Abstract: The static stall about the airfoil at the high angle ofattack deteriorate the characteristics of aerodynamics rapidly. But thisphenomena can be delayed effectively by the dynamic stall caused by theunsteady motion. The dual-step Roe schema developed by Rogers wasused to solve the incompressible Navier-Stokes equations. Computationallysimulated the dynamic stall about the pitching NACA0015 airfoil withidentical pitching rate (\alpha =0^\circ \sim 60^\circ), at Low Reynoldsnumber (Re=4.8 \times 10^4). And compared with Walker's experimentalresults to correct the CFD results. The developments of the mainvortex, the second vortex and the third vortex, and the lift coefficientalteration to the angle of attack during the process were studied. Finally,the effects of the different pitching rate to the dynamic stall werecompared.