Abstract-In the present work, we studied numerical and experimentally analysis lift and drag performances of NACA 0015 airfoil at different attack angle at low Reynolds numbers (Re) by measuring the forces every two degrees from 0° to 20°. The experiment test was conducted in low speed wind tunnel, and the numerical analysis was performed using CFD program which was FLUENT. The results obtained from experiment and numerical were compared. In this study, stall angle depended on turbulent occurred behind airfoil was determined. As result, effect of the stall angle of airfoil performance was investigated.Index Terms-Angle of attack, CFD, NACA 0015, wind tunnel.

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