The CFD analysis of the adaptive airfoil NACA 0024 is subject of this graduate thesis. This project is the realization of a rigid wing-sail to be used as wind assisted propulsion. There are basic terms to be considered in aerodynamics and fluid mechanics before computational fluid dynamics is performed. In reality most kind of fluid flow are turbulent and it is possible to predict future behavior of chaotic, turbulent flow by using turbulence models. The challenge is to design and optimize aerodynamic body shape which maximizes the aerodynamic lift force and minimises drag. An airfoil is the cross-sectional shape of aerodynamic body shape. In computational modeling of turbulent flows, one common objective is to obtain the most efficient angle of attack. The computational domain needs to be discretised into computational grid (or mesh) to solve the discretised of fluid flows. By creating a finite element mesh, with certain settings, all preconditions for starting the simulation are fulfilled and the results are presented in the form of graphs and tables. The simulation results gave us an insight into the lift coefficient to drag coefficient ratio (C_L/C_D ). The lift to drag ratio (C_L/C_D ) indicates airfoil efficiency and shows which is the most efficient angle at which relative wind meets an airfoil. The production of lift and drag vary with changes in the angle of attack . As the angle of attack increases, both the lift coefficient and the drag coefficient increase. Lift force increases up to a certain point. At the critical angle of attack airfoil is producing its maximum lift coefficient. Beyond that point lift decreases but drag continues to increase, so losses caused by vortices increase too. Here simulation is done for velocity of the air mass flow from 5 m/s to 10 m/s and for this airfoil critical angle of attack is in the range of 15° to 18°. It is found that cl/cd ratio is maximum at angle of attack 8 when wind velocity is 10 m/s.