Modification of direct-connect facility and design of dedicated active-cooling systems for nozzle adapter and combustor in the context of scramjet combustion chamber testing
摘要
The design and testing of the combustor for the Scramjet Hypersonic Experimental Vehicle (SHEV) presents a challenge due to the complexity of supersonic combustion within a scramjet combustor. Within the framework of an Italian national project co-funded by the national research program PRO.R.A and the Italian Space Agency (ASI), a comprehensive analysis was carried out. The analysis aimed to develop a robust numerical methodology for characterizing the fluid dynamics and thermo-chemical behavior of the scramjet combustor. This approach will be validated through the experimental results from direct-connect facility tests and will support future aero-propulsive assessments. It will also support future aero-propulsive assessments to verify the thrust produced by the scramjet combustor.