Volume 34 Issue 11
Nov.  2019
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Article Navigation >  Journal of Aerospace Power  > 2019  >  34(11): 2377-2386
LIU Jiaqi, CHEN Rongqian, CHENG Jiaming. Numerical simulation of flow field under coaxial rigid rotor/fuselage interaction[J]. Journal of Aerospace Power, 2019, 34(11): 2377-2386. doi: 10.13224/j.cnki.jasp.2019.11.009
Citation: LIU Jiaqi, CHEN Rongqian, CHENG Jiaming. Numerical simulation of flow field under coaxial rigid rotor/fuselage interaction[J]. Journal of Aerospace Power, 2019, 34(11): 2377-2386. doi: 10.13224/j.cnki.jasp.2019.11.009
shu

Numerical simulation of flow field under coaxial rigid rotor/fuselage interaction

doi: 10.13224/j.cnki.jasp.2019.11.009

  • School of Aerospace Engineering,Xiamen University,Xiamen Fujian 361102,China

  • Received Date: 2019-06-03
  • Publish Date: 2019-11-28
    Abstract
  • The method of solving the Navier-Stokes (RANS) equation by the sliding mesh technique was studied, and the interaction problem of the coaxial rigid rotor/fuselage was analyzed. The correctness of the numerical simulation of the flow field related to rotor was verified by the examples of Caradonna-Tung rotor, Robin helicopter, Maryland helicopter rotor/fuselage interaction, and Harrington 2 coaxial rotors. On this basis, with the Maryland fuselage as the model prototype, the interference characteristics between the coaxial rigid rotor with different pitches and the fuselage were analyzed. Results showed that numerical simulation method can simulate the aerodynamic interference characteristics of the coaxial rigid rotor/fuselage very well; the hovering efficiency of the rotor increased by about 5% due to the blockage of the airflow field of the coaxial rigid rotor., and the increase of the hovering efficiency was more obvious with the increase of the pulling coefficient; the increase of the hovering efficiency of the rotor was mainly related to the increase of the blade lift coefficient near the 0° azimuth of the lower rotor, and the increment of the tensile coefficient was gradually reduced from the root of the blade to the tip of the blade.

     

