Design of target propeller slipstream under propeller-wing interaction

被引：0
|
作者：
Xue C. [1 ,2 ]
Zhou Z. [1 ,2 ]
Fan Z. [1 ,2 ]
Li X. [1 ,2 ]
机构：
[1] School of Aeronautics, Northwestern Polytechnical University, Xi'an
[2] Science and Technology on Unmanned Aerial Vehicle Laboratory, Northwestern Polytechnical University, Xi'an
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2021年 / 36卷 / 01期
关键词：
Distributed electric propulsion(DEP); Drag reduction; Kriging surrogate model; Propeller design; Slipstream;
D O I：
10.13224/j.cnki.jasp.2021.01.013
中图分类号：
学科分类号：
摘要：
For the multi-propeller aircraft with distributed electric propulsion (DEP) configuration, a method to improve the lift-to-drag ratio of the wing was developed by optimizing the propeller slipstream. A propeller design method which can obtain the target induced velocity distribution was proposed. Based on the panel method, an aerodynamic program Prop-wing that can quickly calculate the propeller-wing interference was developed. An efficient optimization method based on Kriging surrogate model was established to obtain the optimal induced velocity distribution and raise the lift-to-drag ratio of the wing. The optimization results showed that the larger axial induced velocity near the propeller hub meant the larger lift drag ratio of the downstream wing. When the power of the propeller was not limited, the optimized propeller can reduce the drag of the downstream wing-segment by 18.75% and increase the lift-to-drag ratio of wing-segment by 25.63% compared with the propeller with the minimum energy loss; when the power of the optimized propeller was limited, the lift-to-drag ratio of the wing-segment increased to 9.62%. Although the lift-to-drag ratio is raised at the cost of propeller efficiency reduction, the research still provides an idea for the use of distributed propeller slipstream. © 2021, Editorial Department of Journal of Aerospace Power. All right reserved.
引用
收藏
页码：104 / 118
页数：14
相关论文
共 36 条
  • [1] FLITTIE K, CURTIN B., Pathfinder solar-powered aircraft flight performance, Simi Valley, California: the 23rd Atmospheric Flight Mechanics Conference, (1998)
  • [2] NOLL T, BROWN J, PEREZ D M, Et al., Investigation of the helios prototype aircraft mishap report: Voume Ⅰ, (2004)
  • [3] ZHANG Jian, ZHANG Dehu, Essentials of configuration design of hale solar-powered UAVs, Acta Aeronautica et Astronautica Sinica, 37, pp. 1-7, (2016)
  • [4] STOLL A M, BEVIRT J B, MOORE M D, Et al., Drag reduction through distributed electric propulsion, Proceedings of AIAA Aviation Technology, Integration, and Operations Conference, pp. 16-20, (2014)
  • [5] STOLL A M., Comparison of CFD and experimental results of the LEAPTech distributed electric propulsion blown wing, Proceedings of AIAA Aviation Technology, Integration, and Operations Conference, pp. 22-26, (2013)
  • [6] KIM H D, PERRY A T, ANSELL P J., A review of distributed electric propulsion concepts for air vehicle technology, AIAA/IEEE Electric Aircraft Technologies Symposium, (2018)
  • [7] DENG Lei, QIAO Zhide, YANG Xudong, Et al., Multi-point/objective optimization design of high lift-to-drag ratio for NLF airfoils, Acta Aerodynamic Sinica, 29, 3, pp. 76-81, (2011)
  • [8] ZHANG Weizhi, HE Dexin, ZHANG Zhaoshun, The design and experiment study for a high airfoil at low reynold numbers, Acta Aerodynamic Sinica, 16, 3, pp. 98-102, (1998)
  • [9] DRELA M., Low-Reynolds-number airfoil design for the M.I.T.Daedalus prototype: a case study, Journal of Aircraft, 25, 8, pp. 724-732, (1988)
  • [10] SELIG M S, GUGLIELMO J J., High-lift low reynolds number airfoil design, Journal of Aircraft, 34, 1, pp. 72-79, (1997)
1234