介质阻挡放电等离子体对翼型流动分离控制的实验研究(英文)

Investigation of flow separation control on an airfoil using DBD plasma actuators

在低速开口风洞中进行了等离子体激励器对NACA0015翼型流动分离控制的实验研究。采用PIV技术,对翼型绕流流场进行了测量,显示了施加等离子体激励后流场的变化。通过五分量天平对升力和阻力的测量,研究了激励电压和激励频率对翼型流动分离控制的规律。研究表明,低风速下在翼型前缘施加等离子体激励,能够有效地控制翼型流动分离,在来流为20 m/s时,最大升力系数增加11%,失速迎角增加6°;在给定的流动状态下,激励电压和激励频率存在一个阈值,不同迎角下该阈值不同,迎角越大,分离越严重,对激励强度的要求也越高。

Influence of plasma actuators on the flow separation control of NACA 0015 airfoil was investigated in an open-circuit low-speed wind tunnel. Particle Image Velocimetry （PIV） technology was applied to visualize the modification of the flow structure over the airfoil by the plasma actuators. Lift and drag were measured by a five-component strain gauge balance to inves- tigate the separation control effect of the actuator voltage and excitation frequency. The results show that the leading-edge plasma actuators are effective in controlling the flow separation over the airfoil at low wind speeds. The maximum lift coefficient and stall angle are increased by 11 % and 6 deg respectively at the free-stream velocity of 20m/s. However,at a given flow state, there exists threshold values for both the actuator voltage and excitation frequency on the actuators. The threshold values are different with the changing attack angles. At the higher attack angles, the plasma actuator＇s authority must be increased due to the much stronger flow separation on the airfoil.