Reynolds averaged Navier-Stokes and Newton method computations are performed for reentry bodies in hypersonic continuum flow using the computational fluid dynamics (CFD) solver DLR Tau code. The present work intends to compare the DLR Tau code models for equilibrium and non-equilibrium chemistry with the predictions of the Newton method model STRAT, with the purpose of identifying a suitable and versatile setup for the evaluation of different geometries in predevelopment. Special focus hence is on the consistent modeling of wall heat transfer and identifying possible limitations of the models. Equilibrium and non-equilibrium chemistry models are reviewed on reference cases from literature as well as approximate correlations for heat transfer. The equilibrium chemistry, the non-equilibrium, and the Newton method model first are compared on a representative test case of a 2D cylinder for a range of load points common for reentry trajectories. Differences in the reference work are discovered and solved in cooperation with the authors including a difference in cylinder radius. Comparison with approximate correlations for heat transfer shows inconsistencies in the STRAT heat transfer module when applied to 2D geometries. The EURASTROS case further aims to reproduce the capsules’ aerodynamic coefficients, as well as the heat flux and pressure distributions. The DLR Tau code provides accurate results for the aerodynamic coefficients at a maximum deviation of −1.16% from the reference work for cD. Larger deviations of up to −14.3% are found for the heat flux distribution. STRAT presents reasonable results for the pressure distribution and aerodynamic coefficients within 5.1% deviation to Tau, but shows larger deviations of up to 46.9% in stagnation point heat flux.