Accurately modeling atmospheric re-entry has become incredibly important with the advent of reusable spacecraft. Computational Fluid Dynamic (CFD) employs solvers, a combination of mathematical models, to attempt to replicate real-world physical characteristics, such as when a spacecraft is re-entering the atmosphere. This research attempts to validate the OpenFOAM hy2Foam solver–which was created to model the environment of atmospheric re-entry–by comparing CFD results to real-world wind tunnel data of the hypervelocity ballistic model 1 (HB-1) at mach 5.1. We show with 99% confidence that the CFD simulations do not produce numerically accurate results when compared to historical wind tunnel data at seven varying angles of attack: -1, 0, 2, 4, 6, 8, 10, and 12 degrees. For all angles of attack, the forebody axial-force coefficient disagrees with historical wind tunnel testing, being 2.38 times less on average. Additionally, for all but the -1 and 0 degree angle of attack, the pitching-moment coefficient disagrees with the historical data, being 52.6 times less on average. Additional research conducted on the HB-2 model has found similar disagreement of aerodynamic results demonstrating a need for additional research to ensure the solver produces numerically accurate results. Accurate solvers are vital to ensure that CFD simulations accurately model real-world conditions, such as during spacecraft re-entry when safety of astronauts could be at stake if a spacecraft is designed based on invalid data.