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.