Volume 33 Issue 1
Jan.  2018
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2018  >  33(1): 116-123
Aerodynamic performance and flow interaction of the coaxial rigid rotor in hover[J]. Journal of Aerospace Power, 2018, 33(1): 116-123. doi: 10.13224/j.cnki.jasp.2018.01.014
Citation: Aerodynamic performance and flow interaction of the coaxial rigid rotor in hover[J]. Journal of Aerospace Power, 2018, 33(1): 116-123. doi: 10.13224/j.cnki.jasp.2018.01.014
shu

Aerodynamic performance and flow interaction of the coaxial rigid rotor in hover

doi: 10.13224/j.cnki.jasp.2018.01.014
  • Received Date: 2016-06-12
  • Publish Date: 2018-01-28
    Abstract
  • A numerical method based on RANS(Reynoldsaveraged NavierStokes) equations was developed to predict the aerodynamic performance of coaxial rigid rotor in hover. Validation of the method was carried out on the hovering tests for the subsonic and transonic flows. The simulation of rigid rotor XH59A in hover showed that CFD prediction of rotor performance agreeed with the flight test data. Compared with single rotor of the same solidity, coaxial rigid rotor had better performance, along with bigger figure of merit. The performance of the upper rotor decreased less than that of the lower rotor. Reasons were related to the suction effect of the lower rotor on the flow and its location in the downwash flow field of the upper rotor, resulting in the decrease of its effect angle attack. Numerical method indicated that the optimum figure of merit for XH59A was 67%, when the collective pitch angle for both rotors was 14°. Compared with traditional coaxial rotor, the interstage distance of rigid rotor was smaller, leading to a better aerodynamic performance.

     

    • FullText(HTML)
  • loading
    • References(18)
  • [1]
    刘成,朱清华,李建波.刚性旋翼复合式直升机技术特点分析［C］∥第26届全国直升机年会论文.江西 景德镇:中国航空学会,2010:13-18.
    [2]
    LAKSHMINARAYAN V K,BAEDER J D.Highresolution computational investigation of trimmed coaxial rotor aerodynamics in hover［J］.Journal of the American Helicopter Society,2009,54(4):42008.1-42008.21.
    [3]
    LAKSHMINARAYAN V K,BAEDER J D.Computational investigation of microscale coaxial rotor aerodynamics in hover［J］.Journal of Aircraft,2010,47(3):940-955.
    [4]
    LAKSHMINARAYAN V K,BADER J D.Computational investigation of small scale coaxial rotor aerodynamics in hover［R］.AIAA2009-1069,2009.
    [5]
    XU Heyong,YE Zhengyin.Coaxial rotor helicopter in hover based on unstructured dynamic overset grids［J］.Journal of Aircraft,2010,47(5):1820-1824.
    [6]
    XU Heyong,YE Zhengyin.Numerical simulation of unsteady flow around forward flight helicopter with coaxial rotors［J］.Chinese Journal of Aeronautics,2011,24(1):1-7.
    [7]
    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)
    [8]
    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 Aerodynamic Sinica,2012,30(4):437-442.(in Chinese)
    [9]
    朱正,招启军,李鹏.悬停状态共轴刚性双旋翼非定常流动干扰机理研究［J］.航空学报,2016,37(2):568-578.ZHU Zheng,ZHAO Qijun,LI Peng.Investigations on unsteady flow interaction mechanism of coaxial rigid rotors in hover［J］.Acta Aeronautica et Astronautica Sinica,2016,37(2):568-578.(in Chinese)
    [10]
    苏大成,史勇杰,黄水林，等.共轴刚性旋翼气动干扰特性研究［J］.航空科学技术,2015,26(11):10-18.SU Dacheng,SHI Yongjie,HUANG Shuilin,et al.Research on aerodynamic interaction effect of rigid coaxial rotor［J］.Aeronautical Science and Technology,2015,26(11):10-18.(in Chinese)
    [11]
    COLEMAN C P.A survey of theoretical and experimental coaxial rotor aerodynamic research［R］.NASA TP-3675,1997.
    [12]
    NAGASHIMA T,OUCHI,H,SASAKI F.Optimum performance and load sharing of coaxial rotor in hover［J］.Journal of Japan Society for Aeronautics and Space Sciences,1978,26(293):325-333.(in Japanese)
    [13]
    HARRINGTON R D.Fullscaletunnel investigation of the staticthrust performance of a coaxial helicopter rotor［R］.NACA TN-2318,1951.
    [14]
    唐正飞,高正.共轴双旋翼与单旋翼悬停流场实验测量值的对比［J］.南京航空航天大学学报,1997,29(6):627-632.TANG Zhengfei,GAO Zheng.Comparison of experimental data for the coaxial rotor and single rotor flowfield in hovering［J］.Journal of Nanjing University of Aeronautics and Astronautics,1997,29(6):627-632.(in Chinese)
    [15]
    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)
    [16]
    CARADONNA F X,TUNG C.Experimental and analytical studies of a model helicopter rotor in hover［R］.NASATM-81232,1981.
    [17]
    FELKERF F.Performance and loads data from a wind tunnel test of a fullscale coaxial hingeless rotor helicopter［R］.NASATM-81329,1981.
    [18]
    JOHNSON W.Liftoffset compound design background,X2TD,JMR ME1A［R］.Moffect Field,CA,US:NASA AMES Research Center,2011.
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF(927.0KB)
    XML

    Article Metrics

    Article views (1227) PDF downloads(555) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return