Oreste RUSSO, Pietro RONCIONI, Marco MARINI, Sara DI BENEDET TO, Giuliano RANUZZI, Simone PIZZURRO

DOI Number: 10.60853/7qpn-kj96

Conference number: HiSST-2024-00126

The paper focuses on the assessment of propulsive and combustion performances of a scramjet engine in hypersonic cruise conditions and its emission indexes for various species involved in the combustion process. Nose-to-tail CFD analysis of the entire internal flow path (inlet, combustor and nozzle) are performed in flight-cruise configuration, for both power-off and power-on conditions, by using ANSYS FLUENT software with steady RANS model with available literature chemical schemes. The performance parameters (combustion efficiency and kinetic and thermodynamic quantities) revealed a significant improvement as well as the achievement of very high combustion efficiency by the end of the engine cycle is achieved.

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In Categories: 1.Events, High-Speed Aerodynamics and Aerothermodynamics, HiSST 2024
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