Aviation kerosene supersonic combustion in dual-mode scramjet

With the software numerical analysis of the aviation kerosene spray supersonic combustion was carried out in the dual-mode scramjet combustor. At Mach number 5 flight conditions, the numerical results were gotten with the discrete droplet model, the equilibrium reaction kinetics model, the k-w turbulence model and the probability density function turbulence combustion model. The wall static pressure distributions derived with the CFD agreed with the experimental results, and the numerical total pressure loss coefficient 0.703, is lower than the experimental value 0.707. The numerical results show the strut and cavities improve the mixture and combustion, and the combustion efficiency of the combustor exit is 0.62, which is less than the experimental combustion efficiency 0.696. This dual-mode combustion system operates in ramjet mode.