基于Fluent的边界层转捩仿真研究

基于Fluent软件,利用已有的RANS求解器,采用SST k-omega湍流模型,对Aerospatiale-A翼型流体绕流问题进行了数值模拟,分析了不同攻角下翼型流场的速度与压力分布云图,并在攻角为13.1°与13.3°条件下,将仿真计算结果与国外风洞实验数据进行了对比分析。结果显示,在该条件下,能够观测到边界层转捩现象,并且直接数值模拟结果与已有的风洞实验数据吻合,验证了仿真结果的可靠性。

Research on the simulation of boundary layer transition based on the software of Fluent

Boundary layer transition is of great significance in many applications of CFD engineering based on the Fluent software,this paper uses the existing RANS solver and the SST k-omega turbulence model to simulate the flow around the Aerospatiale-A airfoil. The velocity and pressure distributions of airfoil flow field under different attack angles are analyzed. Under the condition of attack angle of 13.1 degree and 13.3 degree,the simulation results are compared with the experimental data of wind tunnel abroad. The results show that the boundary layer transition can be observed under this condition and the results of direct numerical simulation agree well with the experimental data of wind tunnel. The simulation study of this model provides a theoretical reference for the subsequent research and prediction of the boundary layer transition phenomenon.