翼型结冰过程数值模拟验算与分析  

Numerical Simulation Check and Analysis of Ice Accretion on Airfoil

作　　者：孔满昭[1] 蒲宏斌[1] 

机构地区：[1]中国航空工业集团公司第一飞机设计研究院,西安710089

出　　处：《航空工程进展》2011年第3期267-272,共6页Advances in Aeronautical Science and Engineering

摘　　要：应用FENSAP-ICE结冰计算软件,对NACA0012翼型进行了流动特性、水滴撞击特性以及冰型生成过程的计算;同时,对结冰前后的翼型进行气动力特性计算对比分析,其中包括升力特性对比、阻力特性对比、流场细节分析以及压力系数分布对比。计算结果表明:翼型前缘结冰后,导致翼型前缘气流提前分离,最大升力系数、失速攻角大幅减小,阻力系数明显增加;冰型计算结果与文献中的实验冰型结果符合良好,满足工程应用要求。The ice accretion code FENSAP-ICE is used to simulate flow characteristic,water impingement and ice generation of NACA0012 airfoil.Besides,the aerodynamic characteristics of the airfoil before and after icing are compared,such as lift characteristic,drag characteristic,flow field detail analyses and pressure coefficient.The calculation results indicate that icing of airfoil leading edge resulted in the flow separation in airfoil leading edge in advance,moreover,maximum lift coefficient and stall angle reduced dramatically as well as drag coefficient increased obviously.The calculated ice shapes agree well with the experimental results,which referred by literatures and the predicted results are satisfied with engineering applications.

关 键 词：翼型 水滴撞击 结冰模拟 气动力特性 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]