Optimization of Hypersonic Scramjet Triple-Ramped Inlet Configurations: Enhancing Pressure Recovery , Shock Stability and Thermal Performance

This study focuses on the computational and optimization-based evaluation of hypersonic triple-ramped scramjet inlets to improve pressure recovery, shock stability and thermal performance at Mach 5 and above. Computational Fluid Dynamics (CFD) simulations combined with Finite Element Analysis (FEA) are utilized, also multi-objective Non-Dominated Sorting Algorithm is used for optimizing the inlet designs. The results from the analysis indicates that the triple-ramp configuration have superior aerodynamic and thermal efficiency as compared to dual or single ramped inlets. Key-Words – Scramjet inlet, hypersonic flow, shock-wave boundary layer interaction, CFD, NSGA-II, FEA, SBX.