Numerical Investigation of the Over-the-Wing Distributed Propeller Aerodynamics Using Potential Flow Panel Method

This study presents a numerical investigation of the key factors influencing the aerodynamic efficiency of the over-the-wing distributed propeller (OTWDP) configuration. The OTWDP layout is compared against two alternative propulsion architectures: the front-wing distributed propeller configuration and the over-the-wing single propeller (OTWP) configuration. An enhanced mid-fidelity potential flow panel method solver is employed to predict the aerodynamic loading of each configuration with improved computational efficiency and accuracy. The simulation framework is based on the NASA X-57 Maxwell electric aircraft, incorporating its wing geometry and high-lift propeller design tailored for low-speed lift augmentation. The results reveal that both the rotation direction and spacing between adjacent propellers in distributed propulsion systems have a significant influence on overall aerodynamic performance. Specifically, optimized propeller spacing and rotation patterns can lead to notable gains in lift-to-drag ratio. Under similar total thrust conditions, the OTWDP configuration is shown to achieve higher aerodynamic efficiency compared to the OTWP configuration. These findings underscore the potential advantages of distributed propulsion integration over the wing for improving low-speed flight performance in electric or hybrid-electric aircraft designs.