摘要
本文研究二维厚度翼型的大攻角非定常运动。用沿翼型表面分布的源和面涡来模拟翼型的厚度效应和升力效应,应用离散涡方法模拟前缘分离涡层和尾涡层。计算了大攻角翼型作俯仰运动的情形,与实验结果符合较好。
The unsteady motion of a two-dimensional thick airfoil at high angles of attack is considered in this paper. The source and vorticity distributed on the airfoil surface are used to model the thick and lift effects. Discrete vortex method is used to model the wake sheet and the leading-edge separated vortex sheet. The pitching oscillation motion of the airfoil at high angle of attack is computed. The computation results are reasonable, comparing with experiments.
出处
《空气动力学学报》
CSCD
北大核心
1990年第1期94-97,共4页
Acta Aerodynamica Sinica
关键词
翼型
非定常流
大攻角
涡方法
模拟
airfoil, unsteady motion, high angles of attack, vortex method.
