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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

[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.