A multi-fidelity study of the aerothermodynamics of a slab delta wing is performed in the context of advancing the understanding of re-entry flow. The slab delta wing is a basic model geometry that provides an avenue for investigating fundamental flow phenomena in an environment of reduced overall complexity. The study assesses the viability of simplified aerothermal analysis techniques for the rapid prediction of heating and pressure outcomes on generic hypersonic geometries. A sophisticated computational fluid dynamics workflow, implemented in OpenFOAM and incorporating meshing strategies designed to accurately account for hypersonic flow characteristics, is validated against experimental results. Computational outcomes found using both levels of analysis are scrutinized regarding their approximation to physical reality, and salient flow features are identified. Specific attention is paid to the success with which the numerical framework captures heat transfer profiles and their interplay with underlying flow phenomena. The significance of viscous effects and their impact on flow structure are evaluated through comparison to a simulation of the Euler equations.