摘要：The aim of the resent work is to predict the aerodynamic performance of modified NACA 4415 airfoil using computational fluid dynamics modelling. The performance is compared to that of NACA 4415 Standard. The simulation is performed using FLUENT with the variables of freestream velocity (i.e. 3, 4, 5, and 18 m/s) and angle of attacks (i.e. -12°, -10°, -8°, -6°, 0°, 6°, 12°, 14°, 16°, 18°, and 20°). The results indicate that the modified NACA 4415 airfoil has better lift and momentum coefficient. The value of lift coefficient of modified NACA 4415 is relatively higher than NACA 4415, especially at -12° < α <-8° and 12° < α <20°. In addition, the momentum coefficient of the modified NACA 4415 is also higher than the NACA 4415 at -12° < α <20°.
