Propulsion/aerodynamic coupling analytic modeling of distributed propulsion wing unit with induced wing

This study addresses the propulsion/aerodynamic coupling characteristics of distributed propulsion wings (DPW) with induced wings, targeting the development of distributed electric propulsion (DEP) vertical take-off and landing (VTOL) unmanned aerial vehicles (UAVs). An aerodynamic analytic modeling approach is proposed to enable rapid computation and evaluation for the overall design and optimization of such aircraft. The DPW configuration is analyzed to establish modeling priorities, focusing on characterizing the aerodynamic behavior of the DPW unit with induced wing. Aerodynamic analytic models for the DPW unit are developed under both axial flow conditions and non-axial flow conditions with angles of attack, grounded in fluid dynamics theory and mathematical modeling. A corresponding model for the induced wing under ducted jet coupling is also established. The integrated characteristics of this complex system are then mathematically described by superimposing these component models. Validation through CFD simulations and experimental analysis under typical flight configurations demonstrates that the modular modeling approach effectively meets the requirements of aerodynamic design and computation, and the model’s solutions accurately characterize the aerodynamic behavior of the DPW unit under complex configurations.