双燃式(超燃)冲压发动机中激波与边界层之间相互作用对内部流动的影响

The Effect of Interaction of Shock Waves with BoundaryLayers to The Cold Internal Flow Field of A Dual Combustor Scramjet Model

在激波风洞中研究了激波与边界层之间相互作用对双燃式（超燃）冲压发动机进气道和燃烧室冷态内部流场的影响，实验发现在进气道中，激波与边界层之间的相互作用产生了两侧均为超声速流的滑移面。实验结果表明内涵道（亚燃室）中流动状态的变化与激波－边界层之间相互作用密切相关。

In this paper,the effect of interaction of shock waves with boundary layers to the cold internal flow field of the inlet and combustor of a dual combustor scramjet model has been investigated in a shock tunnel.It has been found that there was a contact surface caused by the interaction of shock waves with boundary layers on each side of which the flow was supersonic in the inlet.It has been proved that the flow state was closely related to the interaction of shock waves with boundary layers in the pilot duct.