Aeroelastic response of a panel under high speed turbulent boundary layers using direct numerical simulation

The interaction between a thin panel and a Mach 2.25 turbulent boundary layer is investigated using a high-accuracy, high-fidelity approach for the simulation of coupled fluid-structure problems. The solid solution is found by integrating the conservation of momentum equation using a non-linear 3D finite element solver, and the direct numerical simulation of the turbulent boundary layer uses a finite-difference compressible Navier- Stokes solver. The evolution of the panel response progresses from the emergence of low amplitude traveling bending waves to a larger amplitude standing wave type motion. Panel defections exceed 25 wall units into the boundary layer and produce compression waves that oscillate with the panel motion. Turbulence statistics are shown to be modified by the presence of the compliant panel. A large dependence on coupling configuration is shown.