Examination of Coupled Continnum Fluid Dynamics and Radiation in Hypersonic Simulations

Feldick, Andrew; Modest, Michael F.; Levin, Deborah A.; Gno, P.; Johnston, Christopher O.

doi:10.2514/6.2009-475

Cited by 12 publications

(14 citation statements)

References 25 publications

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“…Nevertheless, the present result is comparable to the numerical value of 24,000 K by Oylnick et al [2]. The vibrational relaxation phenomenon associated with the collision process is also correctly duplicated by the computational simulations by comparison with results in literature [2][3][4][5]. The results show that the vibrational temperatures equilibrate with translational mode toward the stagnation point by the isothermal condition of all excited chemical species.…”

Section: Three-dimensional Simulation At 8 Degsupporting

confidence: 91%

“…Aerothermodynamic computational analyses of the Stardust capsule have been carried out by several investigations in the past years [2][3][4][5][6][7]. The present investigation continues these efforts for improving the interdisciplinary computational capability with increased physical fidelity by duplicating the flight-test condition at an angle of attack.…”

Section: Introductionmentioning

confidence: 96%

“…Solving thermal radiation heat transfer problems associated with reentry space vehicles requires the coupling of aerodynamics, chemical kinetics, and quantum physics [4,5]. In practical applications, a classification of the problems into Martian/orbital Earth entry and Earth superorbital entry can further focus the required scientific disciplines.…”

Section: Introductionmentioning

confidence: 99%

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Coupled Radiation-Gasdynamic Model for Stardust Earth Entry Simulation

Суржиков¹,

Shang²

2012

Journal of Spacecraft and Rockets

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A three-dimensional radiative aerodynamic computational simulation has been accomplished for the thermodynamically and chemically nonequilibrium flowfield around the Stardust sample return capsule at an angle of attack. In the early phase of study, the axisymmetric computations using the half-moment method indicate a significant radiative-gasdynamic interaction at high-altitude stages of the reentry trajectory. The radiative heating of the space capsule is studied again according to the preentry trajectory simulation of NASA duplicating the flight condition at an angle of attack of 8 deg. The three-dimensional radiative heat transfer is generated by a spectral multigroup ray-tracing method including the most dominant radiative mechanisms of absorption and emission. The computational results agree very well with data in literature and bring new insights into the interdisciplinary fluid dynamics phenomenon. Nomenclature a j;n , b jn = stoichiometric coefficients of the reaction c p;i , h i = specific heat capacity at constant pressure and specific enthalpy D i = effective diffusion coefficient of species e v;m = specific vibrational energy of m mode J b;! r = blackbody spectral intensity (the Planck function) J ! r;= spectral intensity of heat radiation k f;n , k r;n = rate constants of the forward and reverse reactions ! r = spectral absorption coefficient M i = molecular weight of species p, = pressure and density Q ! r = spectral emission source Q vib = energy source due to vibrational relaxation r = radius-vector of current spatial point S n f;j , S n r;j = rates of the forward and reverse reactions T = translational temperature T V;m = vibrational temperature for m mode of species t = time _ w i = reaction rate for species W j = formation rate for species Vu; v; w = velocity X i = chemical symbol of reactants and products Y i , x i = mass and molar fraction of species , = viscosity and heat conductivity coefficients i , J i = density and mass diffusion flux for species, J i D i grad Y i im = density of species having m mode of vibration = dissipative function = unit vector of solid angle

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Section: Three-dimensional Simulation At 8 Degsupporting

confidence: 91%

Section: Introductionmentioning

confidence: 96%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Coupled Radiation-Gasdynamic Model for Stardust Earth Entry Simulation

Суржиков¹,

Shang²

2012

Journal of Spacecraft and Rockets

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“…The need for reliable numerical tools that can capture thermochemical non-equilibrium with high-fidelity has gained momentum recently, principally due to NASA's upcoming critical missions involving the next Crew Exploration Vehicle, Orion, 3 and complex systems to allow high-mass payload entries in the Martian atmosphere.…”

Section: Introductionmentioning

confidence: 99%

Development of a Two-Temperature Open-Source CFD Model for Hypersonic Reacting Flows

