For Blade Element Momentum (BEM) theory, the airfoil data needs to be as accurate as possible. Nowadays, Computational Fluid Dynamics (CFD) is used for optimization and design of turbine application. Lift coefficient, drag coefficient and lift coefficient over drag coefficient are significant parameters for turbine application. Selecting a suitable computational tool is crucial for design of the turbine. Panel method and an integral boundary layer formulation are combined in the MOIL code for the analysis of potential flow around the airfoils. In this study, XFOIL code and Transition SST k-omega model were used to predict the aerodynamic performance at low Reynolds numbers (Re = 3x10<^>5, 4x10<^>5, 5x10<^>5). The results were compared and CFD results and XFOIL, code result are compatible with each other until stall angle. Also XFOIL, and CFD results were shown a good coherence with literature.