Analysis and modeling the influence of distributed propeller slipstreams on aircraft wing

Distributed Electric Propulsion aircrafts are a novel concept in electric aviation, characterized by the wing-propeller interaction. The interaction depends on several factors, such as the distance between the wing and propeller, the wing chord-to-propeller diameter ratio, the angle between the wing and the propeller, and so on. Firstly, the MRF model was utilized to simulate the APC9060 propeller and to analyze the wing-propeller interaction. This study focuses on the angle between the wing and the propeller, examining its impact on the interaction. A multiplicative factor was introduced to quantify the effects of propeller slipstream velocity and develop a surrogate model for this factor. An independent, low-cost DEP slipstream experimental platform was designed for model parameterization. The numerical simulation revealed that the slipstream increased the flow velocity on the wing surface and enlarged the low-pressure area on the upper surface of the wing. The results from experiments demonstrated the model accurately predicted lift changes as the angle of attack varied from 11 to 15 degrees.