An Investigation of a Mach 15 Flow Over A Blunt Wedge Using First-Principles Potential Energy Surfaces: Influence of Wall Temperature

The work presented here represents a continuation of our previous efforts to obtain the entire hypersonic aerothermodynamic field around a two-dimensional (or axisymmetric) body at near-continuum conditions that are physically representative of hypersonic laminar flow conditions. Here, we extend the investigation to multiple wall temperatures. This approach provides solutions where the coupling between the gas flow mechanics, the local gas-phase thermochemical nonequilibrium, and the diffusive mechanisms for mass, momentum, and energy are all obtained within a consistent, empiricism-free framework. Select comparisons with state-of-the-art computational fluid dynamic solutions obtained with NASA Fun3D will be detailed.