等离子体气动激励抑制机翼失速分离的实验

进行了等离子体气动激励抑制机翼失速分离的风洞实验,研究了等离子体气动激励频率、电压、占空比和激励位置等对流动控制效果的影响.研究表明:在来流速度35m/s时,等离子体气动激励可以有效地抑制机翼大攻角下吸力面的流动分离,将机翼临界失速迎角由17°提高到19°;施加激励后,机翼最大升力系数提高了9.45%,阻力系数减小20.9%;激励频率在200Hz时,控制效果最好,对应的量纲一激励频率为1;迎角越大,流动分离越严重,需要更大的激励电压才能够有效抑制流动分离;最佳激励位置在流动分离起始点的前缘;在流动控制效果相当时,减小占空比可以降低能耗.

Experiment on wing stall separation suppression by plasma aerodynamic actuation

Wind tunnel experimental investigation on wing stall separation suppression was performed and the influence of pulse frequency, voltage, duty cycle and actuation position on flow control effect was analyzed. The results showed that, at the free-stream velocity of 35m/s, the flow separation on the suction side of the wing under large angle of attack was suppressed effectively and the critical stall angle of attack increased from 17° to 19°. The maximum lift coefficient increased by 9.45% with a drag reduction of 20.9%. Experimental results demonstrate that control effect is best when frequency is 200Hz and the corresponding dimensionless actuation frequency is 1. Larger voltage is needed with the increase of the angle of attack because the separation becomes more serious. The best position of plasma aerodynamic actuation is right at the leading edge of the flow separation origin line. Power consumption can be reduced by decreasing the duty cycle at the same control effect.