The NACA0012 isolated airfoil at different angels of attack is numerically simulated with SIMPLE algorithm and GAO-YONG turbulence equations.The problem of checkerboard prediction of pressure was cured by evaluating the cell face velocities by the momentum interpolated principle.In order to improve the calculation precision

an orthogonal body fitted coordinate system was selected and a second-order HLAP discretization for the convective part was used.Separated flow structures over the isolated airfoil at different angles of attack and corresponding aerodynamic parameters are presented in details.By comparing with the experimental data and the results of the large-eddy simulation

it shows the GAO-YONG turbulence equations without using empirical coefficients and wall functions successfully simulate the separated flow pattern on the airfoil surface

and accurately predict the location of separation and the aerodynamic force coefficients.In addition

the results of GAO-YONG turbulence equations are better than that of k-ε、k-ω、k-ω sst turbulence models in the software of FLUENT soft.