Evaluation of Shock Wave-Boundary Layer Interaction Modeling Capabilities for Use in a Hypersonic Aerothermoelastic Framework

This study examines the ability of a computational fluid dynamics solver that employs adaptive mesh refinement and embedded boundaries to model turbulent shock wave-boundary layer interactions. Additionally, a basis is provided for constructing a reduced order model for use in an aerothermoelastic analysis framework. The configuration examined is a panel on an inclined surface. First, the flow solver is used to model Mach 2.9 flow over a 24° compression ramp. The boundary layer properties, pressure profiles, and shock oscillation frequency modeled by the solver are compared to Direct Numerical Simulation and experimental results. Next, a strategy for generating the reduced order model is outlines. It is found that the frequency component caused by the shock oscillation does not propagate into the boundary layer downstream of the interaction and that deformations of the panel cause variations in time-averaged pressure distribution and turbulence in the boundary layer. However, the change in turbulence does not significantly affect the aeroelastic response of the structure. These findings support the use of a reduced order model composed of flow solutions where turbulence is one-way coupled.