Numerical Investigation of the Aeroelastic Response of a CFCF Compliant Panel in Hypersonic Flow
This work investigates the aeroelastic response of a Clamped-Free-Clamped-Free (CFCF) compliant panel subjected to hypersonic flow, with emphasis on understanding the flow physics governing the behavior of the aeroelastic response. Inviscid flow models such as Piston Theory and Euler formulations fail to resolve key hypersonic flow features, such as shock-boundary layer interactions (SBLIs) and flow separation. Such features are particularly relevant in an experimental configuration of interest, significantly influencing surface pressure and temperature. Reynolds-Averaged Navier–Stokes (RANS) simulations with the Spalart–Allmaras turbulence model are performed, and the computed static pressure differential across the panel surfaces is incorporated into the aeroelastic equations as a forcing term. Better agreement between the 2D and 3D RANS centerline results were found for higher angles of attack. As the angle of attack increases, the separation regions grow, and the turbulent recirculating flow effect becomes dominant relative to the edge vorticity. Qualitative comparison is made between the steady-state numerical aeroelastic response and the transient experimental displacement panel measurements. An alternative experimental geometry is also proposed, which is a half diamond shape structure, that may have some advantages for future FSI studies.
