摘要
利用附面层的速度型求解壁面的空气剪切应力,进而求得摩擦阻力,由此计算了一维层流平板边界层和二维层流NACA0012翼型的摩擦阻力.平板边界层计算结果同布拉修斯理论解相比较,吻合性良好.翼型计算结果同实验数据比较发现,小攻角气流不产生分离的情况下,摩擦阻力值与实验数据接近,随着迎角增大,分离区的扩展,压差阻力的比重增加,计算误差明显增加.
In order to obtain skin friction of the boundary layers, we adopt the air velocity model to solve the viscid stress. The skin frictions of two cases, 1-D laminar flat-plate boundary layer and 2-D laminar NA- CA0012 airfoil,are calculated by this method. The result of the flat-plate boundary layer matches Blasius solution quite well. Comparing the result of the airfoil calculation with the experimental data, we find that the calculation precision is acceptable at＇a relatively small angle of attack without airflow separation. As the angle of attack increases and the separation region expands and the proportion of pressure resistance in- creases, the calculation errors of this method will increase significantly.
出处
《成都大学学报（自然科学版）》
2014年第1期29-31,40,共4页
Journal of Chengdu University（Natural Science Edition）
关键词
摩擦阻力
附面层
数值计算
空气粘性
skin friction
boundary layer
numerical calculation
air viscosity
