关键词: 计算流体力学, 非定常, 扰流片, 重叠网格

Abstract: Transient aerodynamic response of an airfoil to a rapidly deploying spoiler is numerically investigated by solving two-dimensional unsteady compressible Navier-Stokes equations. The spoiler moving relative to a stationary airfoil is treated by a dynamic overset grid method. The mechanism of the adverse lift caused by the rapidly deploying spoiler is analyzed. Also, the effects of angle of attack, height of spoiler and rapidly deploying rate on the adverse lift are investigated.

Key words: CFD, unsteady, spoiler, overset grid