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Effect of stagnation temperature on supersonic flow parameters application for air in nozzles

Published online by Cambridge University Press:  03 February 2016

T. Zebbiche  and
Z. Youbi
T. Zebbiche
Affiliation:
Department of Aeronautics, University SAAD Dahleb of Blida, Blida, Algeria
Z. Youbi
Affiliation:
Department of Aeronautics, University SAAD Dahleb of Blida, Blida, Algeria
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Abstract

When the stagnation temperature of a perfect gas increases, the specific heats and their ratio do not remain constant and start to vary with the temperature. The gas remains perfect; its state equations remain valid, so it can be named as calorifically imperfect gas. The aim of this research is to develop the necessary thermodynamic and geometrical equations and to study the supersonic flow at high temperature, lower than the dissociation threshold. The results are found by the resolution of nonlinear algebraic equations and integration of complex analytical functions where the exact calculation is impossible. The dichotomy method is used to solve the nonlinear equations and Simpson’s algorithm for the numerical integration applied. A condensation of the nodes is used. The functions to be integrated have a high gradient at the extremity of the interval of integration. The comparison is made with the calorifically perfect gas to determine the error. The application is made for air in a supersonic nozzle.

Type
Research Article
Information
The Aeronautical Journal , Volume 111 , Issue 1115 , January 2007 , pp. 31 - 40
Copyright
Copyright © Royal Aeronautical Society 2007 

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