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    • References(25)
  • [1]
    BAGAI A.Aerodynamic design of the X2TM technology demonstrator main rotor blade［C］∥Proceeding of American Helicopter Society 64th Annual Forum.Montreal,Canada:American Helicopter Society(AHS),2008:211-242.
    [2]
    CAMERON C,KARPATNE A,SIROHI .Performance and vibratory hub loads of a mach-scale coaxial rotor in hover［C］∥Proceedings of American Helicopter Society 70th Annual Forum.Montreal,Canada:American Helicopter Society(AHS),2014:1-9.
    [3]
    CAMERON C,SIROHI J.Performance and loads of a model coaxial rotor:Part Ⅰ wind tunnel testing［C］∥Proceedings of American Helicopter Society 72nd Annual Forum.West Palm Beach,FL:American Helicopter Society(AHS),2016:1-15.
    [4]
    FEIL R,RAULEDER J.Aeromechanics analysis of a coaxial rotor system in hover and high-advance-ratio forward flight［C］∥Proceedings of the AIAA Applied Aerodynamics onference.Washington:AIAA,2016:1-19.
    [5]
    WALSH D,WEINER S,ARIFIAN K,et al.High airspeed testing of the Sikorsky X2 TechnologyTM demonstrator［R］.Virginia Beach,VA:the 67th American Helicopter Society(AHS) Annual Forum,2011.
    [6]
    SUZAN D,WILLIAM E,EREZ E.S-97TM adaptive survivability［R］.Phoenix,AZ:the American Helicopter Society 69th Annual Forum,2013.
    [7]
    邓彦敏,陶然,胡继忠.共轴式直升机上下旋翼之间气动干扰的风洞实验研究［J］.航空学报,2003,24(1):10-14.DENG Yanmin,TAO Ran,HU Jizhong.Experimental investigation of the aerodynamic interaction between upper and lower rotors of a coaxial helicopter［J］.Acta Aeronautica et Astronautica Sinica,2003,24(1):10-14.(in Chinese)
    [8]
    唐正飞,李锋,高正,等.用三维激光多谱勒测速仪对共轴双旋翼悬停流场的测定［J］.流体力学实与测量,1998,12(1):81-87.TANG Zhengfei,LI Feng,GAO Zheng.Measurement of the coaxial-rotor flow field in hovering using 3-D laser doppler velocimeter.［J］.Experiments and Measurements in Fluid Mechanics,1998,12(1):81-87.(in Chinese)
    [9]
    COLEMAN C P.A survey of theoretical and experimental coaxial rotor aerodynamic research［R］.NASA-3675,1997.
    [10]
    HARRINGTON R D.Full-scale-tunnel investigation of the static-thrust performance of a coaxial helicopter rotor［R］.NACA TN-2318,1951.
    [11]
    LEISHMAN J G,ANANTHAN S.An optimum coaxial rotor system for axial flight［J］.Journal of the American Helicopter Society,2008,53(4):366-381.
    [12]
    童自力,孙茂.共轴式双旋翼流动的N-S方程模拟［J］.航空学报,1998,19(1):1-5.TONGZili,SUN Mao.Navier-Stokes calculations of coaxial rotor aerodynamics［J］.Acta Aeronautica et Astronautica Sinica,1998,19(1):1-5.(in Chinese)
    [13]
    许和勇,叶正寅.悬停共轴双旋翼干扰流动数值模拟［J］.航空动力学报,2011,26(2):453-457.XU Heyong,YE Zhengyin.Numerical simulation of interaction unsteady flows around coaxial rotors in hover［J］.Journal of Aerospace Power,2011,26(2):453-457.(in Chinese)
    [14]
    叶靓,徐国华.共轴式双旋翼悬停流场和气动力的CFD计算［J］.空气动力学学报,2012,30(4):437-442.YE Liang,XU Guohua.Calculation on flow field and aerodynamic force of coaxial rotors in hover with CFD method［J］.Acta Aerodynamica Sinica,2012,30(4):437-442.(in Chinese)
    [15]
    招启军,朱正,原昕.桨叶外形对共轴刚性旋翼悬停性能影响的CFD分析［J］.南京航空航天大学学报,2017,49(5):653-661.ZHAO Qijun,ZHU Zheng,YUAN Xin.CFDanalyses on effects of blade shape on hover performance of coaxial rigid rotors［J］.Journal of Nanjing University of Aeronautics and Astronautics,2017,49(5):653-661.(in Chinese)
    [16]
    陈龙.基于CFD/CSD耦合的旋翼气动弹性数值模拟［D］.南京:南京航空航天大学,2011.CHENG Long.Numerical simulation of rotor aeroelastic using CFD/CSD coupling［D］.Nanjing:Nanjing University of Aeronautics and Astronautics,2011.(in Chinese)
    [17]
    余智豪.基于CFD/CSD耦合的共轴刚性双旋翼振动载荷分析［D］.南京:南京航空航天大学,2018.YU Zhihao.Computational analysis on vibration loads of coaxial rigid rotors based on CFD/CSD coupling［D］.Nanjing:Nanjing University of Aeronautics and Astronautics,2018.(in Chinese)
    [18]
    程载恒,陈荣亮,孙哲.基于非结构滑移网格技术的旋翼型无人机空气动力学并行数值模拟方法［J］.集成技术,2017,6(3):83-90.CHENG Zaiheng,CHEN Rongliang,SUN Zhe.A parallel numerical simulation method for the aerodynamics of rotor unmanned aerial vehicles based on unstructured sliding meshes［J］.Journal of Integration Technology,2017,6(3):83-90.(in Chinese)
    [19]
    黄超.复合式直升机旋翼气动建模与计算［R］.北京:北京力学会第23届学术年会,2017:15-16.
    [20]
    BLAZEK J.Computational fluid dynamics:principles and applications［M］.Oxford:Elsevier Science Limited,2001.
    [21]
    CARADONNA F X,TUNG C.Experimental and analytical studies of a model helicopter rotor in hover［J］.Vertica,1980,5(2):149-161.
    [22]
    RAYMOND E M,SUSAN A G.Steady and periodic pressure measurements on a generic helicopter fuselage model in thepresence of a rotor［R］.NASA-TM-2000-201286,2000.
    [23]
    PHELPS A E Ⅲ,BERRY J D.Description of the U.S. Army small-scale 2-meters rotor test system［R］.NASA TM 87762,1987.
    [24]
    BI N P,LEISHMAN G.Experimental study of rotor/body aerodynamic interactions［J］.Journal of Aircraft,1990,27(9):779-788.
    [25]
    HARRINGTON R D.Full-scale-tunnel investigation of static-thrust performance of a coaxial helicopter rotor［R］.NACA TN-2318,1951.
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