Nonlinear aspects of aeroelastic stability are here investigated for two and three dimensional panels in high subsonic and low supersonic flows. The effects of edge constraints and initial conditions on post-flutter behaviour are also studied.

Such phenomena are crucial for spatial launchers development, that has renewed interest due to a larger number of commercial companies in the frame of space flight access.

Numerical analyses are carried out with a framework developed at CIRA, able to deal with Fluid Structure Interaction simulation in a partitioned approach. The CIRA multi-block structured flow solver for unsteady Navier–Stokes equations was updated and tightly coupled with the open-source finite element method code CalculiX in a modular approach.

The results are compared in terms of static divergence and Limit Cycle Oscillations with literature results.

在高亚音速流和低超音速流中，对二维和三维面板的气动弹性稳定性的非线性方面进行了研究。还研究了边缘约束和初始条件对颤振后行为的影响。

这种现象对于空间发射器的发展至关重要，由于在太空飞行方面越来越多的商业公司，这种现象引起了人们的兴趣。

使用CIRA开发的框架进行了数值分析，该框架能够以分区的方式处理流体结构相互作用模拟。更新了用于非稳定Navier–Stokes方程的CIRA多块结构化流求解器，并以模块化方法与开源有限元方法代码CalculiX紧密耦合。

将结果在静态偏差和极限循环振荡方面与文献结果进行比较。