等离子体气动激励控制激波的机理研究

针对等离子体气动激励控制激波的热效应机理和电离效应机理的争议，分别采用热阻塞模型和离子声波模型，理论推导出了不同机理前提下电弧等离子体对尖劈斜激波的影响规律.对于热效应机理，激波变化规律是激波起始点前移、形状不弯曲以及角度减小；对于电离效应机理，激波变化规律是激波起始点仍维持在尖劈前缘点处、形状分为两段发生弯曲以及起始段的角度增大.针对该对立的理论推导结果，进行了电弧等离子体控制尖劈斜激波的超声速风洞实验研究，实验观察到尖劈斜激波起始点前移4 mm，激波角度减小8.6%，激波形状未发生弯曲.以热效应机理为前提推导出的理论结果与该实验结果相符，从而验证了等离子体气动激励控制激波是热效应机理在起主要作用. 关键词： 等离子体气动激励 激波 热效应 电离效应

The mechanism investigation on shock wave controlled by plasma aerodynamic actuation

In order to distinguish whether thermal mechanism or ionization mechanism dominates shock wave control process by plasma aerodynamic actuation, the transformation rules of wedge oblique shock wave control by arc discharge plasma were theoretically deduced using thermal choking model and ionic sound wave model respectively. If the thermal mechanism dominates shock wave control process, the shock wave start point will shift upward, its shape will not bend and its angle will decrease. However, if the ionization mechanism dominates shock wave control process, the shock wave start point will maintain at the wedge forward apex, its shape will bend as two subsections and its angle of first subsection will increase. Then the wedge oblique shock wave control by arc discharge plasma was studied in a small-scale short-duration supersonic wind tunnel, and the test results showed that the shock wave start point shifted upward 4 mm, its angle decreased 8.6% and its shape did not bend, which demonstrated that the thermal mechanism dominated the shock wave control process by plasma aerodynamic actuation.