发展和完善模拟激波和湍流共存复杂流动的中心-迎风型混合格式。基于湍流模式理论，并借鉴尺度自适应模拟思想，建立分离涡模拟方法中大涡模拟和雷诺平均计算区域的自适应判断准则，发展高效可靠的自适应分区分离涡模拟方法。采用改进后的分离涡模拟方法研究绕飞行器的可压缩湍流，并深入分析其中的复杂流动机理。本课题开展的研究将为航空航天飞行器的复杂流场计算提供高效可靠的数值方法。此外，通过深化认识绕飞行器的复杂流动中所包含的湍流、激波、旋涡和分离流等基本流动规律，为新型高速飞行器的研制提供空气动力学的理论依据。

A central-upwind hybrid scheme to simulate the complex flow involving shock wave and turbulence will be developed. Based on the turbulence model theory and scale-adaptive simulation idea, large-eddy simulation and Reynolds Averaged Navier-Stokes computational regions in the detached-eddy simulation (DES) method can be determined by a zone-adaptive criterion. Complex flow mechanisms with regard to the compressible turbulent flow past an aerocraft will be investigated in detail using the improved DES technique. Based on the researches in this project, it can give an efficient and reliable numerical method to simulate the complex flow around an aerocraft. Furthermore, the detailed knowledge concerning the turbulence, shock, vortex and separated flow over the aerocraft can provide an aerodynamics theory basis for the new high-speed aerocraft development.