激 波 /平 板 层 流 边 界 层 干 扰 熵 增 特 性

There exist complex shock wave/boundary layer interaction phenomena in supersonic flow. The main sources of aerodynamic drag in scramjet engines are“friction drag”caused by boundary layer and“wave drag” caused by shock wave,both of which are directly related to entropy increase,so entropy increase is the key parameter to evaluate the aerodynamic drag. Discrete Boltzmann Modeling and Analysis Method(DBM)based on nonequilibrium statistical physics is used to simulate high mach number regular reflection and shock wave/laminar boundary layer interaction problem. With the help of high-order non-conserved kinetic moments,DBM can easily capture thermodynamic non-equilibrium effects such as viscosity and heat conduction,and quantify the entropy production rate caused by them. The results show that for regular reflection,the non-equilibrium intensity of the reflected shock wave is stronger than that of the incident shock wave. For shock wave/laminar boundary layer interaction,entropy production rate caused by viscosity is dominant in shock wave,and entropy production rate caused by heat conduction is dominant in boundary layer. The intensity of the two entropy production rates increases with the increase of Mach number. The research results can provide theoretical guidance for evaluating the flow quality in the inlet.