A fast optimization method for the propeller layout of distributed propulsion aircraft

The aerodynamic performance of distributed propulsion aircraft is significantly influenced by the propeller layout. Identifying the optimal relative position between propellers and wings is a critical task during the conceptual design phase of aircraft development. This study took the Tecnam P2006T aircraft as a reference model and utilized the vortex lattice method combined with a back propagation (BP) neural network to rapidly calculate and predict the lift coefficient, the drag coefficient, and the lift-to-drag ratio under different propeller layout configurations. The optimal propeller layout position is determined from the perspective of minimizing the takeoff distance and maximizing overall aerodynamic performance. Compared to the aerodynamic performance of the original propeller layout, the optimized configuration significantly improves the propeller slipstream effect, improves the lift coefficient and lift-to-drag ratio, and reduces the ground roll takeoff distance. This method provides a practical solution for the rapid optimization of leading-edge propeller layouts for distributed propulsion aircraft.