中文摘要：

开展了多相等离子体气动激励抑制NACA 0015翼型失速分离的实验,详细研究了翼型升阻特性随激励电压、激励相角、输入电压波形和占空比等激励参数的影响.研究表明：雷诺数Re=4.9×105（来流速度60m/s）时,多相等离子体气动激励可有效抑制NACA 0015翼型吸力面的流动分离,将翼型临界失速攻角提高2°;相位对流动控制效果的影响不大;电压幅值和占空比必须达到一定的阈值才能有效抑制流动分离;流动分离被抑制后,维持流动保持附着状态所需的激励电压幅值可以显著降低.研究为揭示多相等离子体流动控制作用机理奠定了基础.

英文摘要：

Experiments on NACA 0015 airfoil stalling separation control based on multiphase plasma aerodynamic actuation were performed in the paper.The effects of the plasma actuation voltage amplitude,phase,input waveform and duty cycle on the lift and drag of the airfoil were examined specifically.The results show that,when the Reynolds number is 4.9×105,multiphase plasma aerodynamic actuation can suppress flow separation very well.The critical stalling attack angle of NACA 0015 airfoil can increase by 2°.The flow suppression effect is not sensitive to phase difference.The separated flow can be suppressed when the voltage amplitude and duty cycle reach their threshold values.Once the separated flow is suppressed,the actuation voltage magnitude maintaining flow attachment could be reduced significantly.The research can lay a foundation for the mechanism of multiphase plasma flow control.