Quantifying the Influence of Parametric Variation on Internal Flow Characteristics in Hybrid Scramjet Combustor

Scramjet technology enables lightweight space missions, with successful tests conducted worldwide. Researchers are continuously refining combustor designs by incorporating turbulence inserts, flame holders, and struts in parallel-cavity combustors to enhance performance. One such refinement in scramjet combustor design is the addition of a strut to the parallel-cavity configuration. This study utilizes computational fluid dynamics to analyze behaviour internal flow field variables and to estimate the performance of the combustor. The research work presents a parametric variation of the inlet variables for the current combustor. The inlet variable such as the inlet Mach number, temperature and pressure are estimated with the motive to identify the optimum boundary variable on which the scramjet model operates optimum. A validation study has been conducted, the simulation results and the experimental results are in good accord. The computational observations indicate the scramjet model achieves optimal performance at M _air =2.52, Inlet temperature = 340K, and fuel pressure = 1 bar.