Shock wave/boundary layer interaction results in significant aerodynamic heating on the surface of the aircraft. The original flow field structure is also affected by the increase in wall temperature. To investigate the flow field characteristics of shock wave/boundary layer interaction under CHT (conjugate heat transfer) conditions, numerical simulations were performed. The flow field structure, wall parameters and solid domain temperature distribution were analyzed under different wall materials, aerodynamic heating time and total temperature. The numerical results indicate that: the length of the separation bubble obtained using the CHT method is between the results for isothermal and adiabatic walls. As the thermal diffusivity of the wall material decreases and the aerodynamic heating time increases, the length of the separation bubble increases. At the same time, the wall temperature peak increases, and the heat flux peak decreases. For the same material and heating time, an increase in total temperature reduces the length of the separation bubble. This suggests that the change in Reynolds number caused by the total temperature dominates the separation characteristics. Additionally, for the solid domain at the corresponding position of the reattachment zone downstream of the interaction, a significant temperature rise is observed. The high-temperature zone inside the bakelite wall diffuses very slowly and exhibits a flaky distribution.