This paper numerically investigates the heat transfer characteristics of supersonic high-temperature combustion-gas jet impinging to a perpendicular flat plate. First, the numerical method is validated using an experimental case and meanwhile different turbulence models are evaluated for heat transfer prediction. Then, the effects of multi-species, nozzle-to-plate distance, and nozzle pressure ratio on wall heat transfer are studied through a series of numerical experiments. Comparison of different turbulence models indicates that the variations of turbulent viscosity across the detached normal shock wave differ among the studied three models. Furthermore, if the real multi-species of combustion-gas are mixed as a single species with the same thermal-physical properties, the pressure and heat flux distributions are identical with the results of combustion-gas. Finally, when there is no stagnation bubble in the jet flow field, the heat flux on the flat plate produces a local minimum at the stagnation point for short nozzle-to-plate distance, while a local maximum appears at the stagnation point for large nozzle-to-plate distance. When the stagnation bubble exists, the other maximum of heat flux is produced at the edge of bubble.
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