Non-linear panel instabilities at high-subsonic and low supersonic speeds solved with strongly coupled CIRA FSI framework

Abstract

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.