摘要
在小雷诺数条件下，采用N—S方程研究了-4°～10°迎角下不同厚度翼型对气动特性的影响规律，迭代计算结果表明：厚度较小的翼型在某一小攻角下获得最大的升阻比。并利用Solidworks软件，分析了三种不同厚度翼型叶片的应力分布，结果表明，三种翼型叶片均满足强度要求。
At the condition of low Reynolds number, the influence rules of the airfoil with different thickness at the attack angle of-4°～10° on aerodynamic characteris- tics are investigated using the N-S equations. The results show that the little thickness leads to the largeest lift-drag ratio at the condiiton of a small attack angle. The stress distributing of three Rinds of blades which composed different thickness airfoils is researched with SolidWorks. The result shows that all blades can meet the requirement of the intensity.
出处
《风机技术》
2012年第1期35-39,共5页
Chinese Journal of Turbomachinery
关键词
翼型厚度:升阻比:应力分布
叶片强度
气动特性
thickness of airfoils
lift-drag ratio
stress distributing
blade strength
aerodynamic characteristics
