Experimental investigation of kerosene fuel combustion in the supersonic flow

For the dual-mode scramjet it is important to conduct experimental research for its combustor. In order to get the performance parameters of the dual-mode combustor model at the different flight Mach, the investigation of liquid fuel kerosene was carried out in the combustor direct-connect wind tunnel. In the non-cold state cases, fuel kerosene realized ignition and stable combustion, the normal shock wave series appeared in the isolator and these operating processes were the typical ramjet modes. With one-dimensional analysis method, the flow field parameters, the total pressure loss coefficient and combustion efficiency were estimated in terms of the measured wall static pressure data. At the combustor outlet, the total pressure loss coefficients of the non-cold state cases were 0.565, 0.696 and 0.725, respectively and consistent with the experimental measurement values. The combustion efficiencies were 0.82, 0.67 and 0.60, respectively. With the data and parameters of the dual-mode combustor, its performance could be improved.