High Temperature Gas Effect on the Normal Shock Wave Parameters
The aim of this work is to develop a new computational numerical program to determine the effect of gas of
propulsion on the variation of the thermodynamics parameters and Mach number through a normal shock wave in the case at
high temperature below the threshold of dissociation of molecules. The chosen gases are H2, O2, N2, CO, CO2, H2O, NH3, CH4,
and air. The gas is considered as perfect. Its state equation is valid. It is calorically imperfect and thermally perfect. In this case
the specific heats are function of temperature. The calculation of the error committed by the gas compared to air will be
presented for goal to make a suitable choice of gas instead of air. The application is for the nozzle.
Index Terms - High Temperature, Normal Shock Wave, Supersonic And Subsonic Flow, Thermodynamics Ratios