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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。
In the low speed open wind tunnel, a plasma actuator was used to control the separation of NACA0015 airfoil. PIV technology was used to measure the flow field around the airfoil and show the change of the flow field after plasma excitation. Through the five-component balance measurement of lift and drag, the law of separation and control of airfoil flow by excitation voltage and excitation frequency was studied. The results show that plasma excitation at the airfoil front can control the separation of airfoils effectively. When the flow rate is 20 m / s, the maximum lift coefficient increases 11% and the angle of attack increases by 6 °. Under a given flow regime, there is a threshold for the excitation voltage and excitation frequency. The threshold is different for different angles of attack. The larger the angle of attack, the more severe the separation and the higher the requirement for the excitation intensity.