Heat transfer from hypersonic air flow to the «EXPERT» nose region was simulated in the high-frequency plasmatron. The heat flux and surface temperature on the sintered SiC samples are duplicated for the altitudes 52.6 and 43 km in subsonic dissociated air jet flows. Experimental prediction of the heat flux and surface temperature for SiC surface was made under the real flight values of enthalpy, stagnation pressure and velocity gradient at the vehicle stagnation point. Flow parameters and probability of nitrogen and oxygen atoms recombination on the SiC surface were determined by matching the experimental and computational data, in particular the heat flux data. Computational data were obtained by multiparameter numerical simulations of plasma flow in the discharge channel, flow over the model (М << 1), and nonequilibrium boundary layer.
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