Evaluation of Turbulent-Combustion Models for a Hydrogen Fueled Scramjet Engine Using RANS Simulation

Supersonic combustion ramjet (scramjet) engines represent a key propulsion technology for high-speed atmospheric flight, where efficient fuel injection and flame stabilization remain critical challenges. In this study, we conduct a numerical analysis of a hydrogen-fueled scramjet combustor, focusing on the impact of different combustion models on flow characteristics and overall performance. To achieve computational efficiency while maintaining accuracy, Reynolds-Averaged Navier-Stokes (RANS) simulations were performed. Two turbulent-combustion models, including laminar chemistry and Partially Stirred Reactor (PaSR), were systematically compared. The numerical results were validated against available experimental data to assess the predictive ability of each model in capturing key phenomena such as ignition, flame stabilization, and thermal choking. To achieve this, this study aims to select an appropriate combustion model that can objectively evaluate and enhance the reliability of numerical predictions through thorough comparisons with previously validated scramjet cases. This study aims to provide valuable insights for the development of computationally efficient and accurate prediction tools. This will advance the design and optimization of future scramjet propulsion systems.