The influence of CO[sub 2] kinetics on the hypersonic flow near blunt bodies

Кустова, Е. В.; Нагнибеда, Е. А.; Shevelev, Yu. D.; Syzranova, N. G.

doi:10.1063/1.4769664

Cited by 2 publications

(4 citation statements)

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“…While only the slight influence of chemical reaction model on the heat transfer to the non-catalytic surface was found, near the fully catalytic surface this effect occurs more essential [15]. Recently a strong influence of a body shape on the gas parameters in a shock layer and heat fluxes to the surface was found in [37]. Now let us consider the state-to-state solution of a 1D boundary layer problem (see Eqs.…”

Section: Resultsmentioning

confidence: 99%

Vibrational-Chemical Kinetics in Mars Entry Problems

Kustova¹,

Нагнибеда²,

Armenise³

2014

TOPPJ

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The paper deals with kinetic theory methods modelling of reacting gas flows near spacecrafts entering the Mars atmosphere. For mixtures containing CO 2 molecules, the complete kinetic scheme including all vibrational energy transitions, dissociation, recombination and exchange chemical reactions is proposed. For the prediction of gas dynamic parameters and heat transfer to the surface of a spacecraft, a detailed approach taking into account state-to-state CO 2 vibrational and chemical kinetics as well as multi-temperature approaches based on quasi-stationary vibrational distributions are used. A more accurate but complicated and time consuming state-to-state model is applied for the numerical simulation of a one-dimensional flow in a boundary layer near the entering body surface. More simple quasistationary three-temperature, two-temperature and one-temperature approaches are used for the numerical study of a 2-D viscous shock layer under entry conditions. The vibrational distributions near the surface are far from the local vibrational and chemical equilibrium and a noticeable difference is found between the values of CO 2 vibrational-specific energies at the surface obtained by means of the state-to-state and quasi-stationary approaches. At the same time, for all considered approaches, the kinetic model for vibrational distributions and chemical reactions has a weak influence on the heat transfer to the non-catalytic vehicle surface.

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Section: Resultsmentioning

confidence: 99%

Vibrational-Chemical Kinetics in Mars Entry Problems

Kustova¹,

Нагнибеда²,

Armenise³

2014

TOPPJ

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“…Calculations of the convective heat flux and the non-equilibrium radiation were carried out of the MSRO vehicle entering into the Martian atmosphere [7][8][9][10][11][12][13][14][15][16][17][18][19].…”

Section: Advances In Some Hypersonic Vehicles Technologiesmentioning

confidence: 99%

“…[7,8]. If potentials of interaction between particles are defined, then the equations in terms of species densities, macroscopic velocity, and gas temperature can be carried out by methods of the kinetic theory of gases [9][10][11][12]. The transport theory of polyatomic gas mixtures taking into of account internal molecular structure, different rates of vibration, and non-harmonic transitions has been developed for a five component CO 2 /O 2 /CO/O/C mixture taking vibration excitation of molecules into account.…”

Section: Introductionmentioning

confidence: 99%

“…The governing equations with rigorous kinetic schemes for transport coefficients are solved numerically for a flow in a viscous shock layer near the blunt body imitating the form of the spacecraft Mars Sample Return Orbiter (MSRO) and MARS EXPRESS vehicles descending in an atmosphere of Mars for the conditions typical for the re-entering regime [9][10][11][12]. The form of considered vehicles represents spherically blunted cone with aт angle 120 and radius R = 1.0 m (MSRO) and R = 0.38 m (MARS EXPRESS) joined with the cylinder (Figure 1).…”

Section: Introductionmentioning

confidence: 99%

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Numerical Modeling of Hypersonic Aerodynamics and Heat Transfer Problems of the Martian Descent Modules

Shevelev¹

2018

Advances in Some Hypersonic Vehicles Technologies

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Computational fluid dynamics (CFD) is the important tool to analyze physics of fluids. Hypersonic flows over real space configurations represent a substantial problem from the point of view of the development of new and more effective mathematical models, numerical methods, and the use of computer systems. Governing equations for multicomponent, multi-temperature, chemically reacting non-equilibrium radiant mixtures are the mathematical foundation for the study of vehicles entering in Martian atmosphere. Based on the kinetic equations for the distribution functions, an efficient threetemperature model suitable for Mars re-entry applications derived and used for the simulations of a non-equilibrium flow in a viscous shock layer near a space vehicle. The closed self-consistent description of a flow in terms of densities of species, macroscopic velocity, gas temperature, and three vibration temperatures are proposed. The transport properties in dissociating CO 2 flows have been evaluated. The proposed model takes into account real structure of polyatomic CO 2 molecules, non-equilibrium CO 2 vibration excitation, different rates of various energy transitions, and chemical reactions. Numerical investigations of a flow past a frontal part of Mars Sample Return Orbiter (MSRO) and MARS EXPRESS vehicles descending in an atmosphere of Mars are presented. The radiation processes taking into account of non-equilibrium character are considered.

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The influence of CO[sub 2] kinetics on the hypersonic flow near blunt bodies

Cited by 2 publications

References 0 publications

Vibrational-Chemical Kinetics in Mars Entry Problems

Vibrational-Chemical Kinetics in Mars Entry Problems

Numerical Modeling of Hypersonic Aerodynamics and Heat Transfer Problems of the Martian Descent Modules

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