Characteristics of fluid structure interactions due to leading edge vortex systems impact

细长的机翼与适度到高度掠后的前缘创造了一个前缘涡系统，以实现在亚音速和跨音速状态下的高机动性。当迎角较大时，前缘涡以涡爆的形式发生结构变化，在涡爆位置下游存在高湍流流场，湍流动能在一定频率范围内集中。这种类型的气流一方面可以激发产生这种气流的机翼，另一方面，位于下游的部件，如水平和/或垂直尾翼，可以产生强烈的结构振动。这种动态气动弹性问题被称为抖振，它的激励力是在分离流动和涡爆情况下普遍存在的非定常气动力造成的。相对于对刚性表面前缘涡流动的大量实验和数值数据，对非定常流场与结构振动耦合问题的研究很少。因此，本项目旨在通过对模块化模型配置的互补实验和数值分析，详细介绍流动物理和结构动力学的相互作用。该结构包括一个双三角翼，以产生干扰的前缘涡系统，以及一个水平尾翼和一个双垂直尾翼。提供了机翼和尾翼部件的模型结构，包括刚性部件和结构弹性部件。这种方法可以通过系统排列组件来量化各自在流动结构相互作用中的贡献，从而清楚地突出结构弹性表面上气动激励特性的主导作用。研究结果将创建一个以前不可用的数据库，并有助于更精确的飞机设计方法以及改进的数值预测能力。

Slender wings with moderately up to highly swept leading edges create a system of leading edge vortices to achieve high maneuverability in the sub- and transonic regime. For high angles of attack, the leading edge vortices experience a structural change in the form of vortex bursting, which is associated with a highly turbulent flow field downstream of the bursting location with concentrations of the turbulent kinetic energy in certain frequency ranges. This type of flow can, on the one hand, excite the wing that generates it and, on the other hand, components located downstream, such as horizontal and/or vertical tails, to strong structural vibrations. This dynamic aeroelastic problem is known as buffeting, the excitation forces of which result in the present case from the unsteady aerodynamic forces that prevail in the case of separated flow and vortex bursting. Relative to the large experimental and numerical data base for leading edge vortex flow on surfaces that are more or less treated as rigid, only very few studies are available for the coupled probelm of unsteady flow and structural vibrations. The present project is therefore intended to detail the interaction of flow physics and structural dynamics through complementary experimental and numerical analyzes on a modular model configuration. The configuration consists of a double delta wing to generate an interfering leading edge vortex system as well as a horizontal tail and a twin vertical tail. The model structure for wing and tail components is provided to include both rigid and structurally elastic parts. This approach enables to quantify the respective contribution in the flow structure interaction through a systematic permutation of components to clearly highlight dominant effects in the aerodynamic excitation characteristics on structurally elastic surfaces. The results will create a previously unavailable database and contribute to a more precise approach to aircraft design as well as to refined numerical prediction capabilities.