等离子体合成射流改善翼型气动性能实验研究

Experimental Investigation of Enhancing Wing Aerodynamic Performance by Plasma Synthetic Jet

等离子体合成射流(PSJ)是一种新型主动流动控制激励器,目前研究大多集中于激励特性,对于流动控制的应用研究还明显不足。为了深入探究PSJ翼型流动分离的控制能力与规律,以高升力翼型为载体,在翼型前缘施加等离子体合成射流激励(PSJA),研究激励器对升力特性的影响。结果表明:在翼型前缘施加PSJA,可以有效抑制流动分离;近失速迎角状态下,各个激励频率下都能产生良好的控制效果;过失速迎角状态下,低频效果最好,随激励电压增加,有效频率范围变宽;激励效果随来流速度增加而减弱,当来流速度20m/s时,翼型的失速迎角提高5°,最大升力系数提高8.1%;当来流速度为40m/s时,失速迎角提高3°,最大升力系数提高4.5%。

Plasma synthetic jet （PSJ） is a new active flow control actuator. Currently, the most of the stud- ies focuses on the excitation characteristic of PSJ rather than the application characteristic in flow fields. In order to further investigate the ability of the PSJ actuators to control the low-speed flow separation on a high lift configu- ration, this paper installs plasma synthetic jet actuator （PSJA） on the leading edge of wing and studies the influ- ence of PSJA on the lift characteristics of wing. Results show that the flow separation can be suppressed by PSJ. PSJ in a large frequency range can produce efficient control results in near stall angle of attack condition. Howev- er, in post stall angle of attack condition, the PSJ with a low-frequency is better. With the increase of input volt- age, the effective frequency range is widened. With the increase of inflow velocity, the control effect becomes worse. When the inflow velocity is 20m/s, the stall angle of attack increases 5°, the maximum lift coefficient in- creases 8.1%; when the inflow velocity rises to 40m/s, the stall angle of attack increases 3°, the maximum lift coefficient increases 4.5%.