Development of an Unstructured Navier-Stokes Solver for Hypersonic Nonequilibrium Aerothermodynamics

Scalabrin, Leonardo; Boyd, Iain D.

doi:10.2514/6.2005-5203

Cited by 86 publications

(69 citation statements)

References 20 publications

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“…In this case, the second and third terms on the right hand side can be combined and an equivalent mean free path adopted as (9) to give the simpler form shown in Eq. 10.…”

Section: A = 2l 2rt (7)mentioning

confidence: 99%

Velocity Slip and Temperature Jump in Hypersonic Aerothermodynamics

Lofthouse

Scalabrin

Boyd

2007

45th AIAA Aerospace Sciences Meeting and Exhibit

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“…In this case, the second and third terms on the right hand side can be combined and an equivalent mean free path adopted as (9) to give the simpler form shown in Eq. 10.…”

Section: A = 2l 2rt (7)mentioning

confidence: 99%

Velocity Slip and Temperature Jump in Hypersonic Aerothermodynamics

Lofthouse

Scalabrin

Boyd

2007

45th AIAA Aerospace Sciences Meeting and Exhibit

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“…The continuum portion is simulated using the LeMANS code. 19 For the results presented in this article, it is assumed that rotational and translational energy modes can be described by a single temperature T . The vibrational energy mode is not considered.…”

Section: A Ns and Dsmc Solversmentioning

confidence: 99%

Hybrid Particle-Continuum Simulations of Non-Equilibrium Hypersonic Blunt Body Flow Fields

Schwartzentruber

Scalabrin

Boyd

2006

9th AIAA/ASME Joint Thermophysics and Heat Transfer Conference

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A modular particle-continuum (MPC) numerical method is presented which solves the Navier-Stokes (NS) equations in regions of near-equilibrium and uses the direct simulation Monte Carlo (DSMC) method where the flow is in non-equilibrium. The MPC method is designed specifically for steady-state, hypersonic, nonequilibrium flows and couples existing, state-of-the-art DSMC and NS solvers into a single modular code. The MPC method is tested for 2D flow of N 2 at various Mach numbers over a cylinder where the global Knudsen number is 0.01. For these conditions, NS simulations significantly over-predict the local shear-stress, and also over-predict the peak heating rate by 5-10% when compared with full DSMC simulations. DSMC also predicts faster wake closure and 10-15% higher temperatures in the immediate wake region. The MPC code is able to accurately reproduce DSMC flow field results, local velocity distributions, and surface properties up to 2.8 times faster than full DSMC simulations. The computational time saved by the MPC method is directly proportional to the fraction of the flow field which is in near-equilibrium. It is found that particle simulation of the shock interior is not necessary for accurate prediction of surface properties, however particle simulation of the boundary layer and near-wake region is.

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“…Translational-vibrational and vibrational-vibrational energy exchanges are then determined and coupled with an appropriate chemistry module. Among such CFD codes dedicated to the hypersonic regime are NASA's DPLR (Data-Parallel Line Relaxation from the National Aeronautics and Space Administration) [10], LAURA (Langley Aerothermodynamic Upwind Relaxation Algorithm) [11], VULCAN (Viscous Upwind aLgorithm for Complex flow ANalysis) [12], LeMANS (The Michigan Aerothermodynamic Navier-Stokes solver) [13,14], and US3D (UnStructured 3D) [15,16] from the University of Minnesota. For rarefied flow conditions, a DSMC solver called dsmcFoam has been developed and validated within the framework of the open-source CFD platform OpenFOAM [17] at the University of Strathclyde [18,19].…”

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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Development of an Unstructured Navier-Stokes Solver for Hypersonic Nonequilibrium Aerothermodynamics

Cited by 86 publications

References 20 publications

Velocity Slip and Temperature Jump in Hypersonic Aerothermodynamics

Velocity Slip and Temperature Jump in Hypersonic Aerothermodynamics

Hybrid Particle-Continuum Simulations of Non-Equilibrium Hypersonic Blunt Body Flow Fields

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

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