No abstract

No abstract

No abstract

The turbulent model selection was carried out on a three-dimensional wing profile, NACA model, with pronounced camber for automotive applications. The analysis was conducted for five turbulent models [Spalart-Allmaras, SST k-Omega, k-kL-Omega, Transient SST, and Reynolds Stress] at various angles of attack ranging from 0 to 45 degrees, with a velocity of 50 m/s. To perform the analysis, Ansys Fluent solver was used under steady-state conditions with a tetrahedral mesh geometry consisting of 444,623 cells, determined based on sensitivity analysis, where grid refinement is near the wing profile to accurately represent the boundary layer. A steady flow analysis was chosen, varying the angle of attack to compare the results with those provided by the National Advisory Committee for Aeronautics (NACA). The selection of the turbulent model was made using a statistical approach that highlights the model that best approximates the mean values of drag and lift forces