三维机翼表面水滴撞击特性计算  

Calculation of Water-droplet Impingement on Wing Surface

作　　者：孙志国[1] 朱春玲[1] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016

出　　处：《计算物理》2011年第5期677-685,共9页Chinese Journal of Computational Physics

基　　金：国家自然科学基金(10972106)资助项目

摘　　要：系统研究机翼结冰计算中水滴轨迹和撞击特性的计算方法,将网格扇形分区和单元拓扑结构思想应用于水滴轨迹计算,引入欧拉法、预估-校正、四步Runge-Kutta法离散求解水滴运动方程.基于三维NACA 0012机翼模型,讨论水滴所在位置判断、速度插值和表面收集系数的计算方法,分析方程离散格式、水滴释放位置对计算结果的影响.采用三维机翼计算收集系数分布,并与试验结果进行对比,分析水滴直径对收集系数的影响;最后,将水滴计算模块DROP3D集成于结冰软件计算平台,计算不同工况参数下,机翼表面的气流流场和水滴撞击特性及结冰冰形,进一步验证程序的运行性能.We present systematic study on droplet trajectory calculation and impingement on wings. Fan-shaped partition and cell topology methods are applied to water droplet trajectory calculation. The droplet momentum equation is solved with fourth Runge-Kutta method. For a three-dimensional wing, position of droplet and velocity interpolation of collection efficiency on wing surface are discussed. Three discretization methods for control equation are used and compared. They are Euler method, predictor-corrector, and Runge-Kutta method. Impingement of droplet is analyzed and droplet collection efficiency on a NACA0012 wing is presented. Effects of droplet diameter on collection efficiency are considered. A particle trajectory module DROP3D is integrated to ice accretion software, which gives droplet impingements and ice accretion on wing surface in different icing conditions. Accuracy and reliability of the code is verified.

关 键 词：飞机结冰 水滴轨迹 收集系数 离散格式 网格分区 机翼 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]