As one of the active cooling methods, the opposing jet shows its advantages on the aerodynamic thermal reduction for hypersonic flight. To accurately predict the thermal protection properties of the opposing jet, the numerical investigation on the flow and heat transfer characteristics for the opposing jet of nosecone at Mach 6 was conducted by using a fluid-thermal coupling strategy. The related turbulent model and fluid-thermal coupled method were validated by the comparison of the numerical and experimental results. Flow patterns of the opposing jet with different total pressure ratio were gained, and the influence of the total pressure ratio of the opposing jet on the heat transfer between fluid and solid structure was discussed. Besides, the influences of attack angle and solid materials on structural heat reduction were also investigated. The numerical results indicate that:the increase of total pressure ratio of the opposing jet brings obviously further heating reduction, and accordingly the solid structure temperature presents more uniformity; calculation of the heating in 60 s indicates that the positive attack angle enlarges the temperature difference in the solid structure, which induces the lower temperature air flowing to the leeward side furtherly, so the cooling for the leeward side of nosecone is enhanced; for alloy IN718 and C-103 two different materials, their discrepancy of heating can be neglected at the cooling recirculation region of nosecone and the area where the recompression shock influence obviously; in comparison, the use of C-103 shows its advantage of even distribution of temperature in the internal system of structure.