Hypersonic Sharp Fin Shock/Boundary-Layer Interaction Predictions Over a Thermomechanically-Compliant Panel

Reducing design conservatism for high-speed flight systems requires accurately modeling shock/boundary-layer interactions (SBLI) and any aerothermoelastic phenomena resulting from them. The three-dimensional sharp fin SBLI introduces quasi-conical symmetry with significant thermal and mechanical load enhancements in an otherwise undisturbed flat-plate system. While studied extensively at lower supersonic Mach numbers, there is limited data on these interactions at hypersonic-relevant Mach numbers, and efforts have only recently begun towards understanding fluid-thermal-structural interaction (FTSI) associated with them. This work investigates the sharp fin interaction for three different flow conditions in conjunction with experiments at the NASA Langley Research Center: two Mach 6 (low and high Reynolds number) cases and a Mach 10 case. Results from steady and unsteady aerothermal simulations are discussed. SBLI footprints are quantified with virtual conical origin and inceptive origin predictions. Comparisons of pressure and wall heat flux against empirical models are discussed, and flowfield regimes are determined. Unsteady FTSI computations from a thin, compliant panel underneath the interaction are also analyzed.