Fiber-reinforced composites have been recently applied as the potential material for engine fan blades, because of their light weight and high specific strength. In the design of the fan blade, the foreign-object impact is one of the greatest concerns. In particular, the bird-strike impact tends to take place by the suction at the air inlet during the operation. Since the damage induced by such an impact can lead to the engine stall, the detailed knowledge on the behavior of the composite subjected to the bird-strike impact is needed for the safety concerns. In this study, we have constructed a numerical method to analyze the bird-strike impact as a soft body impact on cantilevered composite panel. Especially, we present a stabilized dynamic contact algorithm based on Lagrange multipliers method to predict the impact force on the panel. This method has been verified through the comparison with the experimental results. Its numerically stable characteristics enable us to apply the proposed method to a wide range of impact problems, including soft-body, high-velocity impact due to the bird-strike. This method helps simulating the bird-strike problem on the composite fan blade.