二维机翼防冰表面溢流水膜破裂数值模拟  

Numerical simulation of runback film breakup on two-dimensional anti-icing airfoil surface

作　　者：卜雪琴[1] 马文涛[1] 林贵平[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《航空动力学报》2015年第2期368-375,共8页Journal of Aerospace Power

基　　金：国家自然科学基金(51206008);航空科学基金(2012ZBN2016)

摘　　要：为了准确地预测机翼防冰系统热载荷,对二维机翼防冰表面溢流水流动状态进行了仿真计算.依据剪切力驱动模型,分别推导了水膜破裂前后的速度分布;引入能量最低原理,推导了溪状流模型,运用数值方法对水膜破裂的临界厚度进行了求解;使用基于Fluent软件的用户自定义函数方法编程并加载计算模块,分别以水膜模型和溪状流模型计算得到了溢流水的流动特性.结果表明:在一定结冰条件下,引入溪状流模型后,溢流水的溢流范围在两个不同算例中分别增大了33%和17%,这会很大程度影响防冰系统热载荷的分布.In order to accurately estimate the heat-load of the anti-icing system of airfoil,the numerical simulation of runback flow state on the two-dimensional anti-icing airfoil surface was presented.Based on shear-driven model,the velocity distributions before and after film breakup were derived respectively.By introducing the minimum energy criteria,the rivulet model was established,and the critical thickness of film breakup was solved by numerical method.By using the user defined function method in Fluent software to program and load the calculation procedures,the flow characteristics of runback flow were obtained based on film model and rivulet model respectively.The results indicate that,under a certain icing condition,the ranges of the runback flow increase by 33% and 17%in two different examples respectively due to the rivulet model,thus largely affecting the distribution of the heatload of the anti-icing system.

关 键 词：水膜破裂 溪状流 临界厚度 防冰 二维 

分 类 号：V244.15[航空宇航科学与技术—飞行器设计]