Numerical simulation of subsonic ICP flow and exhausted air-plasma jets around the flat-face model with SiC coating were performed for IPG-4 (IPM RAS) facility test regimes simulating the re-entry heating of the Pre-X space vehicle (Earth). The calculation of the body heat flux maps was based on numerical solution of one-dimensional equations of laminar thermally and chemically non-equilibrium multi components boundary layer with finite thickness. The calculated values of the stagnation point heat fluxes for SiC samples do not depend on thermal non-equilibrium. The duplication predicts the reduction of the wall temperature of the SiC sample by 300-350 K with respects to fully a catalytic wall at the peak heating part of the trajectories.
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