Toufix Zebbiche
International Journal of Aeronautical and Space Sicences, vol. 10, no. 1, pp.1-13, 2009

Abstract : When the stagnation temperature increases, the specific heat does not remain constant and start to vary with this temperature. The gas is perfect, it’s state equation remains always valid, except, it was called by gas calorically imperfect or gas at high temperatures. The purpose of this work is to develop a mathematical model for a normal shock wave normal at high temperature when the stagnation temperature is taken into account, less than the dissociation of the molecules as a generalisation model of perfect for constant heat specific. A study on the error given by the perfect gas model compared to our model is presented in order to find a limit of application of the perfect gas model. The application is for air.

Keyword : Supersonic flow, subsonic flow, high temperature, supersonic nozzle, thermodynamics ratios, normal shock wave, entropy, relative error, interpolation