Reynolds averaged navier-stokes flow computation of RAE2822 airfoil using gas-kinetic BGK Scheme

Reynolds averaged navier-stokes flow computation of RAE2822 airfoil using gas-kinetic BGK Scheme

In this paper, a gas-kinetic solver is developed to solve Reynolds Averaged Navier-Stokes (RANS) equations in two-space dimensions generalized coordinates. The convection flux terms which appear on the left hand side of the RANS equations are discretized by a semi-discrete finite difference method....

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Main Authors: Ong, Jiunn Chit, Omar, Ashraf Ali E., Asrar, Waqar
Format: Conference or Workshop Item
Language:English
Published: 2009
Subjects:
TL500 Aeronautics
Online Access:http://irep.iium.edu.my/6041/
http://irep.iium.edu.my/6041/
http://irep.iium.edu.my/6041/1/IMECS2009_pp2179-2183.pdf
id iium-6041
recordtype eprints
spelling iium-60412011-11-21T21:24:42Z http://irep.iium.edu.my/6041/ Reynolds averaged navier-stokes flow computation of RAE2822 airfoil using gas-kinetic BGK Scheme Ong, Jiunn Chit Omar, Ashraf Ali E. Asrar, Waqar TL500 Aeronautics In this paper, a gas-kinetic solver is developed to solve Reynolds Averaged Navier-Stokes (RANS) equations in two-space dimensions generalized coordinates. The convection flux terms which appear on the left hand side of the RANS equations are discretized by a semi-discrete finite difference method. Then, the resulting inviscid flux functions are approximated by gas-kinetic BGK scheme which is based on the BGK model of the approximate collisional Boltzmann equation. The cell interface values required by the inviscid flux functions are reconstructed to second-order spatial accuracy via the MUSCL (Monotone Upstream-Centered Schemes for Conservation Laws) variable interpolation method coupled with a minmod limiter. As for the diffusion flux terms, they are discretized by a second-order central difference scheme. To account for the turbulence effect, a combined k-ε / k-ω SST (Shear-Stress Transport) two-equation turbulence model is used in the solver. An explicit-type time integration method known as the modified fourth-order Runge-Kutta method is used to march the solution to steady-state. Computation over the RAE2822 airfoil flow corresponding to transonic speed has been solved using the developed gas-kinetic solver. Accuracy of BGK scheme in solving viscous transonic turbulent flow over the airfoil will be examined. Results obtained from the computations are also compared with experimental data and will demonstrate that a very good agreement has been achieved. 2009-03 Conference or Workshop Item PeerReviewed application/pdf en http://irep.iium.edu.my/6041/1/IMECS2009_pp2179-2183.pdf Ong, Jiunn Chit and Omar, Ashraf Ali E. and Asrar, Waqar (2009) Reynolds averaged navier-stokes flow computation of RAE2822 airfoil using gas-kinetic BGK Scheme. In: International MultiConference of Engineers and Computer Scientists (IMECS), 18 - 20 March 2009, Hong Kong. http://www.iaeng.org/IMECS2009/
repository_type Digital Repository
institution_category Local University
institution International Islamic University Malaysia
building IIUM Repository
collection Online Access
language English
topic TL500 Aeronautics
spellingShingle TL500 Aeronautics
Ong, Jiunn Chit
Omar, Ashraf Ali E.
Asrar, Waqar
Reynolds averaged navier-stokes flow computation of RAE2822 airfoil using gas-kinetic BGK Scheme
description In this paper, a gas-kinetic solver is developed to solve Reynolds Averaged Navier-Stokes (RANS) equations in two-space dimensions generalized coordinates. The convection flux terms which appear on the left hand side of the RANS equations are discretized by a semi-discrete finite difference method. Then, the resulting inviscid flux functions are approximated by gas-kinetic BGK scheme which is based on the BGK model of the approximate collisional Boltzmann equation. The cell interface values required by the inviscid flux functions are reconstructed to second-order spatial accuracy via the MUSCL (Monotone Upstream-Centered Schemes for Conservation Laws) variable interpolation method coupled with a minmod limiter. As for the diffusion flux terms, they are discretized by a second-order central difference scheme. To account for the turbulence effect, a combined k-ε / k-ω SST (Shear-Stress Transport) two-equation turbulence model is used in the solver. An explicit-type time integration method known as the modified fourth-order Runge-Kutta method is used to march the solution to steady-state. Computation over the RAE2822 airfoil flow corresponding to transonic speed has been solved using the developed gas-kinetic solver. Accuracy of BGK scheme in solving viscous transonic turbulent flow over the airfoil will be examined. Results obtained from the computations are also compared with experimental data and will demonstrate that a very good agreement has been achieved.
format Conference or Workshop Item
author Ong, Jiunn Chit
Omar, Ashraf Ali E.
Asrar, Waqar
author_facet Ong, Jiunn Chit
Omar, Ashraf Ali E.
Asrar, Waqar
author_sort Ong, Jiunn Chit
title Reynolds averaged navier-stokes flow computation of RAE2822 airfoil using gas-kinetic BGK Scheme
title_short Reynolds averaged navier-stokes flow computation of RAE2822 airfoil using gas-kinetic BGK Scheme
title_full Reynolds averaged navier-stokes flow computation of RAE2822 airfoil using gas-kinetic BGK Scheme
title_fullStr Reynolds averaged navier-stokes flow computation of RAE2822 airfoil using gas-kinetic BGK Scheme
title_full_unstemmed Reynolds averaged navier-stokes flow computation of RAE2822 airfoil using gas-kinetic BGK Scheme
title_sort reynolds averaged navier-stokes flow computation of rae2822 airfoil using gas-kinetic bgk scheme
publishDate 2009
url http://irep.iium.edu.my/6041/
http://irep.iium.edu.my/6041/
http://irep.iium.edu.my/6041/1/IMECS2009_pp2179-2183.pdf
first_indexed 2023-09-18T20:14:52Z
last_indexed 2023-09-18T20:14:52Z
_version_ 1777407720470609920

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