Abstract: Experimental investigation of kerosene supersonic combustion was performed on direct-connect supersonic combustion test facility by using four different configurations of cavity flameholders and multi-diameter kerosene injectors. Kerosene equivalence ratio varies from 0.24 to 1.32 and polite hydrogen equivalence ratio was 0.53. Successful ignition and sustain combustion were achieved in multi-test conditions. The distribution of wall static pressure was measured to validate the combustion performances under different test conditions. The experimental results show the four cavity flameholders used in the test have excellent flame holding effects. The configuration of cavity has great influence on the ignition of kerosene in supersonic airstream.Larger length depth ratio was better for the kerosene ignition, and with several cavities, kerosene can achieve self-ignition without pilot hydrogen. equivalence ratio is the most important influencing factor of kerosene combustion capabilities. At same kerosene equivalence ratio, higher injection pressure can improve the kerosene combustion effects.