Modeling hypersonic entry with the fully-implicit navier-stokes (FIN-S) stabilized finite element flow solver

Benjamin S. Kirk; Roy H. Stogner; Paul T. Bauman; Todd A. Oliver

doi:10.1016/j.compfluid.2013.10.003

Modeling hypersonic entry with the fully-implicit navier-stokes (FIN-S) stabilized finite element flow solver

Benjamin S. Kirk, Roy H. Stogner, Paul T. Bauman, Todd A. Oliver

Research output: Contribution to journal › Article › peer-review

24 Scopus citations

Abstract

In this paper, we present a novel scheme for modeling the hypersonic atmospheric entry of large vehicles with an ablative thermal protection system. The Favre-averaged thermochemical nonequilibrium Navier-Stokes equations with Spalart-Allmaras turbulence closure, thermodynamic, chemical kinetic, and quasi-steady ablation model are presented. The numerical method is based on a streamline upwind Petrov-Galerkin (SUPG) stabilized finite element formulation. The formulation and implementation of the finite element approximation are discussed in detail. The performance of the scheme is investigated through a series of increasingly complex applications, culminating in the simulation of a three-dimensional ablating heatshield in transitioning flow.

Original language	English
Pages (from-to)	281-292
Number of pages	12
Journal	Computers and Fluids
Volume	92
DOIs	https://doi.org/10.1016/j.compfluid.2013.10.003
State	Published - Mar 20 2014
Externally published	Yes

Keywords

Compressible flow
Hypersonic flow
Reentry
Stabilized finite elements
Surface ablation

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10.1016/j.compfluid.2013.10.003

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title = "Modeling hypersonic entry with the fully-implicit navier-stokes (FIN-S) stabilized finite element flow solver",

abstract = "In this paper, we present a novel scheme for modeling the hypersonic atmospheric entry of large vehicles with an ablative thermal protection system. The Favre-averaged thermochemical nonequilibrium Navier-Stokes equations with Spalart-Allmaras turbulence closure, thermodynamic, chemical kinetic, and quasi-steady ablation model are presented. The numerical method is based on a streamline upwind Petrov-Galerkin (SUPG) stabilized finite element formulation. The formulation and implementation of the finite element approximation are discussed in detail. The performance of the scheme is investigated through a series of increasingly complex applications, culminating in the simulation of a three-dimensional ablating heatshield in transitioning flow.",

keywords = "Compressible flow, Hypersonic flow, Reentry, Stabilized finite elements, Surface ablation",

author = "Kirk, {Benjamin S.} and Stogner, {Roy H.} and Bauman, {Paul T.} and Oliver, {Todd A.}",

note = "Funding Information: The authors express their sincere gratitude for the many enjoyable collaborations with the late Graham Carey related to this work. The authors also acknowledge Steve Bova of Sandia National Labs for many fruitful discussions. This material is based upon work supported by the Department of Energy [National Nuclear Security Administration] under Award Number [DE-FC52-08NA28615]; this support is gratefully acknowledged.",

year = "2014",

month = mar,

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doi = "10.1016/j.compfluid.2013.10.003",

language = "English",

volume = "92",

pages = "281--292",

journal = "Computers and Fluids",

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T1 - Modeling hypersonic entry with the fully-implicit navier-stokes (FIN-S) stabilized finite element flow solver

AU - Kirk, Benjamin S.

AU - Stogner, Roy H.

AU - Bauman, Paul T.

AU - Oliver, Todd A.

N1 - Funding Information: The authors express their sincere gratitude for the many enjoyable collaborations with the late Graham Carey related to this work. The authors also acknowledge Steve Bova of Sandia National Labs for many fruitful discussions. This material is based upon work supported by the Department of Energy [National Nuclear Security Administration] under Award Number [DE-FC52-08NA28615]; this support is gratefully acknowledged.

PY - 2014/3/20

Y1 - 2014/3/20

N2 - In this paper, we present a novel scheme for modeling the hypersonic atmospheric entry of large vehicles with an ablative thermal protection system. The Favre-averaged thermochemical nonequilibrium Navier-Stokes equations with Spalart-Allmaras turbulence closure, thermodynamic, chemical kinetic, and quasi-steady ablation model are presented. The numerical method is based on a streamline upwind Petrov-Galerkin (SUPG) stabilized finite element formulation. The formulation and implementation of the finite element approximation are discussed in detail. The performance of the scheme is investigated through a series of increasingly complex applications, culminating in the simulation of a three-dimensional ablating heatshield in transitioning flow.

AB - In this paper, we present a novel scheme for modeling the hypersonic atmospheric entry of large vehicles with an ablative thermal protection system. The Favre-averaged thermochemical nonequilibrium Navier-Stokes equations with Spalart-Allmaras turbulence closure, thermodynamic, chemical kinetic, and quasi-steady ablation model are presented. The numerical method is based on a streamline upwind Petrov-Galerkin (SUPG) stabilized finite element formulation. The formulation and implementation of the finite element approximation are discussed in detail. The performance of the scheme is investigated through a series of increasingly complex applications, culminating in the simulation of a three-dimensional ablating heatshield in transitioning flow.

KW - Compressible flow

KW - Hypersonic flow

KW - Reentry

KW - Stabilized finite elements

KW - Surface ablation

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U2 - 10.1016/j.compfluid.2013.10.003

DO - 10.1016/j.compfluid.2013.10.003

M3 - Article

AN - SCOPUS:84893539855

SN - 0045-7930

VL - 92

SP - 281

EP - 292

JO - Computers and Fluids

JF - Computers and Fluids

ER -

Modeling hypersonic entry with the fully-implicit navier-stokes (FIN-S) stabilized finite element flow solver

Abstract

Keywords

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