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CSME 2019/12
Volume 40 No.6
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741-751
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Stagnation Temperature Effect on the Flow in the Supersonic Axisymmetric Minimum Length Nozzlewith Application for Air
Mohamed Roudane a, Toufik Zebbiche b and Mohamed Boun-jad a
aDepartment of Mechanical Engineering, Faculty of Technology, University of Blida 1, BP 270 Blida 09000, Algeria.
bInstituteof AeronauticsandSpace Studies, University of Blida 1, BP 270 Blida 09000, Algeria.
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Abstract:
The work is to develop a new numerical calculation program to do the correction of the flow parameters in a supersonic axisymmetric minimum length nozzle, dimensioned on the basis of use of ideal gas assumptions at constant CP, giving a uniform and parallel flow at the exit section, by using the model at high temperature of CP variable with the temperature, lower than the threshold of dissociation of the molecules. The shape of the nozzle does not change. It is determined by using the method of characteristics. Only the behavior of the gas exchange and regards itself as a high-temperature gas. It shows that the flow at the exit section of the nozzle is no more uniform and parallel and one will find a degradation of this parameter. Also the flow through the nozzle will be completely changed in comparison with that given by the PG model and in particular the coefficient of the pressure force will be fixed. All flow parameters depend on the stagnation temperature and the exit Mach number. Error caused by the perfect gas model over to high temperature model is calculated. The application is for air.
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Keywords: Axisymmetric Minimum Length Nozzle, High temperature, Cubic spline interpolation method, Predictor corrector algorithm, Method of Characteristics, Flow parameters.
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©
2019
CSME , ISSN 0257-9731
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