.05, k = 0.05, and k = 0.15) was examined at various dimensionless actuation frequencies (F+ = 1, F+ = 2, and F+ = 3). For both light and deep dynamic stall states, NS-DBD had almost no effect on upstroke. However, the lift coefficients on downstroke were increased significantly and the flow control effect at F+ = 1 is the best. The flow control effect of the light stall state is more obvious than that of deep stall state under the same actuation conditions. For the same stall state, with the reduced frequency increasing, the control effect became worse. Based on the in being principles of flow separation control by NS-DBD, the mechanism of dynamic stall control was discussed and the influence of reduced frequency on the dynamic flow control was analyzed. Different from the static airfoil flow separation control, the separated angle of leading-edge shear layer for the airfoil in dynamic stall state is larger and flow control with dynamic oscillation is more difficult. The separated angle is closely related to the effective angle of attack, so the effect of dynamic stall control is greatly dependent on the history of angles of attack.