三维高升力机翼水滴撞击特性数值模拟研究  

Numerical simulation study of droplet impingement characteristics on 3-D highlift wing

作　　者：么虹[1] 王强[1] YAO Hong WANG Qiang(Aviation Key Laboratory of Aerodynamics for High Speed and High Reynolds Number, AVIC Aerodynamics Research Institute, Shenyang 110034, China)

机构地区：[1]中国航空工业空气动力研究院高速高雷诺数气动力航空科技重点实验室,辽宁沈阳110034

出　　处：《大连理工大学学报》2017年第1期11-15,共5页Journal of Dalian University of Technology

基　　金：中航工业集团公司创新基金资助项目(2013A62601R)

摘　　要：基于分区多块结构网格体系,采用欧拉方法建立过冷水滴控制方程,通过有限体积方法对方程进行求解,发展了适合三维复杂外形飞机的水滴撞击特性计算方法和计算程序.通过二维单段翼型、多段翼型等算例对该方法的验证计算表明,在常规尺寸水滴算例中,水滴撞击特性计算结果与国外标准模型试验数据吻合良好.在此基础上,开展了三维高升力机翼水滴撞击特性数值模拟研究,分析表明计算结果可用于飞机防/除冰系统设计.Based on the partition multiblock structured grid system,the control equation of supercooled droplet is established by the Eulerian method.A finite volume method is used to solve the equation.A droplet impingement characteristics calculation method and the simulating program for 3-D complex configuration of airplane are developed.Some cases including 2-D airfoil,multi-element airfoil are used to validate the method.It is shown that,to the normal dimensional droplet,the computational results are in good agreement with the experimental data from abroad standard model.Then,the droplet impingement characteristics on a 3-D highlift wing are numerically simulated.Analyses show that the computational results can be used to design anti/deicing system of airplane.

关 键 词：欧拉方法 水滴撞击特性 高升力机翼 飞机结冰 

分 类 号：V215.21[航空宇航科学与技术—航空宇航推进理论与工程]