Compared with isolated propellers of the same size, the ducted fan has become one of the most promising electric propulsion methods for aviation electrification due to its qualities of high aerodynamic efficiency, excellent safety and low aerodynamic noise. In this paper, a complete set of aerodynamic design process for electrically driven ducted fan is constructed based on the design guideline of Aero-engine compressor, with full consideration of the design characteristics of ducted fan. Taking the 60kW-class ducted fan as the research object, the overall performance scheme is firstly determined by thermal calculation, then the one-dimensional design is carried out based on the geometric relationship, and the three-dimensional modeling of the blades is further completed according to the law of the velocity triangle along the radial section. On this basis, the influence of five key parameters on the aerodynamic performance of the fan, such as rotor/stator solidity, rotor/stator aspect ratio, and the axial gap between rotor and stator, are investigated in detail. Special emphasis is placed on analyzing the effects of the geometric parameters of the fan on the performance indexes such as pressure ratio, efficiency, surge margin, and average outlet airflow angle.