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针对小型暂冲式超声速风洞进行的诱导激波实验结果,提出等离子体气动激励诱导激波的机理不仅取决于放电时产生的焦耳热效应,放电区域的边界层厚度也起到了决定性的作用的推论。为进一步验证此思想,在高超声速激波风洞进行了等离子体气动激励诱导激波的实验研究。结果表明,在边界层很薄的情况下,等离子体气动激励能够诱导出斜激波。分别阐述了两种实验条件下诱导激波的机理,证实了边界层效应在等离子体与激波相互作用中起到了决定性作用。
The experimental results of inducing shock waves in a small transient supersonic wind tunnel suggest that the mechanism of shock induced by plasma pneumatically depends not only on the Joule heating effect during discharge but also on the boundary layer thickness in the discharge region. . In order to further verify this idea, an experimental study of inducing shock wave induced by plasma aerodynamic excitation was carried out in a hypersonic wind tunnel. The results show that the plasma aerodynamic excitation can induce oblique shock waves when the boundary layer is very thin. The mechanisms of induced shocks under two experimental conditions are elucidated respectively. It is confirmed that the boundary layer effect plays a decisive role in the interaction between plasma and shock wave.