摘要
本文用FLUENT软件模拟了结冰后NACA0012翼型周围流场的变化，并与结冰前NACA0012翼型的气动性能进行了对比。工作中首先以未结冰的NACA0012翼型（干净翼型）为标准模型进行了数值验证计算，再以经过检验的方法计算结冰模型，并与结冰风洞试验数据进行了对比。本文计算攻角为0°～20°，温度为250．37K，雷诺数为2，400，000，冰型为圆形坚冰。通过对比升力阻力性能，发现与干净翼型相比，结冰翼型的最大升力系数大约减少了50％，阻力系数增加了约65％，失速攻角降低了4°。结冰后翼型提前失速是造成气动性能恶化的主要原因。
The flow field around NACA 0012 airfoil with software Fluent was simulated, to compare the correspondent aerodynamic performance variation before and after icing. The clear NACA 0012 was used airfoil as a standard model to validate the numerical model that will be used in the following simulation. The parameters used in the numerical simulations were adopted from the wind tunnel tests, and the results were compared and analyzed. The parameters used herein is： AOA = 0°～20° , T = 250.37K, Re = 2, 400,000. The ice profile is round ice which is adopted from the wind tunnel tests. Results indicate that the ice accretion leads to the loss of maximum lift coefficient by about 50%, the decrease of stall angle by about 4° and the drag coefficient increase by nearly 65%. Stall is the main reason for all these aerodynamic performances worsen.
出处
《力学季刊》
CSCD
北大核心
2007年第1期28-33,共6页
Chinese Quarterly of Mechanics
