Video supporting the paper: Unsteady Non-linear Control Surface Modelling for Aeroservoelastic Applications

These two videos show the aeroelastic responses of flexible wings under rapid control surface deflections in the transonic regime (M=0.85). The aileron and spoiler deflections in the videos go from +5.7 degrees to -5.7 degrees in amplitude (with a -30 degrees offset for the spoiler). The videos are not real-time however (about two times slower). A fluid-structure interaction (FSI) framework coupling RANS-CFD and FEM models was used to obtain these simulations. These simulations were then used to validate the aeroelastic and aerodynamic models developed in the following paper: Lancelot, P., De Breuker, R. (2021). "Unsteady Non-linear Control Surface Modelling for Aeroservoelastic Applications". Journal of Aeroelasticity and Structural Dynamics. The FSI setup is also described in this paper.<br><br>

本数据集包含两段视频，展示了跨音速工况（马赫数M=0.85）下柔性机翼在操纵面快速偏转时的气动弹性响应。视频中副翼与扰流板的偏转幅值范围为+5.7度至-5.7度，其中扰流板额外带有-30度的偏移量。需说明的是，本视频并非实时播放，播放速度约为实际速度的二分之一。

本数据集的仿真结果基于耦合了雷诺平均Navier-Stokes计算流体动力学（RANS-CFD）与有限元法（Finite Element Method, FEM）模型的流固耦合（Fluid-Structure Interaction, FSI）框架生成。上述仿真结果被用于验证下述论文中开发的气动弹性与空气动力学模型：Lancelot, P.、De Breuker, R.（2021），《用于伺服气动弹性应用的非定常非线性操纵面建模》，刊载于《气动弹性与结构动力学学报》（Journal of Aeroelasticity and Structural Dynamics）。本数据集采用的流固耦合设置也在该论文中有所阐述。