Towards a generalised lattice Boltzmann method for aerodynamic simulations
Towards a generalised lattice Boltzmann method for aerodynamic simulations
The conventional lattice Boltzmann method is restricted to Cartesian grids, making it remarkably expensive for capturing thin boundary layers, and therefore impractical for most relevant problems in aerodynamics. In this paper, a finite difference approach is taken to solve the discrete-velocity Boltzmann equation in generalised curvilinear coordinates to perform fluid flow simulations with non-uniform grids. The present method resolves large gradients in wall vicinity with fewer mesh elements, thereby leading to a reduction in computational effort. Two-dimensional flows at low Reynolds number over circular cylinder and NACA0012 aerofoil are specifically investigated to assess accuracy and performance of the proposed approach.
Curvilinear Coordinates, Finite Difference, Non-Uniform Grids
Reyes Barraza, Juan Antonio
5d754742-de9f-47e5-a5f1-10327f04d437
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314
1 September 2020
Reyes Barraza, Juan Antonio
5d754742-de9f-47e5-a5f1-10327f04d437
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314
Reyes Barraza, Juan Antonio and Deiterding, Ralf
(2020)
Towards a generalised lattice Boltzmann method for aerodynamic simulations.
Journal of Computational Science, 45, [101182].
(doi:10.1016/j.jocs.2020.101182).
Abstract
The conventional lattice Boltzmann method is restricted to Cartesian grids, making it remarkably expensive for capturing thin boundary layers, and therefore impractical for most relevant problems in aerodynamics. In this paper, a finite difference approach is taken to solve the discrete-velocity Boltzmann equation in generalised curvilinear coordinates to perform fluid flow simulations with non-uniform grids. The present method resolves large gradients in wall vicinity with fewer mesh elements, thereby leading to a reduction in computational effort. Two-dimensional flows at low Reynolds number over circular cylinder and NACA0012 aerofoil are specifically investigated to assess accuracy and performance of the proposed approach.
Text
paper_v5
- Accepted Manuscript
More information
Accepted/In Press date: 18 June 2020
e-pub ahead of print date: 26 June 2020
Published date: 1 September 2020
Keywords:
Curvilinear Coordinates, Finite Difference, Non-Uniform Grids
Identifiers
Local EPrints ID: 442223
URI: http://eprints.soton.ac.uk/id/eprint/442223
ISSN: 1877-7503
PURE UUID: f699e969-a963-48f0-a850-1c3c5844400f
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Date deposited: 09 Jul 2020 16:31
Last modified: 17 Mar 2024 05:43
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Author:
Juan Antonio Reyes Barraza
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