摘要:
根据螺旋桨雷诺相似准则和等离子体射流相似准则,提出了一种基于螺旋桨叶素理论,利用地面实验设备开展平流层螺旋桨等离子体流动控制研究的实验方法。首先根据螺旋桨几何参数和运动参数计算叶素微段来流速度和迎角,然后根据螺旋桨雷诺相似准则确定常压翼型风洞模拟平流层叶素流动的吹风参数,最后根据等离子体射流雷诺相似准则,确定激励器和激励电源参数模拟平流层等离子体射流并评估其流动控制效果。利用该方法研究了20km 高度 S1223翼型螺旋桨的等离子体流动控制效果,实验表明:飞艇以5~20m/s 的速度前进时,SD-BD 激励电压峰-峰值13.6kV,频率10kHz 时,诱导的等离子体射流使螺旋桨300r/min 时推力最大可提高10.9%,600r/min 时推力反而减小了0.52%~1.7%。
Abstract:
According to the propeller Reynolds-similarity theory and the plasma induced jet similarity theory,the method which is used to study the performance of plasma flow control of high-attitude propeller by ground experiment is put forward based on the blade element theory. First,the propeller geometry and motion parameters are converted to the inflow velocity and an-gle of attack on the blade element.Second,the induced plasma voltage and inflow parameters are determined based on the similarity theory in ground experiment.Finally,the collected experi-mental data is processed to assess the aerodynamic performance of propeller.A high-attitude 20km S1223 airfoil propeller plasma flow control experiment is conducted by this method.It is found that when the propeller revolves at the speed of 300r/min under forward velocity of 5 ~20m/s,the thrust of propeller is increased by 6.6%~10.9% with the high voltage AC input, but at the speed of 600r/min the thrust is reduced by 0.52%~1.7%.
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