Modeling of high pressure arc-discharge with a fully-implicit Navier–Stokes stabilized finite element flow solver

Sahai, Amal; Mansour, Nagi N.; López, Bruno; Panesi, Marco

doi:10.1088/1361-6595/aa638b

Cited by 12 publications

(3 citation statements)

References 69 publications

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“…For example, numerical simulations of a 20 MW aerodynamic heating facility and 60 MW interaction heating facility have been conducted [22][23][24]. Sahai et al [25] numerically investigated a three-dimensional unsteady arc-heated flow. Takahashi et al [26][27][28][29] conducted plasma flow analyses of a 20 kW constrictor-type Japan Aerospace Exploration Agency (JAXA) arc-heated wind tunnel and a DLR arc-heated wind tunnel.…”

Section: Introductionmentioning

confidence: 99%

Nonequilibrium shock layer in large-scale arc-heated wind tunnel

Takahashi¹,

Takasawa²,

Yamada³

et al. 2022

J. Phys. D: Appl. Phys.

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An arc-heated wind tunnel is one of the most important facilities to reproduce the high-temperature environment during atmospheric entry for plasma studies and spacecraft development. However, the properties of the plasma flow cannot be determined easily, because of the complex physical phenomena, such as arc discharge and supersonic expansion, occurring inside the tunnel. The shock-layer structure should be clarified to evaluate the aerodynamic characteristics, communication conditions, and thermal- protection performance in a high-temperature environment. In this study, shock-layer spectroscopic measurements of a plasma flow in a 1 MW-class arc-heated wind tunnel were performed. The γ-band system spectra of nitric oxide (NO) molecules in the ultraviolet region were measured, and the rotational temperature was determined via spectral fitting through comparison with numerical spectra. The rotational temperature of the NO molecules in the shock layer was 6,620±350 K, whereas that in the free jet was much lower at 770±60 K. This difference is attributed to the increase in translational temperature by flow stagnation across the shock wave, followed by the increase in rotational temperature owing to energy relaxation. A computational science approach revealed the detailed structure of the flow through comparisons with the spectroscopic measurement data. The wind tunnel flow became hypersonic with high temperature and low pressure due to the expansion and acceleration at the nozzle and test chamber. Although the temperature increased across the shock wave, the chemical reaction progressed slowly owing to the low-pressure environment. The rotational temperature in the shock layer increased with the translational temperature; this agrees with the trend of the measurement results. The arc-heated flow was found to be in strong thermo- chemical nonequilibrium in the shock layer. Through this study, a detailed structure of arc-heated flow was revealed and its methodology was also proposed.

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Section: Introductionmentioning

confidence: 99%

Nonequilibrium shock layer in large-scale arc-heated wind tunnel

Takahashi¹,

Takasawa²,

Yamada³

et al. 2022

J. Phys. D: Appl. Phys.

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“…Plasma flow simulations performed by Katsurayama et al [18] and Yu et al [19] indi-cated that a higher-accuracy transport property model is effective at accurately predicting the discharge formation. Sahai et al [20] carried out an unsteady three-dimensional (3D) simulation of the arc-heating flow in NASA's 20 MW AHF, and the dynamic process of the discharge attachment on electrodes was captured by the simulation. These recent efforts involving numerical studies mainly focused on constrictor-type and segmented-type arc-heated wind tunnels, whereas there are currently relatively few studies on the Huels-type arc heater.…”

Section: Introductionmentioning

confidence: 99%

Plasma flow modeling for Huels-type arc heater with turbulent diffusion

et al. 2017

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In this study, we developed an analytical model for the flow field in the Huels-type arc-heated wind tunnel (L2K) of the German Aerospace Center. This flow-field model can be used to accurately reproduce the discharge behavior in the heating section and expansion in the nozzle section of L2K. It includes the radiation transport and turbulent flow, as well as thermochemical nonequilibrium models, which are tightly coupled with electric field calculations. In addition, we considered the turbulent diffusion model for the mass conservation of the species and performed numerical simulations for several cases with and without the turbulent diffusion model. Computations were used to obtain the general characteristics of an arc-heated flow containing an arc discharge and supersonic expansion. We verified that radiation and turbulence play important roles in the transfer of heat from the high-temperature core flow to the outer cold gas in the heating section of L2K. In addition, we performed parametric studies that involved varying the degree of turbulent diffusion. The results showed that turbulent diffusion has a large influence on the formation of the arc discharge in the heating section and on the enthalpy distribution at the nozzle exit.

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“…Some of their results have been compared to anode jet experimental data. A threedimensional unsteady simulation of NASA's Aerodynamic Heating Facility was performed by Sahai et al [29] using the Fully-Implicit Navier-Stokes (FIN-S) solver [16,17]. Their finite element solver included Joule heating, 3D radiative transfer, and non-equilibrium model for the plasma.…”

mentioning

confidence: 99%