Study on the Influence of Distributed Propeller Slipstream Effects Considering Lift-Enhancing Characteristics

This study investigates the slipstream effect generated by a distributed propeller configuration on an aircraft designed for lift enhancement. A numerical simulation approach adopting the Multiple Reference Frame (MRF) method is implemented to assess the influence of key propeller parameters, such as disc diameter and rotational speed, on the slipstream. A specific distributed propeller layout aimed at enhancing lift is proposed and examined. The aerodynamic interference caused by the propeller slipstream on the full aircraft is systematically studied, with a focus on its impact on overall aerodynamic characteristics. The results indicate that the slipstream effect is highly sensitive to variations in propeller disc diameter and rotational speed. Specifically, increasing the rotational speed or reducing the disc radius intensifies the slipstream. However, higher speeds may lead to challenges in power requirements and motor compatibility. For the distributed layout, the propeller flow not only accelerates the wake but also interacts with the wing, leading to segmentation and a reorganization of the vortex structure. This interaction drastically alters the pressure distribution over the wing surface. Consequently, both the lift and drag coefficients increase under slipstream conditions. Furthermore, the slipstream’s induced flow delays boundary layer separation at key areas, resulting in improved stall characteristics.