Abstract: To design low-flow loss supersonic fan blades,a design software of the blades was developed based on numerical optimization method.The blade main geometrical parameters were selected as blade design parameters.For the first stage of fan of inlet flow in axial direction,the objective function was set as minimum flow loss at given specific work.The optimal blades thickness increase along blade chord direction,so the cascade passage is contractive;in general,it results in the decrease of speed and increase of pressure of the supersonic flow passing through the cascades.There are several shock waves in the flow fields of cascades constructed by the optimal blades,and the flow loss is quite low.The design results show the feasibility of this supersonic blade design method,and provide new ideas for supersonic fan blade design.