Winglet parametrics study: CFD and wind tunnel

[EN] On this project we will complete a parametric CFD study for a 2-D NACA 0012 airfoil determining the minimum mesh needed to guarantee convergent values for CL and CD using di erent turbulence models. Also, we will perform a wind tunnel parametric analysis to establish which is the best type of winglet geometry under certain ying conditions. Before considering the results obtained from the CFD analysis as correct we must compare them with the real values. Thus, the minimum distance to satisfy result convergence and correct results occurs in the k - turbulence model. For = 0o we get CL = 0 and CD = 0:006 On the other hand, the wind tunnel parametric study establishes which is the winglet geometry that has the minimum drag for di erent values of angle of attack at a given velocity of 11 m/s. The nal conclusion states that when varies from 2 [0o-12o] the double winglet has the lowest drag. The lift to drag ratio, L/D, establishes that the winglet with the highest L/D ratio will depend on the angle of attack.