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Heat transfer management of the combustion chamber walls of rocket engines is key to predicting their life-cycle. This study used a test apparatus to measure heat transfer on the inner wall of a film-cooled combustion chamber. Experiments on a heat-sink GH2/GO2 combustion chamber with film cooling at the injector head were carried out to measure the distribution of wall heat flux and temperature under different chamber pressures and propellant mixture ratios. Averaged heat fluxes and transient values were obtained in the tests, which found a high correlation between transient heat flux and chamber pressure. A heat flux peak appeared in the near-injector region, and its distance from the injector head increased with chamber pressure. The thermal loads decreased obviously when the mixture ratio was increased from 5.0 to 7.0. The measurement data were used to interpolate two-dimensional contours of the wall’s thermal loads. The results will be useful for the thermal-structural analysis needed to provide detailed boundary conditions in the hot-gas-side walls of rocket combustion chambers.