Escoamento sobre o perfil aerodinâmico NACA 4412

Abstract

The objective of this work is to obtain the distribution of velocity and pressure, together with the coefficients of drag and lift NACA 4412 airfoil in a subsonic subjected to two-dimensional, incompressible and steady flow. The distribution of the pressure coefficient, cp, around the airfoil, the drag coefficient, cD, lift coefficient, cL, velocity profiles in the extrados and intrados, within the boundary layer, the velocity field, the field were obtained static pressure field and the turbulent kinematic viscosity with angle of attack ranging from 0 to 18 °. It was observed that for angles of attack of 0 to 16 ° there is an increase in the coefficients of lift and drag. For angles greater than 16 ° attack is the sudden drop in lift coefficient due to detachment of the boundary layer that characterizes the phenomenon of stall. From this angle of attack of flow has a larger recirculation zone and thus kinematic eddy viscosity (featuring a higher production of turbulence). The results for the drag coefficient and lift coefficient showed good agreement with experimental data found in literature. This indicates that the Spalart-Allmaras turbulence model used satisfactorily describes the behavior of the turbulent flow over the NACA 4412 profile.