This study explores hypersonic flow separation, vital for hypersonic space vehicle designs. It is challenging to model shock wave boundary layer interaction (SWBLI) in high-speed gas flow through compression corners. Comparative experiments on various flow models reveal insights into hypersonic chemical non-equilibrium flow. Divergence in shockwave behaviour is influenced by re-circulation zone variations, emphasizing the flow dynamics complexity. Compression corner tests, using the k-omega SST model, elucidate this turbulent boundary layer flow. The successful flow separation which occurs due to the effects of SWBLI interaction is captured. The use of RANS techniques requires advanced models for non-equilibrium turbulent processes, crucial for understanding shock wave boundary layer interactions' effects on pressure and heating loads. This study provides a comprehensive understanding of hypersonic chemical non-equilibrium flow, emphasizing the importance of suitable models, meticulous mesh refinement, and accurate boundary conditions for robust simulations and meaningful comparisons with experimental data.