摘要
论文通过数值模拟方法对NACA6412层流翼型的低速绕流特性进行了研究,采用修正的BaldwinLomax湍流模型对来流速度为25m/s、8°迎角时翼型的流场、背风区的速度型分布、不同弦向位置附面层厚度的变化规律以及转捩位置进行了模拟,数值模拟结果与风洞实验结果具有一定的相关性.
Through numerical simulation method the low speed flow field around NACA6412 laminar airfoil has been studied.The modified Baldwin-Lomax turbulence model is applied.For a 25 m/s inflow under the attack angle of 8°,flow field structure and velocity profile at the leeward area,boundary layer thickness at different chord positions and the transition position has been obtained.The numerical simulation results and wind tunnel experiment results have a good correlation.
出处
《固体力学学报》
CSCD
北大核心
2014年第S1期85-90,共6页
Chinese Journal of Solid Mechanics
关键词
层流翼型
附面层
数值模拟
风洞实验
laminar airfoil,boundary layer,numerical simulation,wind tunel experiment
