For the active film cooling is deemed as one of the ideal thermal protection measures for the surface of high-speed or hypersonic vehicle, studies on the flow and heat transfer characteristics is significant to effectively protect the inlet and provide guidelines for the inlet design. 主动式气膜冷却被认为是高超声速飞行器表面的一种理想热防护措施之一,因此研究与之相关的流动规律与传热特性对有效地保护进气道、指导进气道设计有着重要的意义。