International Journal of Aeronautical and Space Sciences

  • 제10권1호
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  • Pages.1-14
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  • 2009
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  • 2093-274X(pISSN)
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  • 2093-2480(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
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Effect of the Stagnation Temperature on the Normal Shock Wave

  • Zebbiche, Toufik (Department of Aeronautics, Faculty of Engineering, University SAAD Dahleb of Blida)
  • 발행 : 2009.05.30
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초록

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.

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참고문헌

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피인용 문헌

  1. Stagnation temperature effect on the supersonic flow around pointed airfoils with application for air vol.19, pp.3, 2018, https://doi.org/10.1051/meca/2018001
  2. Stagnation Temperature Effect on the Supersonic Flow Around Pointed Airfoils with Application for Air pp.2191-4281, 2018, https://doi.org/10.1007/s13369-018-3451-4