With the advances in the plasma technology in several fields as waste management, space technology and medical applications, non-thermal plasmas have become popular. They replace the combustion fuels for stationary hall thrusters and require minimal voltage to sustain longer duration. Generally, non-reactive gases such as Xenon, Argon, Krypton in a pure or mixture form is used to generate plasma, in order to have overall better performance of the system. Hence, the study of these gases and its properties becomes very crucial for further improvement in any kind of application. Xenon has proven to be most efficient in Hall thruster as compared to the other gases, but its limited availability and high cost has led to the idea of replacing it with other gases that are in abundant. As the DC glow discharge is considered to be canonical problem of interest, the paper focuses on modelling and simulation of 1-D and 2-D. DC glow discharge tubes using Argon and Xenon as gases to generate plasma and study its properties. The trend in distribution of electron density, electron temperature and electric potential have shown little variation. However, the magnitude on electron density is slightly higher for Argon relative to Xenon for given operating conditions in 1-D simulation and in the case of 2-D simulation the diffusive nature in lateral direction has shown higher peak value for Xenon.
Staged transverse sonic injection into supersonic flow in a confined environment usually employed in scramjet combustor has been explored numerically using an indigenously developed three-dimensional Reynolds Averaged Navier Stokes solver with Roes scheme and k-w turbulence model. Simulations were carried out for both without injection and with injection in Mach 2 flow behind a backward-facing step in a rectangular duct. Simulation captured all finer details of flow structures including recirculation bubble behind a backward-facing step, barrel shocks and Mach discs caused due to transverse injection and reattachment of shear layer in the downstream wake region. K-w turbulence model with compressibility correction performed extremely well in predicting the overall behaviour of the flow field. The jet from the second injector was found to penetrate more in the free-stream due to the loss of free-stream total pressure across the barrel shock of the first injection point. Excellent agreement of computed profiles of various flow parameters at different axial locations in the duct with experimental results and other numerical results available in the literature demonstrate the robustness and accuracy of the indigenously developed code.
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