<p>The influence of the surface temperature of a confuser channel, consisting of a converging entrance section and a section of constant cross section, on the structure of a supersonic air flow in the channel and the characteristics of the separation zones in it under the conditions of interaction of compression shocks with a turbulent boundary layer was investigated numerically. A compression shock causing the separation of the boundary layer in the channel was generated by a compression wedge with an angle δ_wed = 13°, located in the entrance section of the channel. The range of the channel surface temperature factor values <i>T</i>_wr = 0.4–1 was considered. The flow in the channel was assumed to be completely turbulent. Numerical data were obtained on the basis of the solution of the Navier–Stokes equations with the use of the <i>k</i>–ω SST turbulence model for the Mach number 4.5 at the inlet cross section of the channel. Data on the structure of the flow in the channel, the pressure and Stanton number distributions in it, and the positions of the beginning and end of the boundary layer separation zones on the lower and side surfaces of the channel are presented.</p>