Comparison of Different Turbulence Models in Numerical Calculation of Low-Speed Flow around NACA0012 Airfoil

Abstract To further develop a more effective turbulence model and improve the calculation accuracy of flow, new was constructed using deformation rate tensor, grouping average. Due to need evaluate applicability in numerical calculation, flow around NACA0012 airfoil with Mach number 0.15 multiple angles attack calculated on OpenFOAM platform based grid independence research. The Spalart-Allmaras (S-A) newly proposed were adopted. surface pressure lift coefficients compared experimental data. It revealed that two models simulated well, S-A slightly better for calculating coefficient. accurate coefficient, thus illustrating preliminary low-speed airfoil.