Supersonic combustion ramjet technology using liquid hydrocarbon fuels is invaluable due to great benefits of the energy density per unit volume and handling. This study carried out experiments to investigate the effects of the components in thermally cracked n-dodecane on ignition and supersonic combustion behavior at supersonic speeds (Mach 2.0) and at stagnation temperatures between 1800 K and 2400 K in a supersonic model combustor with a cavity flame holder. Components of the thermally cracked n-dodecane at 1.0 MPa in a flow reactor were experimentally measured by using a gas chromatograph. Based on the measured components, surrogate fuels consisting of main components of cracked n-dodecane, hydrogen, methane, ethane and ethylene were defined, and fractions of the component was varied at less than 10%. Ignition and supersonic combustion behaviors were tested for single component and surrogate fuels. In all cases where supersonic combustions were achieved, ignitions were firstly observed in the boundary layer at the expanding cross section zone. The flames, then, propagated upstream and were held at the cavity. Two combustion modes, jet wake stabilized and cavity stabilized flames were observed based on the distribution of rise in pressure and OH chemiluminescence. In cases of pure fuel injections, ignitions for ethylene injections could be observed at a stagnation temperature of 1800 K. On the other hand, ignitions for methane and ethane injections could be observed above a stagnation temperature of 2200 K. Ignitions for surrogate fuel injections were also investigated. These ignition limits were also validated by a simple estimation of chemical reaction and residence times. It was also found that an increase in fuel temperature improved the ignition limits although the effect of the dynamic pressure ratio between the fuel injection and the main flow was rather limited in the present study. (C) 2015 The Combustion Institute. Published by Elsevier Inc. All rights reserved.