Combustion Scaling in an Inlet Injection Scramjet

摘要

This paper presents the results from a coupled numerical and experimental investigation of the flow and combustion characteristics of an inlet-fuelled scramjet engine. Testing of the model was conducted in the T4 shock tunnel at the University of Queensland in Brisbane. The conditions chosen were equivalent to a flight Mach number range from 7.78 to 8.46 and altitudes ranging from 22.5 km to 30.1 km. The experiments and the CFD exhibit a good agreement across the range tested for both unfuelled and fuelled cases. At the highest altitude of 30.1 km neither the experiment or the CFD show combustion, while there is clear evidence that the H2 fuel is burnt for all the other test conditions.