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Rapid Design Method of Heavy-Loaded Propeller for Distributed Electric Propulsion Aircraft

Author

Listed:
  • Shijie Shi

    (School of Aeronautics and Astronautics, Guilin University of Aerospace Technology, Guilin 541004, China)

  • Jiabo Huo

    (School of Aeronautics and Astronautics, Guilin University of Aerospace Technology, Guilin 541004, China
    School of Aerospace Sciences, National University of Defense Technology, Changsha 410073, China)

  • Zhongbao Liu

    (Caihong UAV Technology Co., Ltd., China Academy of Aerospace Areodynamics, Beijing 10074, China)

  • Aicheng Zou

    (School of Aeronautics and Astronautics, Guilin University of Aerospace Technology, Guilin 541004, China)

Abstract

On Distributed Electric Propulsion (DEP) aircraft, the deployment of numerous high-lift propellers with small diameters on the wing’s leading edge significantly enhances lift during low-speed flight. The increase in the number of propellers leads to a decrease in diameter, which increases the disc loading. In this paper, a rapid design method applicable to heavy-loaded propellers is developed and does not require iterative calculations compared to traditional heavy-loaded propeller design methods, enabling rapid completion of the propeller design. The results of CFD computation show that the relative thrust error of the method proposed in this paper is within 5% for disc loading ranging from 600 Pa to 1400 Pa, features a high-accuracy design of propellers with required thrust, and high thrust coefficients are achieved within large advance ratio range.

Suggested Citation

  • Shijie Shi & Jiabo Huo & Zhongbao Liu & Aicheng Zou, 2024. "Rapid Design Method of Heavy-Loaded Propeller for Distributed Electric Propulsion Aircraft," Energies, MDPI, vol. 17(4), pages 1-17, February.
    • Handle: RePEc:gam:jeners:v:17:y:2024:i:4:p:786-:d:1334632
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