Numerical simulation of compressible turbulent flow via improved gas-kinetic BGK scheme

Shengwei Xiong; Chengwen Zhong; Congshan Zhuo; Kai Li; Xiaopeng Chen; Jun Cao

doi:10.1002/fld.2449

Numerical simulation of compressible turbulent flow via improved gas-kinetic BGK scheme

Shengwei Xiong, Chengwen Zhong, Congshan Zhuo, Kai Li, Xiaopeng Chen, Jun Cao

School of Aeronautics

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

22 Scopus citations

Abstract

In order to solve compressible turbulent flow problems, this study focuses on incorporating the Spalart-Allmaras turbulence model into gas-kinetic BGK (Bhatnagar-Gross-Krook) scheme. The Spalart-Allmaras turbulence model is solved using finite difference discretization. The variables on the cell interface are interpolated via the van Leer limiter in the reconstruction stage. Simulation of subsonic and transonic flow over a NACA0012 airfoil has been implemented using two-dimensional body-fitted grids. The numerical results obtained appear in good agreement with the AGARD results, demonstrating the effectiveness and usefulness of the strategy of coupling the Spalart-Allmaras turbulence model with the BGK scheme for compressible turbulent flow simulation.

Original language	English
Pages (from-to)	1833-1847
Number of pages	15
Journal	International Journal for Numerical Methods in Fluids
Volume	67
Issue number	12
DOIs	https://doi.org/10.1002/fld.2449
State	Published - 30 Dec 2011

Keywords

Compressible turbulent flow
Gas-kinetic BGK scheme
NACA0012 airfoil
Spalart-Allmaras model

Access to Document

10.1002/fld.2449

Cite this

@article{088ef49d02094ff793316eb99a4c931c,

title = "Numerical simulation of compressible turbulent flow via improved gas-kinetic BGK scheme",

abstract = "In order to solve compressible turbulent flow problems, this study focuses on incorporating the Spalart-Allmaras turbulence model into gas-kinetic BGK (Bhatnagar-Gross-Krook) scheme. The Spalart-Allmaras turbulence model is solved using finite difference discretization. The variables on the cell interface are interpolated via the van Leer limiter in the reconstruction stage. Simulation of subsonic and transonic flow over a NACA0012 airfoil has been implemented using two-dimensional body-fitted grids. The numerical results obtained appear in good agreement with the AGARD results, demonstrating the effectiveness and usefulness of the strategy of coupling the Spalart-Allmaras turbulence model with the BGK scheme for compressible turbulent flow simulation.",

keywords = "Compressible turbulent flow, Gas-kinetic BGK scheme, NACA0012 airfoil, Spalart-Allmaras model",

author = "Shengwei Xiong and Chengwen Zhong and Congshan Zhuo and Kai Li and Xiaopeng Chen and Jun Cao",

year = "2011",

month = dec,

day = "30",

doi = "10.1002/fld.2449",

language = "英语",

volume = "67",

pages = "1833--1847",

journal = "International Journal for Numerical Methods in Fluids",

issn = "0271-2091",

publisher = "John Wiley and Sons Ltd",

number = "12",

}

TY - JOUR

T1 - Numerical simulation of compressible turbulent flow via improved gas-kinetic BGK scheme

AU - Xiong, Shengwei

AU - Zhong, Chengwen

AU - Zhuo, Congshan

AU - Li, Kai

AU - Chen, Xiaopeng

AU - Cao, Jun

PY - 2011/12/30

Y1 - 2011/12/30

N2 - In order to solve compressible turbulent flow problems, this study focuses on incorporating the Spalart-Allmaras turbulence model into gas-kinetic BGK (Bhatnagar-Gross-Krook) scheme. The Spalart-Allmaras turbulence model is solved using finite difference discretization. The variables on the cell interface are interpolated via the van Leer limiter in the reconstruction stage. Simulation of subsonic and transonic flow over a NACA0012 airfoil has been implemented using two-dimensional body-fitted grids. The numerical results obtained appear in good agreement with the AGARD results, demonstrating the effectiveness and usefulness of the strategy of coupling the Spalart-Allmaras turbulence model with the BGK scheme for compressible turbulent flow simulation.

AB - In order to solve compressible turbulent flow problems, this study focuses on incorporating the Spalart-Allmaras turbulence model into gas-kinetic BGK (Bhatnagar-Gross-Krook) scheme. The Spalart-Allmaras turbulence model is solved using finite difference discretization. The variables on the cell interface are interpolated via the van Leer limiter in the reconstruction stage. Simulation of subsonic and transonic flow over a NACA0012 airfoil has been implemented using two-dimensional body-fitted grids. The numerical results obtained appear in good agreement with the AGARD results, demonstrating the effectiveness and usefulness of the strategy of coupling the Spalart-Allmaras turbulence model with the BGK scheme for compressible turbulent flow simulation.

KW - Compressible turbulent flow

KW - Gas-kinetic BGK scheme

KW - NACA0012 airfoil

KW - Spalart-Allmaras model

UR - http://www.scopus.com/inward/record.url?scp=80355139897&partnerID=8YFLogxK

U2 - 10.1002/fld.2449

DO - 10.1002/fld.2449

M3 - 文章

AN - SCOPUS:80355139897

SN - 0271-2091

VL - 67

SP - 1833

EP - 1847

JO - International Journal for Numerical Methods in Fluids

JF - International Journal for Numerical Methods in Fluids

IS - 12

ER -

Numerical simulation of compressible turbulent flow via improved gas-kinetic BGK scheme

Abstract

Keywords

Access to Document

Other files and links

Fingerprint

Cite this