基于AC-DBD等离子体激励的NACA0012翼型动态失速控制  

Dynamic Stall Control of NACA0012 Airfoil Using AC-DBD Plasma Actuators

作　　者：沙珺 史志伟[1] 陈臻 姚张奕 SHA Jun;SHI Zhi-wei;CHEN Zhen;YAO Zhang-yi(MIIT Key Laboratory of Unsteady Aerodynamics and Flow Control, Department of Aerodynamics, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China)

机构地区：[1]南京航空航天大学航空学院空气动力学系非定常空气动力学与流动控制工信部重点实验室,江苏南京210016

出　　处：《气体物理》2021年第3期50-61,共12页Physics of Gases

摘　　要：以NACA0012翼型为研究对象,采用动态测压及PIV测量技术,研究了AC-DBD等离子体激励器对翼型俯仰及耦合运动动态失速的控制作用和机理.研究表明,等离子体激励能够显著推迟失速迎角,抑制失速后的升力系数陡降,提前流动再附和升力系数回升,减小升力及俯仰力矩系数曲线迟滞环面积,改善翼型气动特性.研究了不同运动参数及激励器设置参数对控制效果的影响,结果表明翼型俯仰运动频率及激励器激励频率分别对激励器控制效果影响最大,为后续相关研究提供了数据基础.In order to study the control effect and mechanism of AC-DBD plasma actuators on NACA0012 airfoil,dynamic pressure measurement and PIV measurement were used in research of dynamic stall control over pitching and coupled motion.The results show that the plasma actuators can significantly delay the stall angle of attack,suppress the sharp drop of lift coefficient,advance the flow reattachment and lift coefficient recovery,reduce the hysteresis loop area of lift and pitch moment coefficient circles and improve the aerodynamic characteristics of airfoil.The influence of different motion parameters and actuator setting parameters on the control effect was studied.The results show that the frequencies of airfoil motion and actuator excitation have the greatest impact on the actuator control effect,respectively.This work also provides a data basis for the following related research.

关 键 词：动态失速 等离子体 流动控制 风洞实验 测压实验 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]