Wall heat flux distributions under different configurations for a kerosene-fueled supersonic combustor were experimentally studied. The influences of combustion, global fuel equivalence ratio, mass flow rate, total temperature, and inlet Mach number on the wall heat flux of the kerosene-fueled supersonic combustor were systematically presented and analyzed for the first time. Methods to calibrate and validate the in-house-developed heat flux sensors are also presented. The revealed trends would be useful to guide the design of thermal management systems for kerosene-fueled scramjets.