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NACA (national advisory committee for aeronautics) airfoils have been generated according to the NACA standards. The effects of fluid flow have been studied over the two airfoils 4412 and S1223 through computational fluid dynamics. The comparison was done on the basis coefficient of lift and coefficient of drag. The angle of attack was varied and their effect was seen on velocity, pressure, coefficient of lift and coefficient of drag. In the present research the angle of attack will be varied from 0 degree to 15 degree with the increment of 5 degree.

Study of NACA 4412 and Selig 1223 airfoils through computational fluid dynamics