Casseau¹,

Scanlon²,

Brown³

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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This version is available at https://strathprints.strath.ac.uk/55053/ Strathprints is designed to allow users to access the research output of the University of Strathclyde. Unless otherwise explicitly stated on the manuscript, Copyright © and Moral Rights for the papers on this site are retained by the individual authors and/or other copyright owners. Please check the manuscript for details of any other licences that may have been applied. You may not engage in further distribution of the material for any profitmaking activities or any commercial gain. You may freely distribute both the url (https://strathprints.strath.ac.uk/) and the content of this paper for research or private study, educational, or not-for-profit purposes without prior permission or charge.Any correspondence concerning this service should be sent to the Strathprints administrator: strathprints@strath.ac.ukThe Strathprints institutional repository (https://strathprints.strath.ac.uk) is a digital archive of University of Strathclyde research outputs. It has been developed to disseminate open access research outputs, expose data about those outputs, and enable the management and persistent access to Strathclyde's intellectual output. Development of a Two-Temperature Open-Source CFD Model for Hypersonic Reacting FlowsVincent Casseau * , Thomas J. Scanlon † and Richard E. Brown ‡ University of Strathclyde, Glasgow, G1 1XJ, UKThe highly complex flow physics that characterise re-entry conditions have to be reproduced by means of numerical simulations with both an acceptable level of accuracy and within reasonable timescales. In this respect, a new CFD solver, hyFoam, has been developed within the framework of the open-source CFD platform OpenFOAM for modelling hypersonic reacting flows. hyFoam has been successfully validated for two 0-degree adiabatic heat bath test cases and the limitations of a one-temperature CFD model have been highlighted. To cope with high-temperature gas chemistry, the internal energy has been decomposed into its elementary energy modes, thus introducing the translational-rotational and the vibrational temperatures. A two-temperature CFD model is being implemented in order to attain a better agreement between CFD and DSMC results. Validation of the code for a single species has been executed while mixture-related libraries are currently being developed. The vibrational-translational relaxation time formulation has also been presented and discussed.

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“…The study of high-speed vehicles re-entering the Earth's atmosphere is of current interest as witnessed by the ongoing tests on the Orion capsule (see Figure 1a) [1,2]. Access to space continues to be a challenging area with significant economic and scientific implications in the near-future for the leading countries.…”

Section: Introductionmentioning

confidence: 99%

A Two-Temperature Open-Source CFD Model for Hypersonic Reacting Flows, Part One: Zero-Dimensional Analysis

et al. 2016

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A two-temperature CFD (computational fluid dynamics) solver is a prerequisite to any spacecraft re-entry numerical study that aims at producing results with a satisfactory level of accuracy within realistic timescales. In this respect, a new two-temperature CFD solver, hy2Foam, has been developed within the framework of the open-source CFD platform OpenFOAM for the prediction of hypersonic reacting flows. This solver makes the distinct juncture between the trans-rotational and multiple vibrational-electronic temperatures. hy2Foam has the capability to model vibrational-translational and vibrational-vibrational energy exchanges in an eleven-species air mixture. It makes use of either the Park TTv model or the coupled vibration-dissociation-vibration (CVDV) model to handle chemistry-vibration coupling and it can simulate flows with or without electronic energy. Verification of the code for various zero-dimensional adiabatic heat baths of progressive complexity has been carried out. hy2Foam has been shown to produce results in good agreement with those given by the CFD code LeMANS (The Michigan Aerothermodynamic Navier-Stokes solver) and previously published data. A comparison is also performed with the open-source DSMC (direct simulation Monte Carlo) code dsmcFoam. It has been demonstrated that the use of the CVDV model and rates derived from Quantum-Kinetic theory promote a satisfactory consistency between the CFD and DSMC chemistry modules.

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Examination of Coupled Continnum Fluid Dynamics and Radiation in Hypersonic Simulations

Cited by 12 publications

References 25 publications

Coupled Radiation-Gasdynamic Model for Stardust Earth Entry Simulation

Coupled Radiation-Gasdynamic Model for Stardust Earth Entry Simulation

Development of a Two-Temperature Open-Source CFD Model for Hypersonic Reacting Flows

A Two-Temperature Open-Source CFD Model for Hypersonic Reacting Flows, Part One: Zero-Dimensional Analysis

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