Combustion characteristics of a supersonic combustor model for a JAXA flight experiment

Abstract JAXA is conducting a flight-ground test comparison program to clarify the “facility effect” on hypersonic aerodynamics and combustion phenomena develop CFD tool for predicting flight data from ground data. The aim experiment obtain aerodynamic heating supersonic under actual conditions validate using corresponding This study aimed at determining flow-path geometry fuel injector configuration combustor suitable clarifying influence of different flow compositions between combustion. candidate configurations proposed by were evaluated direct-connect tests ethylene fuel. results showed that was symmetric when equivalence ratio low asymmetric pressure in high. Because an unsuitable validating based steady RANS, total limited 0.44. model uses two-stage injectors cavity flame holders combust depth holder had little However, number injection holes located downstream affected pressure. design finalized results. In addition, ignition method pilot hydrogen injection, adopted experiment, also demonstrated successfully.