Volume 36 Issue 1
Jan.  2021
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2021  >  36(1): 8-14
NI Zhangsong, LIU Senyun, ZHANG Jun, WANG Mao, WANG Zixu. Influnce of environment parameters on anti-icing heat load for aircraft[J]. Journal of Aerospace Power, 2021, 36(1): 8-14. doi: 10.13224/j.cnki.jasp.2021.01.002
Citation: NI Zhangsong, LIU Senyun, ZHANG Jun, WANG Mao, WANG Zixu. Influnce of environment parameters on anti-icing heat load for aircraft[J]. Journal of Aerospace Power, 2021, 36(1): 8-14. doi: 10.13224/j.cnki.jasp.2021.01.002
shu

Influnce of environment parameters on anti-icing heat load for aircraft

doi: 10.13224/j.cnki.jasp.2021.01.002
  • 1.

    School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China

  • 2.

    State Key Laboratory of Aerodynamics,China Aerodynamics Research and Development Center,Mianyang Sichuan 621050,China

  • 3.

    Key Laboratory of Icing and Anti/de-icing,China Aerodynamics Research and Development Center,Mianyang Sichuan 621050,China

  • Received Date: 2020-06-17
  • Publish Date: 2021-01-28
    Abstract
  • To accurately calculate the surface heat load for the design of the anti-icing system of an aircraft, the method for calculation of anti-icing heat load was studied and the calculation process was presented. And the influnce of the incoming flow speed, flight altitude, temperature, liquid water content and median volumetric diameter on the surface heat load distribution was studied. The results showed that: (1) the heat load was mainly located at the leading edge of the wing, and the closer to the tip of the wing, the larger the heat load value. The heat load curve had a trough in the middle and two shoulders at each side. (2) The non-zero range and the amplitude of the surface heat load were in proportion to the incoming flow speed and water median volumetric diameter. The variation of the flight altitude had trivial influence. As the incoming flow temperature decreased or liquid water content increased, the amplitude of the heat load increased, but the distribution range of the curve remained the same. The distribution range of the heat load on upper wing surface increased about 50% as the diameter of the water droplet increased 10 μm.

     

    • FullText(HTML)
  • loading
    • References(18)
  • [1]
    WILLIAM O,ROBERT S,JAMES N.Ice shapes and the resulting drag increase for a NACA 0012 airfoil［R］.NASA TM-14427,1984.
    [2]
    COLE J,SAND W.Statistical study of aircraft icing accidents［R］.AIAA-1991-0558,1991.
    [3]
    CORTINAS J V,BERNSTEIN B C,ROBBINS C C,et al.An analysis of freezing rain,freezing drizzle,and ice pellets across the United States and Canada:1976-1990［J］.Weather Forecasting,2004,19(2):377-390.
    [4]
    PLANQUART P,VANDEN B G.Aviation accident statistics:accidents,fatalities,and rates,1989-2008,for U.S.air carriers operating under 14 CFR 121［EB/OL］.［2020-05-20］.http:∥ntsb.gov∥aviation/Stats.htm.
    [5]
    MACKLIN W C.The density and structure of ice formed by accretion［J］.Quarterly Journal of the Royal Meteorological Society,1962,88(375):30-50.
    [6]
    ROBERT N,KREEGER R E.Analysis of a hovering rotor in icing conditions［R］.NASA/TM-2012-217126,2012.
    [7]
    PETERSON A,OLDENBURG J.Spray nozzle investigation for the improved helicopter icing spray system (IHISS)［R］.AIAA-1990-0666,1990.
    [8]
    PASTORBARSI C,ARRINGTON A.Aero-thermal calibration of the NASA Glenn icing research tunnel (2012 test)［R］.AIAA-2012-2934,2012.
    [9]
    陈维建,张大林.飞机机翼结冰过程的数值模拟［J］.航空动力学报,2005,20(6):1010-1017. CHEN Jianwei,ZHANG Dalin.Numerical simulation of ice accretion on airfoils［J］.Journal of Aerospace Power,2005,20(6):1010-1017.(in Chinese)
    [10]
    WU J,TANG L,LUKE E A,et al.A comprehensive numerical study of jet flow impingement over flat plates at varied angles［R］.AIAA-2001-0745,2001.
    [11]
    LIU T,HUA J.Three-dimensional integrated thermodynamic simulation for wing anti-icing sytem［J］.Journal of Aircraft,2004,41(6):1291-1297.
    [12]
    PLANQUART P,VANDEN B G,BUCHLIN J M.Experimental and numerical optimization of a wing leading edge hot air anti-icing system［R］.AIAA-2005-1277,2005.
    [13]
    常士楠,候雅琴,袁修干.周期电加热控制律对除冰表面温度的影响［J］.航空动力学报,2007,22(8):1247-1251. CHANG Shinan,HOU Yaqin,YUAN Xiugan.Influence of periodic electro heating pulse on deicing surface temperature［J］.Journal of Aerospace Power,2007,22(8):1247-1251.(in Chinese)
    [14]
    COLIN S,MARK G.User’s manual for the NASA Lewis three-dimensional ice accretion code (LEWICE3D)［R］.NASA Technical Memorandum 105974,1993.
    [15]
    AL-KHALIL M H.Validation of NASA thermal ice protection computer codes:Part 3 validation of ANTICE［R］.AIAA-1997-0051,1997.
    [16]
    SILVA G A L,SILVARES O M,ZERBINI E J.Airfoil anti-ice system modeling and simulation［R］.AIAA-2003-734,2003.
    [17]
    孙志国.飞机结冰数值计算与冰风洞部件设计研究［D］.南京:南京航空航天大学,2012. SUN Zhiguo.Research on numerical simulation of ice accretion and desing for icing research tunnel parts［D］.Nanjing:Nanjing University of Aeronautics and Astronautics,2012.(in Chinese)
    [18]
    刘森云,朱程香,朱春玲,等.水滴动力学行为对其撞击特性的影响［J］.航空动力学报,2018,33(3):581-589. LIU Senyun,ZHU Chengxiang,ZHU Chunling,et al.Effect of dynamic behavior on its impingement characteristics for droplets［J］.Journal of Aerospace Power,2018,33(3):581-589.(in Chinese)
    • 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(2932.0KB)
    XML

    Article Metrics

    Article views (460) PDF downloads(277) 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