Inflatable wings possess charming potential in airships and future morphing aircrafts. But the structural features of inflatable soft wing are obviously different with traditional hard wing, and there are many bumps on the profile of inflatable wing. The effects of these bumps on aerodynamical and aeroelastical behavior get increasing attention from researchers recently. This paper constructed the CFD models of smooth NACA0015 airfoil and bumpy inflatable wing(named 0015F2 airfoil) with CFX software. Numerical results show that 0015F2 airfoil has larger stall attack angle than NACA0015 airfoil, but the slope of the lift coefficients vs attack angel curve and the lift-drag ratio of bumpy wing is lower than the smooth NACA0015 airfoil. The effects of the bumps on boundary layer can be grasped though analysis of the velocity profiles normal to the surface at different chord locations. The bumpy airfoil promotes a thicker boundary layer than that of the smooth airfoil at the same chord locations. The unsteady simulations show that the vortices form within each vicinity of the bumps, and these vortices prevents the separation seen in the smooth airfoil simulations so that the stall angel of attack is increased.