Écoulement hors d'équilibre chimique et vibrationnel dans une tuyère hypersonique axisymétrique

Haoui, Rabah; Gahmousse, Abderrahmane; Zeitoun, D.

doi:10.1016/s1290-0729(01)01265-0

Cited by 8 publications

(2 citation statements)

References 3 publications

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“…Although several modelling studies have been conducted on ICPs in conditions close to those studied in this work, only a few [10,11] include the modelling of an RF induction torch, a converging-diverging duct and a free expansion zone. The attention of most authors has been devoted either to the induction zone, where plasma is generated by assuming LTE [12][13][14][15][16][17][18][19][20] and non-LTE conditions [21][22][23][24][25][26][27][28][29], or to the characteristics of the jet at the exit of the convergentdivergent nozzle, neglecting the effect of the plasma coupling of the electromagnetic and aerodynamic fields and assuming LTE [30][31][32][33] or taking into account the deviation from LTE [5,[34][35][36][37][38][39][40][41][42]. The advantage of these numerical models is that they give detailed information on the characteristics of the jet at the exit of the plasma torch.…”

Section: Introductionmentioning

confidence: 99%

Chemical non-equilibrium modelling of an argon–oxygen supersonic ICP

Morsli¹,

Proulx²,

Gravelle³

2011

Plasma Sources Sci. Technol.

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In this paper, a non-equilibrium mathematical model for an argon-oxygen inductively coupled plasma (ICP) torch with a supersonic nozzle is developed without making chemical equilibrium assumptions. Reaction rates of dissociation and recombination of diatomic gas and ionization are taken into account. Higher-order approximations of the Chapman-Enskog method are used to obtain better accuracy for transport properties, taking advantage of the most recent sets of collision integrals available in the literature.In order to validate the developed model, results are compared qualitatively and quantitatively with existing experimental data. The calculated results for the axial temperature profile for pure argon less than 10 mm above the substrate are in good agreement with spectroscopic measurements.

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Section: Introductionmentioning

confidence: 99%

Chemical non-equilibrium modelling of an argon–oxygen supersonic ICP

Morsli¹,

Proulx²,

Gravelle³

2011

Plasma Sources Sci. Technol.

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“…The infinite conditions of the flow are those of the atmosphere at a given altitude. In addition, it is necessary to take into account the air under a non-equilibrium state at the exit of a nozzle (Haoui at al., 2001 (Haoui et al, 2001). …”

Section: Introductionmentioning

confidence: 99%

Finite Volume Analysis of a Supersonic Non-Equilibrium Flow Around an Axisymmetric Blunt Body

Haoui¹

2010

International Journal of Aeronautical and Space Sciences

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The aim of this work is to analyze high temperature flows around an axisymmetric blunt body taking into account chemical and vibrational non-equilibrium state for air mixture species. For this purpose, a finite volume methodology is employed to determine the supersonic flow parameters around the axisymmetric blunt body. This allows the capture of a shock wave before a blunt body placed in supersonic free stream. The numerical technique uses the flux vector splitting method of Van Leer. Here, adequate time stepping parameters, along with Courant, Friedrich, Lewis coefficient and mesh size level are selected to ensure numerical convergence, sought with an order of 10

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Physico-chemical state of the air at the stagnation point during the atmospheric reentry of a spacecraft

Haoui

2011

Acta Astronautica

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Hypersonic flows around spatial vehicles during their reentry phase in planetary atmospheres are characterized by intense aerothermal phenomena. The aim of this work is to analyze high temperature flows around an axisymmetric blunt body taking into account chemical and vibrational non-equilibrium for air mixture species. For this purpose, a finite volume methodology is employed to determine the supersonic flow parameters around the axisymmetric blunt body, especially at the stagnation point and along the wall of spacecraft for several altitudes. This allows the capture shock wave before a blunt body placed in supersonic free stream. The numerical technique uses the Flux Vector Splitting method of Van Leer. Here, adequate time stepping parameter, along with CFL coefficient and mesh size level are selected to ensure numerical convergence, sought with an order of .

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Écoulement hors d'équilibre chimique et vibrationnel dans une tuyère hypersonique axisymétrique

Cited by 8 publications

References 3 publications

Chemical non-equilibrium modelling of an argon–oxygen supersonic ICP

Chemical non-equilibrium modelling of an argon–oxygen supersonic ICP

Finite Volume Analysis of a Supersonic Non-Equilibrium Flow Around an Axisymmetric Blunt Body

Physico-chemical state of the air at the stagnation point during the atmospheric reentry of a spacecraft

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