Research and experimental validation of loose coupling design method for propulsion wing unit

Based on the research background of advanced aerodynamic design technology of distributed hybrid electric propulsion aircraft, a loose coupling design method of rectangle ducted fan unit under engineering constraints is proposed for the propulsive/aerodynamic coupling problem of distributed propulsion wing. Through the coupling iteration of the rotor blade design optimization module influenced by the duct wall and the duct wall design optimization module based on a given rotor blade momentum source model, the complexity of the design problem is effectively reduced, and the multi-objective design optimization considering both hovering and forward flight characteristics of the rectangle ducted fan unit is achieved for this complex, multi-parameter object. Finally, the effectiveness and feasibility of the present loose coupling design method are verified through wind tunnel tests including force and pressure measurements.