真实气体效应下高马赫数内转进气道特性研究

为初步研究高马赫数内转进气道在真实气体效应下的工作特性,首先设计额定工作状态Ma=12的高超声速内转进气道,再结合不同气体模型对其进行数值模拟。研究结果表明:化学非平衡气体在流场结构、工作性能和气动加热方面与热完全气体较为相近,与热化学非平衡气体存在一定差别。离解反应发生在边界层内和低速涡流区内,热化学非平衡气体的离解反应程度比化学非平衡气体大。在隔离段内激波反射处,相比完全气体,化学反应气体的静温降低了2000～2500K。高热流区在上壁面喉道位置与下壁面激波反射点位置附近,温度较高的等温壁面、热化学非平衡气体均可降低壁面热流密度,不同壁面条件对隔离段出口性能参数影响较为明显。真实气体效应、壁面温度对隔离段涡流区的影响较为复杂,有待进一步研究。

Study on the characteristics of high Mach number inward turning inlet under real gas effect

In order to preliminarily study the working characteristics of the high Mach number inward turning inlet under real gas effect, firstly design the hypersonic inward turning inlet with rated working state Ma=12, and then numerically simulate it with different gas models. The results shows that the chemical non-equilibrium gas is similar in flow field structure, performance and aerodynamic heating to thermally perfect gas, and there is a certain difference from thermochemical non-equilibrium gas. The dissociation reaction occurs in the boundary layer and the low-speed vortex region, and the degree of dissociation reaction of the thermochemical non-equilibrium gas is larger than that of the chemical non-equilibrium gas. At the shock reflection in the isolator, the static temperature of the chemical reaction gas decreases by about 2000-2500K compared with that of the complete gas. The high heat flow region is close to the location of the throat on up-wall and the reflection point of the shock wave on low-wall.The higher temperature isothermal wall and thermochemical non-equilibrium gas can reduce the wall heat flux density. Different wall conditions have obvious influence on performance parameters of isolator outlet. The effects of real gas effects and wall temperature on the vortex zone of isolator are complex and need further study.