Quasi-Direct-Connect Scramjet Combustor Experiments in the X3R Shock Tunnel Using T4’s Mach 4 Nozzle

Axisymmetric supersonic combustion experiments were conducted in the newly commissioned X3/R dual-mode free-piston shock tunnel in Brisbane, Australia. Mach 8 flight-equivalent flow was delivered to the supersonic combustor model through the T4 Mach 4 nozzle using the newly commissioned X3/T4 nozzle adapter. The stability of scram-mode, jet-wake-anchored, and dual-mode combustion was observed over a stable facility flow duration of 10 ms. These results were compared to previous experiments of this combustor model in the T4 shock tunnel and showed good agreement regarding normalized pressure distribution and combustion mode transition points. Evolution of inlet unstart was also observed for equivalence ratios greater than 1.0 within stable facility test time.