Spoilers play a vital role in the flight control systems of modern transport aircraft. Because of their efficiency and fast deflection rates, they are widely used to assist in roll control or for gust load alleviation purposes. Simulating the aerodynamic behavior of spoilers still is a challenging task, as deflecting a spoiler always induces flow separation. The work presented in this paper therefore focused on extending the application range of DLR, German Aerospace Center’s in-house flow solver TAU by verifying and validating it for spoiler applications. In a first step, the work focused on steady and unsteady simulations of static and dynamic spoiler deflections in the low-speed regime. It was shown that the chosen numerical approach is well suited to reproduce the surface pressure distribution for static spoiler deflections of up to 50 deg. Above that, the simulated transient aerodynamic response was found to be in good agreement with experimental data for a variety of deflection times and deflection angles.

扰流板在现代运输机的飞行控制系统中起着至关重要的作用。由于它们的效率和快速的偏转率，它们被广泛用于辅助侧倾控制或用于减轻阵风载荷的目的。模拟扰流板的空气动力学行为仍然是一项具有挑战性的任务，因为扰流板的偏转总是会导致流动分离。因此，本文中介绍的工作重点是通过验证和验证 DLR（德国航空航天中心的内部流动求解器 TAU）在扰流器应用中的应用来扩展 DLR 的应用范围。第一步，工作重点是低速状态下静态和动态扰流板偏转的稳态和非稳态模拟。结果表明，所选择的数值方法非常适合再现高达 50 度的静态扰流板偏转的表面压力分布。