Propulsion/aerodynamic coupling modeling for distributed-propulsion-wing with induced wing configuration

This paper proposes a propulsion/aerodynamic coupling model for the distributed-propulsion-wing with induced wing configuration based on the research on distributed-propulsion vertical takeoff and landing vehicles, combined theoretical models and engineering assumptions. This model enables real-time and rapid calculation of the aerodynamic performance of distributed-propulsion-wing with induced wing configuration within the entire flight envelope, including vertical takeoff, transition, and cruise phases. Firstly, a fast calculation method for ducted jet velocity is developed by combining the ducted flow field model and the ducted thrust enhancement coefficient. Then, based on the momentum theory, the propulsion-aerodynamic coupling model is derived for both powered and unpowered conditions. Finally, the characteristics of the propulsion-aerodynamic coupling model are analyzed, and CFD simulations and analyses conducted for typical flight conditions. The results show that the proposed propulsion/aerodynamic coupling model for the distributed-propulsion-wing with induced wing configuration exhibits high accuracy and fast computation speed, meeting the real-time calculation requirements for dynamic system analysis and flight control system design.