模拟飞机迎风面三维积冰的数学模型

曹广州; 吉洪湖; 胡娅萍; 庞黎刚; 斯仁; 冯晓星

模拟飞机迎风面三维积冰的数学模型

南京航空航天大学能源与动力学院,南京 210016

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出版历程
- 收稿日期: 2010-10-21
- 修回日期: 2011-02-19
- 刊出日期: 2011-09-28

An icing model for simulating three dimensional ice accretion on the upwind surfaces of a plane

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 针对飞机迎风面的积冰建立了三维积冰模型,给出了模型的求解方法和求解步骤.该模型不但可以模拟明冰积冰、霜冰积冰和不结冰三种情况下的冰层生长,还可以模拟未凝结水膜在冰层表面的流动,而且在求解过程中可以自动判断过冷水滴撞击到迎风面以后的积冰形态.利用该模型数值模拟了翼型与平板相正交而形成的简单三维结构上的积冰过程,并将所得结果中翼型上三维冰形的二维截面与美国航空航天局(NASA)的冰形进行了对比,获得了较好的一致性,证实了所建立的积冰模型是合理的.
- 三维积冰 /
- 积冰模型 /
- 明冰 /
- 霜冰 /
- 薄水膜流动
Abstract: A three-dimensional (3-D) icing model was built for the ice accretion on the upwind surfaces of the plane.The methods and steps for solving the model were also presented.The model can simulate both the ice accretion in the glaze ice,rime ice and no ice conditions and the water film flow on the ice surface.The model can also estimate which kind of ice accretion occurs when the super-cooled water droplets impinge on the surfaces.The 3-D ice accretion on airfoil-plane intersecting wall was simulated with the model.The two-dimensional (2-D) section of the 3-D ice on the airfoil was compared with National Aeronautics and Space Administration's (NASA's) ice shape.Good agreement proves the icing model is logical.
- three-dimensional (3-D) ice accretion /
- icing model /
- glaze ice /
- rime ice /
- shallow water film flow

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参考文献(14)

[1]	袁燮纲,韩凤华.飞机防冰系统[M].北京:航空专业教材编审组,1996.
[2]	Ruff G A,Berkowitz B M.User’s manual for the NASA Lewis ice accretion prediction code(LEWICE) .NASA CR-185129,1990.
[3]	Messinger B L.Equilibrium temperature of an unheated icing surface as a function of airspeed[J].Journal of Aeronautical Science,1953,20(1):29-42.
[4]	Hedde T,Guffond D.Development of a three-dimensional icing code,comparison with experimental shapes .AIAA-1992-0041,1992.
[5]	Potapczuk M G,Bidwell C S.Numerical simulation of ice growth on a MS-317 swept wing geometry .AIAA-1991-0263,1991.
[6]	Hedde T,Guffond D.Improvement of the ONERA 3D icing code,comparison with experimental shapes .AIAA-1993-0169,1993.
[7]	Bourgault Y,Beaugendre H,Habashi W G.Development of a shallow-water icing model in FENSAP-ICE .AIAA-1999-0246,1999.
[8]	Myers T G,Charpin J P,Thompson C P.Slowly accreting ice due to supercooled water impacting on a cold surface[J].Physics of Fluids,2002,14(1):240-256.
[9]	Da Silveira R A,Maliska C R,Estivam D A,et al.Evaluation of collection efficiency methods for icing analysis .Sao Paulo:Proceedings of 17th Intemational Congress of Mechanical Engineering,2003.
[10]	Wirogo S,Srirambhatla S.An Eulerian method to calculate the collection efficiency on two and three dimensional bodies .AIAA-2003-1073,2003.
[11]	卜雪琴,林贵平.基于CFD的水收集系数及防冰表面温度预测[J].北京航空航天大学学报,2007,33(10):3810-3813. BU Xueqin,LIN Guiping.Predictions of collection efficiency and anti-icing surface temperature[J].Journal of Beijing University of Aeronautics and Astronautics,2007,33(10):3810-3813.(in Chinese)
[12]	Matheis B D,Rothmayer A P.Numerical simulations of thin air driven films .AIAA-2002-0525,2002.
[13]	王福军.计算流体动力学分析[M].北京:清华大学出版社, 2006.
[14]	Moriarty J A,Schwartz L W,Tuck E O.Unsteady spreading of thin liquid films with small tension[J].Physics of Fluids,1991,3(5):733-742.