Chatelain, PhilippeSchrooyen, PierreHarika, JohnnyJohnnyHarika2025-05-142025-05-142025-05-142023https://hdl.handle.net/2078.2/33659Developing ablative Thermal Protection Systems (TPS) is the next stage for understanding the universe. These TPS are designed to endure extreme conditions, enabling spacecraft to enter planetary atmospheres, collect samples from other planets, and will be used for human missions. As no ground test can reproduce the exact flight conditions, simulation tools are used to design and size the TPS. Four categories of solvers can be found: flow, material, loosely coupled and unified solvers. This thesis is aimed at enhancing the flow solver implemented in Argo. This improvement builds upon the previous developments of the code in which a material solver and a unified solver have been implemented. Even though flow solvers are less accurate than unified solvers when focusing on the gas-surface interactions, they remain powerful tools in the early stages of the development of a TPS. Indeed, there computational costs remain lower for the results they can get. To achieve this, a mass and energy balance accounting for the gas-surface interactions is implemented. The material response is modeled using simplifying assumptions. The models used in this thesis allow to consider the catalytic reactions and the re-radiation of the energy due to the surface. Those models were first tested against test codes and then, the physical solutions were observed for different wall conditions and mixture properties.Atmospheric entryThermal Protection System (TPS)AblationCFDGas-surface interaction modelling during atmospheric entrytext::thesis::master thesisthesis:43282