To investigate the influence of the real-gas effect on the flow of the inward-turning inlet while an air-breathing propulsion system flies at a high Mach number, gas models of thermally perfect gas, chemical non-equilibrium gas, and thermochemical non-equilibrium gas are used for numerical simulation of the inward-turning inlet at Mach 12. The results show that the dissociation reaction is the most severe in the initial stage of the stream-wise vortex and the attachment area of the slip-line near the symmetry plane. The degree of the dissociation reaction in thermochemical non-equilibrium gas is more severe than in chemical non-equilibrium gas. In the thermochemical non-equilibrium gas model, the dissociation degree of oxygen reaches 54.8% at the symmetry plane, and the vortex area of the isolator exit is the smallest, which makes the performance at the isolator exit different from the other two gas models. The real-gas effect in thermochemical non-equilibrium gas has a more obvious influence on the flow characteristics and performance of the inward-turning inlet at Mach 12.

为了研究当进气驱动系统以高马赫数飞行时，气体对内向进气流的影响，包括热完美气体，化学非平衡气体和热化学非气体的气体模型。平衡气体用于对12马赫的向内进气口进行数值模拟。结果表明，离解反应在流向涡流的初始阶段和对称附近滑移线的附着区域最严重。飞机。热化学不平衡气体中的离解反应的程度比化学不平衡气体中的离解反应的程度更严重。在热化学非平衡气体模型中，氧气在对称平面上的解离度达到54.8％，并且隔离器出口的涡流面积最小，这使得隔离器出口处的性能不同于其他两种气体模型。热化学非平衡气体中的实际气体效应对12马赫的向内进气口的流动特性和性能有更明显的影响。