According to the conception of the forward sweep leading edge, this paper puts the design of forward sweep leading edge into the blade of NASA67 rotor. The Navier - Stokes equations, Baldwin - Lomax algebraic turbulence model, finite volume method and Runge - Kutta time stepping schemes are used in analyzing the effect on the performance of blade by the different forward degree of leading edge. The rather extensive computed results give three preliminary conclusions: (1 ) the efficiency of the forward sweep blade is higher than that of non-sweep blade; ( 2 ) the forward sweep blade can remarkably improve the stability and the scope of flux, and the influences are increasing with the increase of the forward sweep degree; ( 3 ) the pressure ration of the forward sweep blade is lower than that of the non-sweep blade, and the pressure ratio is decreased with the increase of the forward sweep degree.