Li Wang, PhD

This is a good validation for FSI involving highly compressible supersonic flow, as it involves both the shock wave and the two-way FSI. The shock wave induces evident deformation of the flexile plate, which has been both experimentally measured and numerically modelled. See section 4.4 in ref.

This is a two-way FSI in hypersonic flow at Mach = 5.8, which was experimentally measured in a wind tunnel, and this 2D simulation matches very well the experimental measurements in terms of both the histories of the deformation of the flexible plate trailing edge and the pressure near the trailing edge. See section 4.5 in ref.

This blunt body with a spike ahead in supersonic flow is a typical configuration of many space vehicles, and the instability of such FSI is an important issue reqiuring to be properly handled to improve the aerodynamic performance of the vehicle. This preliniminary simulation captures the instability very well even the mesh is far less fine to resolve the turbulence, indicating the interaction of the separations at the leading edge with the blunet body could be the major source of such instabilities.