Supersonic Two-Dimensional Minimum Length Nozzle Design at High Temperature. Application for Air

When the stagnation temperature of a perfect gas increases, the specific heat ratio does not remain constant any more, and start to vary with this temperature. The gas remains perfect, its state equation remains always valid, except it will name in more calorically imperfect gas or gas at High Temperature. The goal of this work is to trace the profiles of the supersonic Minimum Length Nozzle with centered expansion when the stagnation temperature is taken into account, lower than the threshold of dissociation of the molecules and to have for each exit Mach number several nozzles shapes by changing the value of the temperature. The method of characteristics is used with a new form of the Prandtl Meyer function at high temperature. The resolution of the obtained equations is done by the second order of finite differences method by using the predictor corrector algorithm. A study on the error given by the perfect gas model compared to our model is presented. The comparison is made with a calorically perfect gas for goal to give a limit of application of this model.The application is for the air.

作 者： Toufik Zebbiche ZineEddine Youbi   作者單位： Department of Aeronautics, Faculty of Sciences of Engineer, University SAAD Dahleb of Blida,B.P. 270 Ouled Yaich, 09470 Blida, Algeria  刊 名： 中國航空學報（英文版）  ISTIC 英文刊名： CHINESE JOURNAL OF AERONAUTICS  年，卷(期)： 2007 20(1)  分類號： V2  關鍵詞： supersonic flow   minimum length nozzle   calorically imperfect gas   interpolation   Prandtl Meyer function   stretching function   Simpson quadrature   supersonic parameters   conception   method of characteristics  

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