Numerical Simulation of a Scramjet Engine for JAXA's Flight Experiment Using Hyshot

In this study, a numerical simulation was made on the scramjet engine examined in the JAXA’s flight experiment program using the HyShot planed for 2005 under Mach 8 flight conditions. Two different fuel injectors were applied to the engine, namely Hyper Mixer injector, which generates streamwise vortices to enhance supersonic mixing and combustion, and Back Step injector, which generates no streamwise vortices. The numerical simulation method well predicted the ground experiment data obtained by the High Enthalpy Shock Tunnel (HIEST) before the flight experiment. The computed results revealed the details of the engine characteristics and the influences of changing the incoming free stream temperature and the wall temperature, which are probably different between the flight experiment and the ground experiment.