类乘波飞行器进气道/隔离段数值仿真研究

Numerical Simulation of Quasi-waverider's Inlet/isolator

采用二维耦合隐式NS方程和标准k-ε湍流模型对超燃冲压发动机进气道/隔离段进行了数值仿真研究,分析了隔离段出口反压、长高比以及进气道入口马赫数对进气道出口性能参数的影响,发现反压对进气道出口参数影响很小;长高比对进气道出口上下壁面处静压影响较大,但对出口处马赫数及静温影响很小;进气道入口马赫数的变化对出口上下壁面处静压影响剧烈,且随着入口马赫数的增加,进气道出口马赫数和静温均增加,入口马赫数越低,进入隔离段内的气流越均匀。

The two-dimension coupled implicit Naviers-Stokes equations and standard κ-εviscid models were introduced to simulate the flow of inlet/isolator in the scramjet engine. The effect of back pressure, length-to-height of isolator and Math number of inlet entrance on the specifications of inlet exit was discussed. It is concluded that the effect on the pa- rameters of inlet exit is hot obviovy; the effect on static pressure of upper and lower wall of inlet exit is bigger, but the effect on roach number and static pressure is the effect of freestream mach number on static pressure of upper and lower wall is acute, and with the increase of free-stream mach number, math number and static temperature are rising, the flow is more uniform when free-stream mach number is lower.