Math. Model. Nat. Phenom.
Volume 15, 2020
|Number of page(s)||26|
|Published online||04 December 2020|
Gas effect for oblique and conical shock waves at high temperature
Industrial Technology Studies and Research Laboratory (Ex Aircraft Laboratory), Department of Mechanical Engineering, Faculty of Technology, University of Blida 1, Algeria.
2 Institute of Aeronautics and Space Studies, University of Blida 1, BP 270 Blida 09000, Algeria.
* Corresponding author: firstname.lastname@example.org
Accepted: 18 September 2020
The work focuses to develop a new numerical calculation program for determining the gas effect at high temperature instead air on the calculation of the oblique and conical shock waves parameters and make applications for various external and internal aerodynamics problems like, the calculation of the suitable intake adaptation parameters, dihedron and cone wave drag, aerodynamic coefficients of a pointed supersonic airfoil and oblique shock reflection without forgetting others no less important like the detonation propulsion and the dust explosion applications, where the high temperature gas effect is very important. All this for future aerodynamics (gas dynamics) like the phenomenon of climate change in the near and far future because of the enlargement progressive of the layer ozone hole which will lead to an increase in the temperature of the ambient medium, and by the environment pollution by the shining of the waste which will cause a new decomposition of gases from the ambient environment. Another interesting application for actual aerodynamics (gas dynamics) is the performance of tests in wind tunnels supplied by a combustion chamber making a reaction of gases giving a gas with new thermodynamics parameters which is not necessarily air. To make a calculation, the selected gases are H2, O2, N2, CO, CO2, H2O, NH3, CH4 and air. All shock parameters depend on the stagnation temperature, upstream Mach number, the thermodynamics of the used gas, dihedron and cone deviation and others parameters. The specific heat at constant pressure varies with the temperature and the selected gas. Gas is still considered as perfect. It is calorically imperfect, and thermally perfect, less than the molecules dissociation threshold. A comparison between the parameters of each gas and air is presented to choose the suitable gas witch giving good performances as required by design parameters instead air.
Mathematics Subject Classification: 35Q92
Key words: Supersonic flow / subsonic flow / high temperature / thermodynamics ratios / normal shock wave / oblique shock wave / gas / conical shock wave / intake adaptation / shock reflection / aerodynamic coefficients / pointed airfoil / specific heat at constant pressure / detonation propulsion / dust explosion / error
© The authors. Published by EDP Sciences, 2020
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