基于可压缩格子Boltzmann方法的激波/边界层干扰模拟研究

Shock wave/boundary layer interaction is one of the most complex flow phenomena in high-speed flight field. It exists widely in the internal/external flows of transonic, supersonic and hypersonic vehicles. Shock wave/boundary layer interaction has a crucial influence on the propulsion system and overall performance of vehicles. However, the phenomena and mechanism of shock wave/boundary layer interaction is not completely understood yet. Lattice Boltzmann method is a mesoscopic method, which is more basic than the macroscopic fluid mechanics equations and contains more physical information. As a result, lattice Boltzmann method has advantages in simulating multi-scale complex fluid systems. In recent years, the lattice Boltzmann method has great progress in high-speed compressible model. The compressible lattice Boltzmann method provides a new direction to study shock wave/ boundary layer interactions. In the proposed projects, the numerical simulation and analysis of shock wave/boundary layer interaction are carried out by potential energy double-distribution-function compressible lattice Boltzmann method in which the large eddy simulation and parallel computing are introduced. The results of this study will help us to understand the physical mechanism of shock wave/boundary layer interaction in a more detailed way, explore new ways to reduce the harm and use the advantages of shock wave/boundary layer interaction, which provide the theoretical foundation and basis for the shape and engine design of high speed vehicles.

激波/边界层干扰是高速飞行领域最为复杂的流动现象之一，广泛存在于跨声速、超声速及高超声速飞行器内/外流场中，对飞行器推进系统及整体性能有着至关重要的影响。但是目前对激波/边界层干扰的流动现象和物理机制仍然缺乏全面的理解和认识。格子Boltzmann方法作为一种介观方法，比宏观流体力学方程更基本，包含更多的物理内涵，在模拟多尺度的复杂流体系统时有优势。近些年格子Boltzmann方法在高速可压缩模型方面取得了很大进展。可压缩格子Boltzmann方法为研究激波/边界层干扰提供了一个全新的视角。本项目拟在势能双分布函数可压缩格子Boltzmann方法的基础上，结合大涡模拟和并行计算，对激波/边界层干扰进行数值模拟和分析。研究结果有助于更加细致地了解激波/边界层干扰的物理机制，探索降低激波/边界层干扰危害、利用激波/边界层干扰特性的新途径，为高速飞行器外形及发动机的工程设计提供理论基础和依据。