低速三角翼纳秒脉冲等离子体激励实验

在30m/s来流速度下,进行了纳秒脉冲介质阻挡放电等离子体气动激励改善47°后掠角钝前缘三角翼气动特性的测力实验.为寻求优化的激励位置,实验研究了5种不同激励位置的流动控制效果.实验结果表明:激励位置对流动控制效果有决定性影响,位于三角翼前缘的等离子体气动激励能有效改善三角翼的气动特性,推迟失速,而上翼面不同展向位置的等离子体气动激励的流动控制效果十分微弱;激励频率是流动控制效果的重要影响因子,激励电压峰峰值为13kV时,激励频率为200Hz下的流动控制效果最好,在迎角30°时可使升力系数由1.31增大到1.44,增大9.6%,升阻比提高3.3%.

Experiment on low-speed delta wing using nanosecond pulse plasma actuation

Force measurement experiment was conducted to improve the aerodynamic characteristics of 47 degree sweep blunt leading edge delta wing using nanosecond pulse dielectric barrier discharge plasma aerodynamic actuation at the freestream flow velocity of 30m/s. In order to investigate the optimized actuation position, flow control effects at five different actuation positions were studied experimentally.The results show that the actuation position determines flow control effect.Plasma aerodynamic actuation at leading edge of delta wing can significantly improve the aerodynamic characteristics of delta wing and delay stall, while plasma aerodynamic actuations at different spanwise positions on the upper surface have little effect on the flow control.It is also found that flow control effect depends on actuation frequency.When the peak-peak actuation voltage is 13kV and actuation frequency is 200Hz, the flow control effect is best, which increases lift coefficient from 1.31 to 1.44 by 9.6% at attack angle of 30 degree, with lift-drag ratio by 3.3%.