航空工程进展2012，Vol.3Issue(3)：289-293,5.
低速翼型分离流动的等离子体主动控制研究
Study on the Plasma Active Control in the Low-speed Airfoil Separation Flow
摘要
Abstract
The discharge pattern, the characteristics of flow induced by plasma aerodynamic actuation, and the impacts of angle of airfoil and free flow speed on the airfoil flow separation suppression effect are investigated re- spectively. Active flow control investigation of NACA 0015 airfoil by stagger electrode dielectric barrier plasma actuation is performed under low velocity and Reynolds number conditions. The results indicate that the mode of dielectric barrier plasma discharge is filamentary discharge; the direction of the flow induced by the plasma actu- ator is from the upper electrode down to the bottom electrode, which depends on the distribution of electrodes and has nothing to do with the actuator＇s wiring mode; when the inflow velocity is 25 m/s, corresponding Reynolds number is 2.03× 10^5 , plasma aerodynamic actuation can effectively suppress flow separation on the suction side of the airfoil, which causes a 9.7 ~ augment of maximal coefficient of lift, and the stall angle of the airfoil increases from 17.5° to 20.5°. The real reason for the stall delay of airfoil is not a simple gas accelera- tion; it has been discovered that the effectiveness of the plasma actuation decreases as the speed of free flow in- creases, further exploration of unsteady plasma excitation or the coupling effect between plasma and flow field, maybe have great potential.关键词
等离子体/流动控制/介质阻挡放电/翼型/流动分离Key words
plasma/flow control/dielectric barrier discharge/airfoil/flow separation分类
航空航天引用本文复制引用
徐长群,杨波,孟宣市,李华星..低速翼型分离流动的等离子体主动控制研究[J].航空工程进展,2012,3(3):289-293,5.基金项目
国家自然科学基金（60801010）西北工业大学基础研究基金（JC200901）中国博士后科学基金 （）
