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.
出处
《航空工程进展》
2011年第3期267-272,共6页
Advances in Aeronautical Science and Engineering
关键词
翼型
水滴撞击
结冰模拟
气动力特性
airfoil
water impingement
ice accretion simulation
aerodynamic characteristics
