The Aerodynamic Effects of Distributed Propulsion on the Performance of a UAV Wing

Jyun Han Shih, Pei Ching Wang, Ching Yao Chen, Kim Boon Lua*

*此作品的通信作者

研究成果: Article同行評審

1 引文 斯高帕斯(Scopus)

摘要

This study explores the aerodynamic performance of a wing and propeller system through experiments and numerical simulations. Three configurations, including a single tip propeller and four distributed propellers with the same or alternative rotational directions, are tested. The findings demonstrate that the distributed propulsion technique enhances wing performance by generating higher lift but may also increase drag and reduce cruising efficiency. The effects of propeller slipstream on pressure distribution, lift distribution, and boundary layer separation are analyzed, providing insights into the underlying mechanisms. The presence of a single tip propeller improves overall performance, whereas four propellers distributed in front of the leading edge delay stall and enhance the lift-to-drag ratio at high angles of attack. At these high angles of attack, an interesting phenomenon occurs in which the propeller slipstream is deflected upward toward the upper surface of the wing. This upward deflection of the slipstream plays a crucial role in suppressing separation of the boundary layer above the wing. This phenomenon effectively delays stall and significantly enhances the overall aerodynamic performance of the wing.

原文English
文章編號04024123
期刊Journal of Aerospace Engineering
38
發行號2
DOIs
出版狀態Published - 1 3月 2025

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