Reconstruction design of propeller induced flow-field based on aerodynamic loading distributions

WANG Kelei; ZHOU Zhou; ZHU Xiaoping; GUO Jiahao; FAN Zhongyun

doi:10.7527/S1000-6893.2019.23118

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2020 , Vol. 41 >Issue 1: 123118 - 123118

DOI: https://doi.org/10.7527/S1000-6893.2019.23118

Fluid Mechanics and Flight Mechanics

Reconstruction design of propeller induced flow-field based on aerodynamic loading distributions

WANG Kelei ,
ZHOU Zhou ,
ZHU Xiaoping ,
GUO Jiahao ,
FAN Zhongyun

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1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. Yangtze River Delta Research Institute, Northwestern Polytechnical University, Taicang 215400, China;
3. School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China

Received date: 2019-04-29

Revised date: 2019-07-11

Online published: 2019-07-22

Supported by

Equipment Pre-research Program (41411020401); Civil Aircraft Project (MJ-2015-F-009); Taicang Innovation Leading Institute Project (TC2018DYDS24)

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Abstract

Based on the innovative developing concept of the distributed electric propulsion aircrafts, the reconstruction design of the propeller induced flow-filed is carried out in this study to obtain the maximum propeller/wing integrated aerodynamic efficiency. First, the quasi-steady numerical simulation technique is developed based on the momentum source method, then the relationship between the aerodynamic loading distributions and the propeller induced flow-field properties is established. Second, the optimization design method developed for the reconstruction of the propeller induced flow-field is proposed by controlling the parameterized aerodynamic loading distribution profiles. Finally, both the reliability and efficiency of the proposed aerodynamic design concept are studied. The results show that compared with the minimum induced loss propeller, the optimized aerodynamic loading distributions on the propeller disk lead to significant improvement of the wing aerodynamic performance under the slipstream effect. As a result, the wing section has a relative lift augmentation of 10.40%, a relative drag decrease of 7.05%, and a relative lift-to-drag increment of 18.77%.

Key words： distributed electric propulsion; propeller; momentum source; aerodynamic loading distribution; flow-field reconstruction

Cite this article

WANG Kelei , ZHOU Zhou , ZHU Xiaoping , GUO Jiahao , FAN Zhongyun . Reconstruction design of propeller induced flow-field based on aerodynamic loading distributions[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020 , 41(1) : 123118 -123118 . DOI: 10.7527/S1000-6893.2019.23118

