边界层效应影响等离子体气动激励诱导激波机理  

Mechanism investigation on boundary layer affecting shock wave induced by plasma aerodynamic actuation

作　　者：程邦勤[1] 孙权[1] 喻永贵[1] 孔维嵩[1] 刘嘉[2] 

机构地区：[1]空军工程大学飞行器与动力工程系,西安710038 [2]空军工程大学电子科学系,西安710038

出　　处：《强激光与粒子束》2011年第8期2093-2096,共4页High Power Laser and Particle Beams

基　　金：国家自然科学基金项目(50776100)

摘　　要：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。Based on the experimental result of inducing shock wave in a small-scale short duration supersonic wind tunnel, this paper illustrated the theory of inducing shock wave that was not only lied on Joule heating effect but also decided by the discharge area thickness of boundary layer. Moreover, the experimental investigation on inducing plasma shock wave in the hyper sonic wind tunnel in order to confirm such theory drew the conclusion that under the condition that the boundary layer is very thin the plasma aerodynamic actuation could induce oblique shock wave. This paper discussed the theory of inducing shock wave in these two different conditions and also confirmed the key effect of boundary layer in plasma and shock wave interaction.

关 键 词：边界层 等离子体气动激励 焦耳热效应 激波 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]