Multigrid computation of flow past airfoil using k-ε turbulence model

Yong Zhao, Damodaran Murali

Research output: Contribution to journalArticle

1 Citation (Scopus)

Abstract

A method for calculating compressible turbulent flows around an airfoil is presented. A modified low-Reynolds-number k-ε turbulence mode is used in the method to predict turbulent flows. The model is incorporated in a Navier-Stokes flow solver that is based on the cell-centered finite-volume method and Runge-Kutta multistage time-stepping scheme. Linear upwinding is used to specify the far-field boundary conditions for the turbulence transport equations. A limited amount of nonlinear numerical dissipation is introduced to ensure stable and converged results, but care is taken to ensure that the artificial viscosity is much smaller than the physical viscosity. Multigrid algorithm, implicit residual smoothing and local time stepping are used to achieve faster convergence of numerical solutions. Computational results for flows around a NACA 0012 airfoil are presented and discussed. Pressure distribution on the airfoil surface is compared with the corresponding measurement and good agreement is observed. Techniques that are used for solving the k and ε equations for stable and fast convergence are also presented and discussed.

Original languageEnglish
Pages (from-to)180-188
Number of pages9
JournalJournal of Aerospace Engineering
Volume8
Issue number4
DOIs
Publication statusPublished - 1995
Externally publishedYes

Fingerprint

Turbulence models
Airfoils
Turbulent flow
Turbulence
Viscosity
Finite volume method
Pressure distribution
Reynolds number
Boundary conditions

ASJC Scopus subject areas

  • Aerospace Engineering
  • Civil and Structural Engineering
  • Mechanical Engineering
  • Materials Science(all)
  • Engineering(all)

Cite this

Multigrid computation of flow past airfoil using k-ε turbulence model. / Zhao, Yong; Murali, Damodaran.

In: Journal of Aerospace Engineering, Vol. 8, No. 4, 1995, p. 180-188.

Research output: Contribution to journalArticle

@article{e313e30bb6614313b539a6527f3836a7,
title = "Multigrid computation of flow past airfoil using k-ε turbulence model",
abstract = "A method for calculating compressible turbulent flows around an airfoil is presented. A modified low-Reynolds-number k-ε turbulence mode is used in the method to predict turbulent flows. The model is incorporated in a Navier-Stokes flow solver that is based on the cell-centered finite-volume method and Runge-Kutta multistage time-stepping scheme. Linear upwinding is used to specify the far-field boundary conditions for the turbulence transport equations. A limited amount of nonlinear numerical dissipation is introduced to ensure stable and converged results, but care is taken to ensure that the artificial viscosity is much smaller than the physical viscosity. Multigrid algorithm, implicit residual smoothing and local time stepping are used to achieve faster convergence of numerical solutions. Computational results for flows around a NACA 0012 airfoil are presented and discussed. Pressure distribution on the airfoil surface is compared with the corresponding measurement and good agreement is observed. Techniques that are used for solving the k and ε equations for stable and fast convergence are also presented and discussed.",
author = "Yong Zhao and Damodaran Murali",
year = "1995",
doi = "10.1061/(ASCE)0893-1321(1995)8:4(180)",
language = "English",
volume = "8",
pages = "180--188",
journal = "Journal of Aerospace Engineering",
issn = "0893-1321",
publisher = "American Society of Civil Engineers (ASCE)",
number = "4",

}

TY - JOUR

T1 - Multigrid computation of flow past airfoil using k-ε turbulence model

AU - Zhao, Yong

AU - Murali, Damodaran

PY - 1995

Y1 - 1995

N2 - A method for calculating compressible turbulent flows around an airfoil is presented. A modified low-Reynolds-number k-ε turbulence mode is used in the method to predict turbulent flows. The model is incorporated in a Navier-Stokes flow solver that is based on the cell-centered finite-volume method and Runge-Kutta multistage time-stepping scheme. Linear upwinding is used to specify the far-field boundary conditions for the turbulence transport equations. A limited amount of nonlinear numerical dissipation is introduced to ensure stable and converged results, but care is taken to ensure that the artificial viscosity is much smaller than the physical viscosity. Multigrid algorithm, implicit residual smoothing and local time stepping are used to achieve faster convergence of numerical solutions. Computational results for flows around a NACA 0012 airfoil are presented and discussed. Pressure distribution on the airfoil surface is compared with the corresponding measurement and good agreement is observed. Techniques that are used for solving the k and ε equations for stable and fast convergence are also presented and discussed.

AB - A method for calculating compressible turbulent flows around an airfoil is presented. A modified low-Reynolds-number k-ε turbulence mode is used in the method to predict turbulent flows. The model is incorporated in a Navier-Stokes flow solver that is based on the cell-centered finite-volume method and Runge-Kutta multistage time-stepping scheme. Linear upwinding is used to specify the far-field boundary conditions for the turbulence transport equations. A limited amount of nonlinear numerical dissipation is introduced to ensure stable and converged results, but care is taken to ensure that the artificial viscosity is much smaller than the physical viscosity. Multigrid algorithm, implicit residual smoothing and local time stepping are used to achieve faster convergence of numerical solutions. Computational results for flows around a NACA 0012 airfoil are presented and discussed. Pressure distribution on the airfoil surface is compared with the corresponding measurement and good agreement is observed. Techniques that are used for solving the k and ε equations for stable and fast convergence are also presented and discussed.

UR - http://www.scopus.com/inward/record.url?scp=0029394179&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=0029394179&partnerID=8YFLogxK

U2 - 10.1061/(ASCE)0893-1321(1995)8:4(180)

DO - 10.1061/(ASCE)0893-1321(1995)8:4(180)

M3 - Article

AN - SCOPUS:0029394179

VL - 8

SP - 180

EP - 188

JO - Journal of Aerospace Engineering

JF - Journal of Aerospace Engineering

SN - 0893-1321

IS - 4

ER -