The aviation kerosene is a practical candidate fuel for scram-jet engine in the flight regimes of Mach number less than 8, because of the characteristic of high energy, high density, safety and portable. The key is how to achieve shabbily burning in super combustor. In this paper, the ignition characteristics of a scramjet combustor model fueled by aviation kerosene is experimentally investigated by using the resistance heating direct-connected supersonic combustion facility of Northwestern Polytechnical University. The inflow conditions at the direct-connected combustor entrance are specified as: the nominal Mach of 2, the total temperature of 870-930 K and the total pressure of about 770 kPa. Three combustor performances of different ER are compared and analyzed by applying CFD simulation. The experimental results suggest that the cavity design is a key problem for kerosene successful ignition in the combustor. The choice of appropriate gas-oil ratio can increase the performance of combustor and keep the isolator from being interfered by gas.