Dynamic Stall Control around Practical Airfoil Using Nanosecond-Pulse-Driven Dielectric Barrier Discharge Plasma Actuators
Dynamic Stall Control around Practical Airfoil Using Nanosecond-Pulse-Driven Dielectric Barrier Discharge Plasma Actuators
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DOI：
10.3390/en13061376
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发表时间：
2020-03
期刊：
影响因子：
3.2
通讯作者：
Yuto Iwasaki;T. Nonomura;Koki Nankai;K. Asai;Shoki Kanno;Kento Suzuki;A. Komuro;A. Ando;
中科院分区：
文献类型：
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作者：
Yuto Iwasaki;T. Nonomura;Koki Nankai;K. Asai;Shoki Kanno;Kento Suzuki;A. Komuro;A. Ando;
对纳秒脉冲驱动介质阻挡放电等离子体激励器（ns-DBDPA）在动态失速流中的流动控制效果进行了实验研究。 ns-DBDPA 安装在直升机桨叶形式的机翼模型的前缘。该模型在弦长的 25% 附近周期性振荡。使用压力分布计算空气动力系数，该压力分布是通过模型内部传感器测量非稳态压力而获得的。利用气动系数讨论了流量控制效果及其对俯仰振荡和 ns-DBDPA 控制参数的敏感性。采用自由流速度、平均攻角和折减频率作为振荡参数。此外，采用脉冲电压的无量纲频率、峰值脉冲电压以及ns-DBDPA的类型和位置作为控制参数。结果表明，ns-DBDPA可以降低气动系数的滞后性，并且在所有情况下都获得了流量控制效果。采用低无量纲频率的脉冲电压可以使流量控制效果最大化。
The flow control effects of a nanosecond-pulse-driven dielectric barrier discharge plasma actuator (ns-DBDPA) in dynamic stall flow were experimentally investigated. The ns-DBDPA was installed on the leading edge of an airfoil model designed in the form of a helicopter blade. The model was oscillated periodically around 25% of the chord length. Aerodynamic coefficients were calculated using the pressure distribution, which was obtained by the measurement of the unsteady pressure by sensors inside the model. The flow control effect and its sensitivity to pitching oscillation and ns-DBDPA control parameters are discussed using the aerodynamic coefficients. The freestream velocity, the mean of the angle of attack, and the reduced frequency were employed as the oscillation parameters. Moreover, the nondimensional frequency of the pulse voltage, the peak pulse voltage, and the type and position of the ns-DBDPA were adopted as the control parameters. The result shows that the ns-DBDPA can decrease the hysteresis of the aerodynamic coefficients and a flow control effect is obtained in all cases. The flow control effect can be maximized by adopting the low nondimensional frequency of the pulse voltage.