Some aspects in the numerical simulation of the aerodynamics of a NACA 0012 airfoil

The paper discusses the numerical simulation of the aerodynamics of an airfoil at different angles of attack. Two approaches to determining the angle of attack are considered: by changing the position of the velocity vector of the oncoming flow and by changing the relative position of the flat airfoil. The value of the angle of attack varies in the range from −5 to +10°. Numerical simulation is performed with the openFoam package for solving continuum mechanics problems in the stationary setting based on finite volumes using the rhoSimpleFoam solver. The study results in the values of flow velocity and pressure, partially determined by the method of setting the angle of attack. A significant influence of the method of setting the angle of attack on the calculated aerodynamic coefficients is demonstrated. The mathematical correctness and numerical ambiguity of the considered approaches are assessed. A comparison among the drag coefficients, together with a qualitative analysis of the fields of physical quantities, shows incorrectness in determining the angle of attack by changing the position of the incoming flow velocity vector.