The impact of the computational domain discretization method on the results of flow simulations around the NACA 0012 airfoil profile

<ns3:p>This article analyzes the impact of the method of computational domain discretization on the results of flow simulations around the NACA 0012 airfoil profile. For this purpose, a set of structural and hybrid meshes differing in the number of elements and the value of the 〖wall y〗^+ parameter were constructed, based on which the profile flow simulations were performed. Numerical studies were carried out using ANSYS FLUENT software and consisted in determining the aerodynamic coefficients of the NACA 0012 profile and comparing their values with experimental data. The analyses carried out made it possible to determine the impact of the type of mesh and its main parameters on the reliability of the numerically obtained results.</ns3:p>