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The paper presents the modified method for the supersonic nozzle profiling with respect to non-monotonic dependence of adiabatic index on temperature, as well as the results of nozzle profile calculation for two sets of input parameters, based on independently determined specific heat curve for molecular nitrogen N2 and products of its thermal decomposition in the temperature range of T = 260-1 K and atmospheric pressure.

Supersonic nozzle profiling for supersonic aerospace testing in a view of high-temperature of properties of real gases