ஏரோநாட்டிக்ஸ் & ஏரோஸ்பேஸ் இன்ஜினியரிங் ஜர்னல்
திறந்த அணுகல்

சுருக்கம்

Numerical Investigation on Scramjet Performance Parameters at Various Mach Numbers and Inlet Forebody Ramps

Mayur Anvekar, Venkatesh Kusnur

Scramjet is a hypersonic vehicle, and its performance majorly depends on upstream subcomponents and the amount of fuel consumed. The engine thrust is produced using divergent nozzle but it will have a large pressure thrust component as well. A triple ramp scramjet engine will escalate the pressure and temperature of the approaching air to a higher-level which further approach to the combustion chamber and nozzle, results in high momentum and pressure thrust. The scramjet engine performance parameters are investigated for two different triple ramps at various Mach number ranging from lower supersonic to hypersonic speeds, and also at various equivalence ratios. It also helps in understanding the start and unstarts conditions of the engine and the relative variations in the performance. Two different fore body triple ramps are studied to understand the variations in their scramjet performance. Study of hydrogen-based triple ramp scramjet at various equivalence ratios will result in understanding the significant variations in thrust generation and also the other related performance parameters. The performance parameters focused in this research work are thrust, propulsive efficiency, specific impulse, specific thrust, and specific fuel consumptions.