The actuator disk model applied in ducted fan based on self-developed "TRI sonic Platform"(TRIP 3.0) is developed, and the aerodynamic characteristics of BWB analog low-speed aerodynamics configuration with and without ducted fan are analyzed. Firstly, the computational results of thrust and torque of a single propeller are in good agreement with the testing data. Secondly, in order to achieve the designed fan thrust, the key parameters of blade number, mounting angle and rotational speed of a isolated ducted fan are calculated. Finally, applied the key parameters in ducted fan of aircraft, a BWB analog low-speed aerodynamics configuration with and without ducted fan are presented. The results show that pressure coefficients distribution at fuselage and tail had obvious effect with ducted fan compared to without fan. By sucking the forward flow with ducted fan, the flow speed above the fuselage was increased and the angle of attack of horizontal tail was decreased. Therefore, the lift and pitching moment coefficients of fuselage and horizontal tail influenced by with and wihout fan were obvious. Otherwise, in the range of little angle of attack, with the effect of ducted fan, the lift and pitching moment of fuselage is increased and horizontal tail is decreased, but for the entire aircraft, the different of lift and pitching moment coefficients with and without ducted fan is comparatively small.