Transonic Aeroelastic Flutter Computations With Mesh Adaptation

This paper considers multiscale mesh adaptation of aeroelastic wing models in transonic flow. Workflows are developed which allow for high-fidelity static aeroelastic equilibrium conditions and a matched-point dynamic aeroelastic flutter mechanism, to evolve alongside the mesh adaptation mechanics, via a staggered procedure. Rather than enforcing static equilibrium or matched-point constraints for a given mesh, these conditions are allowed to be more gradually met across the mesh adaptation process. These cost-effective workflows are successfully demonstrated for a wing-body semispan wind tunnel model. For this configuration, the results show substantial interdependencies between the mesh-adapted static and dynamic aeroelastic physics.