Abstract
This work is to develop a new computational program to determine the effect of using gas propellant of the combustion chamber at high temperature on the calculation of the value of the Prandtl Meyer function and application to supersonic nozzles design. The selected gases are the H2 , O2 , N2 , CO, CO2 , H2 O, NH3 , CH4 and air. Prandtl Meyer function depends on the stagnation temperature, Mach number and the gas used. The specific heat at constant pressure and the enthalpy of the gases vary with the temperature and the selected gas. The gas is still considered as perfect and it will be calorically imperfect and thermally perfect below the threshold of dissociation of molecules. A calculation of the difference between the Prandtl Meyer function for different gases with the air is made for the purpose of comparison. The application is made for designing the supersonic MLN nozzle at high temperature.
Highlights
Gases play an important role in the propulsion of aerospace vehicles
This work is to develop a new computational program to determine the effect of using gas propellant of the combustion chamber at high temperature on the calculation of the value of the Prandtl Meyer function and application to supersonic nozzles design
We focus on the specific heat CP (T ) at high temperature and R gas constant [20,21,22,23,24,25,26,27]
Summary
Gases play an important role in the propulsion of aerospace vehicles. They influence the behavior of the supersonic flows and in particular on all design parameters [1, 2]. References [5,11,12,13,14,15,16,17] have studied at high temperature for air on the supersonic nozzles design by the method of characteristics.
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