本文考虑无粘、不可压缩流中平板薄翼在大迎角下气流沿边缘分离出现脱体涡时的非定常气动载荷数值计算。采用离散涡格法,从某一初始备件开始,计算一系列时刻机翼的非线性气动载荷以及脱体涡的几何形状,从而了解脱体涡的形成过程。当保持边界条件不随时间改变,则随着计算时刻的增加,结果趋近于稳态解。算例计有矩形翼、箭形翼。 In this paper, we consider the unsteady aerodynamic loads of non-viscous and incompressible thin-walled slab at the high angle-of-attack separation along the edge. Discrete vortex method is used to calculate the non-linear aerodynamic loads of the wing and the geometric shape of the extant vortex from a certain initial spare part so as to understand the formation process of the detached vortex. When the boundary conditions are kept unchanged with time, the result approaches the steady-state solution as the calculation time increases. Examples include rectangular wings, arrow-shaped wings.