Analysis on supercooled large droplet impingement characteristics and ice shape of two-dimensional airfoils
-
摘要: 基于现有大尺寸过冷水滴(supercooled large droplet, SLD)动力学特性,分析水滴变形对阻力的影响.并根据几种典型的反弹/飞溅模型,分析了SLD的阻力变化、反弹、飞溅等对水滴撞击特性的影响,采用软件FENSAP-ICE的飞溅模型和LEWICE 2.0的反弹模型研究了反弹及飞溅现象对冰形的影响.计算结果显示:水滴撞击前的破碎现象对水滴尺寸分布有较大的影响,进行撞击特性以及冰形计算的时候需进行考虑;SLD破碎、飞溅、反弹降低了局部水收集系数、减小了水滴撞击范围;飞溅现象主要发生在机翼前缘附近区域,反弹主要在撞击边缘区域;水滴直径增加,飞溅现象逐渐减弱,但边缘位置的反弹现象一直很明显.SLD变形带来的阻力影响对冰形及结冰区域影响很小;与未考虑飞溅及反弹现象得到的冰形比较,考虑飞溅及反弹得到冰形前缘区域形状变化不大,但是整体结冰区域减小.Abstract: Based on existing supercooled large droplet (SLD) dynamic characteristics, the effects of droplet deformation on drag were analyzed, and the effects of drag change, rebounding and splashing of SLD on droplet impingement characteristics were analyzed by several typical rebounding/splashing models. The splashing model from software of FENSAP-ICE and rebounding model from software of LEWICE 2.0 were used to study the influence of rebounding and splashing to ice shape. The results show that the droplet diameter distribution is influenced greatly by the breaking up before droplet impingement, which should be considered in calculation of impingement characteristics and ice shape; breaking up, splashing and rebounding of SLD results in the decrease of local water collection coefficient and droplet impingement region; the splashing occurs mainly near the leading edge of airfoils and rebounding occur near the edge of the impingement region; with the droplet size increasing, splashing becomes weak, while rebounding is still obvious; the effect of drag change induced by SLD deformation on ice shape and ice accretion region is negligible; compared with the ice shape without considering splashing and rebounding, the ice shape considering splashing and rebounding is approximately the same at the leading edge, while the whole ice accretion region is smaller.
-
Key words:
- supercooled large droplet /
- empirical models /
- breaking up /
- splashing /
- rebounding /
- impingement characteristics /
- ice accretion
-
[1] 裘燮纲,韩凤华.飞机防冰系统[M].北京:航空专业教材编审组,1985. [2] Miller D,Ratvasky T,Bernstein B,et al.NASA/FAA/NCAR supercooled large droplet icing flight research:summary of winter 96-97 flight operations .AIAA 98-577,1998. [3] 罗辉.SLD环境下的水滴破裂和模拟成冰 .上海:上海交通大学,2011. LUO Hui.Droplets breakup under the SLD environment and its icing simulation .Shanghai:Shanghai Jiaotong University,2011.(in Chinese) [4] 闵现花.结冰条件下过冷水滴撞击特性及热平衡分析 .上海:上海交通大学,2010. MIN Xianhua.Supercooled water droplet impingement property and thermal balance analysis under the condition of icing .Shanghai: Shanghai Jiaotong University,2010. (in Chinese) [5] Wright W B,Potapczuk M G.Semi-empirical modeling of SLD physics .AIAA 2004-0412,2004. [6] Iuliano E,Mingione G,Petrosino F.Eulerian modeling of SLD physics towards more realistic aircraft icing simulation .AIAA 2010-7676,2010. [7] Wright W B.Validation results for LEWICE 3.0 .AIAA 2005-1234,2005. [8] 杨胜华.二维飞机结冰过程仿真 .北京:北京航空航天大学,2010. YANG Shenghua.Two-dimensional in-flight ice accretion simulation .Beijing:Beijing University of Aeronautics and Astronautics,2010.(in Chinese) [9] Fluent Inc.Fluent 6.3 users guide[M].NewYork:Fluent Inc,2006. [10] Clift R,Grace J R,Weber M E.Bubbles,drops and particles[M].New York:Academic Press,1978. [11] Hsiang L P,Faeth G M.Second drop breakup in the deformation regime .AIAA 92-0110,1992. [12] Honsek R,Habashi W G.Fensap-ice:Eulerian modeling of droplet impingement in SLD regime of aircraft icing .AIAA-2006-465,2006. [13] Villedieu P,Trontin P,Guffond D.SLD Lagrangian modeling and capability assessment in the frame of ONERA 3D icing suite .AIAA-2012-3132,2012. [14] Newtech Infosystems.FENSAP-ICE manual[M].Toronto,Canada:Newtech Infosystems,2011. [15] Hospers J M,Harry W M.Eulerian method for ice accretion on multiple-element airfoil sections .AIAA-2010-1236,2010. [16] Papadakis M,Wong S C.Large and small droplet impingement data on airfoil and two simulated ice shapes .NASA/TM-2007-213959,2007.
点击查看大图
计量
- 文章访问数: 1527
- HTML浏览量: 2
- PDF量: 1001
- 被引次数: 0