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On-line Access: 2022-01-26

Received: 2021-04-23

Revision Accepted: 2021-07-25

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Cited: 0

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Citations:  Bibtex RefMan EndNote GB/T7714

 ORCID:

Yao LEI

https://orcid.org/0000-0002-4764-2081

Wen-jie YANG

https://orcid.org/0000-0001-9356-1090

Yi-yong HUANG

https://orcid.org/0000-0002-4724-6804

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Journal of Zhejiang University SCIENCE A 2022 Vol.23 No.1 P.27-39

http://doi.org/10.1631/jzus.A2100192


Aerodynamic performance of distributed electric propulsion with wing interaction


Author(s):  Yao LEI, Wen-jie YANG, Yi-yong HUANG

Affiliation(s):  School of Mechanical Engineering and Automation, Fuzhou University, Fuzhou 350116, China; more

Corresponding email(s):   yaolei@fzu.edu.cn

Key Words:  Distributed electric propulsion (DEP), Aerodynamics, Low Reynolds numbers, Wing interaction


Yao LEI, Wen-jie YANG, Yi-yong HUANG. Aerodynamic performance of distributed electric propulsion with wing interaction[J]. Journal of Zhejiang University Science A, 2022, 23(1): 27-39.

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Abstract: 
distributed electric propulsion (DEP) uses multiple propellers driven by motors distributed along the leading edge of the wing to produce beneficial aerodynamic interactions. However, the wing will be in the sliding flow of the propeller and the lift and drag characteristics of the wing will change accordingly. The performance of the propeller will also be affected by the wing in its rear. In this paper, combined with wind tunnel tests, the low Reynolds aerodynamic properties of multiple DEP structures are numerically simulated by solving the Reynolds averaged Navier-Stokes (RANS) equation of multiple reference frames (MRF) or slip grid technology. The results demonstrate that the lift and drag of DEP increase in all cases, with the magnitude depending on the angle of attack (AOA) and the relative positions of propellers and wing. When the AOA is less than 16° (stall AOA), the change of lift is not affected by it. By contrast, when the AOA is greater than 16° the L/D (lift-to-drag ratio) of the DEP system increases significantly. This is because the propeller slipstream delays laminar flow separation and increases the stall AOA. At the same time, the inflow and the downwash effect, which is generated on both sides of the rotating shaft, result in the actual AOA of the wing being greater than the free flow AOA with a fluctuation distribution of the lift coefficient along the span. Also, for the propeller in the DEP, the blocking effect of the wing and the vortex of the trailing edge of the wing result in a significant increase in thrust.

考虑机翼干扰的分布式电力推进系统的气动性能分析

目的:分布式电力推进(DEP)系统可以通过沿机翼前缘分布的多个旋翼来提高系统整体气动性能。本文旨在探讨不同旋翼安装位置产生的涡流尾迹与机翼之间的气动干扰对系统整体气动性能的影响,尤其是升阻力系数的变化。
创新点:1.推导旋翼与机翼相互干扰时的气动模型。2.对比数值模拟与风洞实验得到不同旋翼位置对DEP气动性能的影响。
方法:1.通过理论推导,建立DEP系统旋翼与机翼相互干扰时的气动模型;2.通过数值模拟,得到不同构型的DEP系统的升阻力系数变化、压力以及流速变化;3.通过风洞实验,对比数值模拟确定不同旋翼位置的DEP系统的升阻力系数,也验证数值模拟的有效性并确定模拟精度。
结论:1.旋翼加速了DEP系统的轴向气流和下洗流,适当排布的旋翼可大幅提高系统升力。2.迎角小于16°(失速攻角)时,DEP系统的升力变化不明显,机翼的升阻力减小。3.在负迎角和迎角大于16°时机翼具有更高的升力和升阻比,有利于整机爬升或下降。

关键词:分布式推进系统;空气动力学;低雷诺数;机翼干扰

Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article

Reference

[1]ArefP, GhoreyshiM, JirasekA, et al., 2018. Computational study of propeller–wing aerodynamic interaction. Aerospace, 5(3):79.