References

[1] WELLS D. NASA green flight challenge:Conceptual design approaches and technologies to enable 200 passenger miles per gallon[C]//11th AIAA Aviation Technology, Integration, and Operations (ATIO) Conference, including the AIAA Balloon Systems Conference and 19th AIAA Lighter-Than-Air Technology Conference. Reston, VA:AIAA, 2011.
[2] 黄俊, 杨凤田. 新能源电动飞机发展与挑战[J]. 航空学报, 2016, 37(1):57-68. HUANG J, YANG F T. Development and challenges of electric aircraft with new energies[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(1):57-68(in Chinese).
[3] KIM H, BROWN G, FELDER J. Distributed turboelectric propulsion for hybrid wing body aircraft[C]//Proceedings of 2008 International Powered Lift Conference. London:Royal Aeronautical Society, 2008.
[4] TIAN W. Review of more-electric aircrafts[C]//Proceedings of 2016 IEEE Chinese Guidance, Navigation and Control Conference, 2016.
[5] KIM H. Distributed propulsion vehicles[C]//27th International Congress of the Aeronautical Sciences, 2010.
[6] 孔祥浩, 张卓然, 陆嘉伟, 等. 分布式电推进飞机电力系统研究综述[J]. 航空学报, 2018, 39(1):021651. KONG X H, ZHANG Z R, LU J W, et al. Review of electric power system of distributed electric propulsion aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(1):021651(in Chinese).
[7] AMIR S, GEORGIOS D, RITI S. Challenges of future aircraft propulsion:A review of distributed propulsion technology and its potential application for the all electric commercial aircraft[J]. Progress in Aerospace Science, 2011, 47:369-391.
[8] MICHAEL D P, BRIAN J G. Wing aerodynamic analysis incorporating one-way interaction with distributed propellers[C]//14th AIAA Aviation Technology, Integration, and Operations Conference. Reston, VA:AIAA, 2014.
[9] MOOREL M, FREDERICKS B, BORER N. Drag reduction through distributed electric propulsion[C]//14th AIAA Aviation Technology, Integration, and Operations Conference. Reston, VA:AIAA, 2014.
[10] SRILATHA A. Design of a 4-seat, general aviation, electric aircraft[D]. San Jose:San Jose State University, 2012.
[11] 王科雷, 周洲, 祝小平, 等. 低雷诺数多螺旋桨/机翼耦合气动设计研究[J]. 航空学报, 2018, 39(10):121918. WANG K L, ZHOU Z, ZHU X P, et al. Research on multi-propeller/wing coupled aerodynamic design at low Reynolds numbers[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(10):121918(in Chinese).
[12] BORER N, PATTERSON M, VIKEN J, et al. Design and performance of the NASA SCEPTOR distributed electric propulsion flight demonstrator[C]//16th AIAA Aviation Technology, Integration, and Operations Conference. Reston, VA:AIAA, 2016:1-20.
[13] BORER N, DERLAGA J, DEERE K, et al. Comparison of aero-propulsion performance predictions for distributed propulsion configurations[C]//55th AIAA Aerospace Sciences Meeting. Reston, VA:AIAA, 2017:1-16.
[14] PATTERSON M, BORER N. Approach considerations in aircraft with high-lift propeller systems[C]//17th AIAA Aviation Technology, Integration, and Operations Conference. Reston, VA:AIAA, 2017:1-18.
[15] PATTERSON M, DERLAGA J, BORER N. High-lift propeller system configuration selection for NASA's SCEPTOR distributed electric propulsion flight demonstrator[C]//16th AIAA Aviation Technology, Integration, and Operations Conference. Reston, VA:AIAA, 2016:1-19.
[16] PATTERSON M, BORER N, GERMAN B. A simple method for high-lift propeller conceptual design[R]. Washington, D.C.:NASA Langley Research Center, 2016.
[17] PATTERSON M. Conceptual design of high-lift propeller systems for small electric aircraft[D]. Georgia:Georgia Institute of Technology, 2016.
[18] LARRABEE E. Practical design of minimum induced loss propeller:SAE Preprint 790585[R]. 1979.
[19] RAJAGOPALAN R, FANUCCI J. Finite-difference model for vertical axis wind rotors[J]. Journal of Propulsion and Power, 1985, 1(6):432-436.
[20] RAJAGOPALAN R, ZHANG Z. Performance and flow field of a ducted propeller[C]//AIAA/ASME/SAE/ASEE 25th Joint Propulsion Conference. Reston, VA:AIAA, 1989.
[21] RAJAGOPALAN R, LIM C. Laminar flow analysis of a rotor in hover[J]. Journal of the American Helicopter Society, 1985, 38(3):14-25.
[22] RAJAGOPALAN R, BERG D, KLIMAS P. Development of a three-dimensional model for the darrieus rotor and its wake[J]. Journal of Propulsion and Power, 1995, 11(2):185-195.
[23] MENTER F R. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal, 1994, 32(8):1598-1605.
[24] 陈广强, 白鹏, 詹慧玲, 等. 一种推进式螺旋桨无人机滑流效应影响研究[J]. 空气动力学学报, 2015, 33(4):554-562. CHEN G Q, BAI P, ZHAN H L, et al. Numerical simulation study on propeller slipstream effect on unmanned air vehicle with propeller engine[J]. Acta Aerodynamica Sinica, 2015, 33(4):554-562(in Chinese).
[25] TUNG W, JINGXUAN L, HSIANGCHUN K. Aerodynamic analysis of helicopter rotor blade in heavy rain condition[C]//51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, VA:AIAA, 2013.
[26] LIU Z, ALBERTAIN R, MOSCHETTA J M, et al. Experimental and computational evaluation of small microcoaxial rotor in hover[J]. Journal of Aircraft, 2011, 48(1):220-229.
[27] RITU M E, YUVRAJ D, CHONG Z, et al. Numerical design optimization of the S-76 rotor for hover performance[C]//2018 AIAA Aerospace Sciences Meeting. Reston, VA:AIAA, 2018.
[28] MCKEE J, NAESETH R. Experimental investigation of the drag of flat plates and cylinders in the slipstream of a hovering rotor:NACA-TN-4239[R]. Washington,D.C.:NASA, 1958.
[29] 刘丽娜, 吴国新. 基于Hicks-Henne型函数的翼型参数化设计以及收敛特性研究[J]. 科学技术与工程, 2014, 14(30):151-155. LIU L N, WU G X. Research on application of Hicks-Henne function in airfoil shape parameterization & convergence[J]. Science Technology and Engineering, 2014, 14(30):151-155(in Chinese).
[30] MUKESH R, LINGADURAI K, KARTHICK S. Aerodynamic optimization using proficient optimization algorithms[C]//2012 International Conference on Computing, Communication and Applications (ICCCA), 2012:1-5.
[31] 孙美建, 詹浩. Kriging模型在机翼气动外形优化中的应用[J]. 空气动力学学报, 2011, 29(6):759-764. SUN M J, ZHAN H. Application of Kriging surrogate model for aerodynamic shape optimization of wing[J]. Acta Aerodynamica Sinica, 2011, 29(6):759-764(in Chinese).
[32] SACKS J, WELCH W J, MICHELL T L, et al. Design and analysis of computer experiments[J]. Statistical Science, 1989, 4(4):409-435.
[33] 王琪, 杨晨俊. 基于涡格法的任意环量分布螺旋桨数值设计方法[J]. 中国造船, 2018, 59(2):90-102. WANG Q, YANG C J. A numerical design method for marine propellers with arbitrary distribution of circulation based on vortex lattice method[J]. Shipbuilding of China, 2018, 59(2):90-102(in Chinese).
[34] 范中允, 周洲, 祝小平. 一种可任意给定环量分布的螺旋桨设计方法[J]. 航空动力学报, 2019, 34(2):434-441. FAN Z Y, ZHOU Z, ZHU X P. A design method for propeller with arbitrary circulation distribution[J]. Journal of Aerospace Power, 2019, 34(2):434-441(in Chinese).

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