Abstarct: The use of the two-dimensional Aerodynamic coefficient in a numerical method which analyzes horizontal axis wind turbine such as Actuator line has caused an increase in the calculation errors. Investigating the effect of a 3D correction of the Aerodynamic coefficient on results obtained from Actuator line modeling of the Mexico rotor on OpenFoam is the aim of this study. There are various methods to correct two-dimensional coefficients. In this study, by simulating the blade of the Mexico rotor on Fluent and using the Reduced Velocity Method, lift and drag coefficients for three particular sections of the blade have been corrected. This method has been adopted in order to correct three different speeds 10, 15 and 24 meters per second. Results of the three-dimensional correction have demonstrated that in the near-root sections, the coefficients differed noticeably from the 2D coefficients. The calculated lift coefficient at the nearest section to the root has been estimated 8% less than the two-dimensional coefficients. By increasing distance from the root due to the formation of tip vortices, corrected results and the two-dimensional coefficients converged into the expected results. In the closest section to the blade’s tip, the lift coefficient obtained from the turbulence model has been calculated 5% higher than the 2-D coefficient. The Actuator line model is very powerful to predict the flow behavior around horizontal axis wind turbines. Since it is unnecessary to generate mesh around the boundary laxyer, the high speed of computation is another feature of the Actuator line model. Corrected coefficients have been applied in the Actuator line model and the results of performance parameters were investigated. At r = 1.377 meters, the result of axial velocity has improved to have an error of 4%. This decrease in the calculated error has also been observed in the estimation of axial and tangential distributed forces on the blade. The developed model was able to reduce the error of axial velocity about 16 N. The improvement rate of the design speed was 2% for the thrust calculation and 3% for the torque estimation.