[2]BorerNK, PattersonMD, VikenJK, et al., 2016. Design and performance of the NASA SCEPTOR distributed electric propulsion flight demonstrator. 16th AIAA Aviation Technology, Integration, and Operations Conference.

[3]BreljeBJ, JRRAMartins, 2019. Electric, hybrid, and turboelectric fixed-wing aircraft: a review of concepts, models, and design approaches. Progress in Aerospace Sciences, 104:1-19.

[4]ErhardRM, ClarkeMA, AlonsoJJ, 2021. A low-cost aero-propulsive analysis of distributed electric propulsion aircraft. AIAA Scitech 2021 Forum.

[5]EslamiE, TadjfarM, NajafiS, 2013. Aerodynamic performance of Parastoo UAV. Aircraft Engineering and Aerospace Technology, 85(2):97-103.

[6]GallaniMA, GoesLCS, NeroskyLAR, 2020. Effects of distributed electric propulsion on the performance of a general aviation aircraft. AIAA Propulsion and Energy 2020 Forum.

[7]GohardaniAS, DoulgerisG, SinghR, 2011. Challenges of future aircraft propulsion: a review of distributed propulsion technology and its potential application for the all electric commercial aircraft. Progress in Aerospace Sciences, 47(5):369-391.

[8]KayaD, KutayAT, 2014. Aerodynamic modeling and parameter estimation of a quadrotor helicopter. AIAA Atmospheric Flight Mechanics Conference.

[9]KohlmanDL, 1979. Flight test results for an advanced technology light airplane. Journal of Aircraft, 16(4):250-255.

[10]KongXH, ZhangZR, LuJW, et al., 2018. Review of electric power system of distributed electric propulsion aircraft. Acta Aeronautica et Astronautica Sinica, 39(1):46-62 (in Chinese).https://doi:10.7527/s1000-6893.2017.21651

[11]LeiY, YeYQ, 2020. Aerodynamic characteristics of a hex-rotor MAV with three coaxial rotors in hover. IEEE Access, 8:221312-221319.

[12]LeknysRR, ArjomandiM, KelsoRM, et al., 2018. Leading-edge vortex development on a pitching flat plate with multiple leading edge geometries. Experimental Thermal and Fluid Science, 96:406-418.

[13]LiangJY, ZhangJL, ZhangX, et al., 2013. Energy management strategy for a parallel hybrid electric vehicle equipped with a battery/ultra-capacitor hybrid energy storage system. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 14(8):535-553.

[14]MianAA, WangDB, 2008. Dynamic modeling and nonlinear control strategy for an underactuated quad rotor rotorcraft. Journal of Zhejiang University-SCIENCE A, 9(4):539-545.

[15]MooreKR, NingA, 2018. Distributed electric propulsion effects on existing aircraft through multidisciplinary optimization. AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference.

[16]NguyenDH, LiuY, MoriK, 2018. Experimental study for aerodynamic performance of quadrotor helicopter. Transactions of the Japan Society for Aeronautical and Space Sciences, 61(1):29-39.

[17]PattersonMD, GermanBJ, 2015. Simplified aerodynamics models to predict the effects of upstream propellers on wing lift. 53rd AIAA Aerospace Sciences Meeting.

[18]PattersonMD, BorerNK, 2017. Approach considerations in aircraft with high-lift propeller systems. 17th AIAA Aviation Technology, Integration, and Operations Conference.

[19]PattersonMD, DerlagaJM, BorerNK, 2016. High-lift propeller system configuration selection for NASA’s SCEPTOR distributed electric propulsion flight demonstrator. 16th AIAA Aviation Technology, Integration, and Operations Conference.

[20]StollAM, BevirtJ, MooreMD, et al., 2014. Drag reduction through distributed electric propulsion. 14th AIAA Aviation Technology, Integration, and Operations Conference.

[21]VeldhuisLLM, HeymaPM, 2000. Aerodynamic optimisation of wings in multi-engined tractor propeller arrangements. Aircraft Design, 3(3):129-149.

[22]ViswanathanV, KnappBM, 2019. Potential for electric aircraft. Nature Sustainability, 2(2):88-89.

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