A zonal characteristic boundary condition for simulations of aerodynamic sound
A zonal characteristic boundary condition for simulations of aerodynamic sound
This paper presents a non-reflecting boundary condition that significantly reduces the spurious pressure oscillations that are produced when vortical structures in a compressible flow cross the computational farfield boundaries. The method is based on commonly used characteristic boundary conditions. Here, incoming characteristics are ramped to zero in a buffer region as opposed to merely setting them to zero at the boundary. One of the key features of the approach is that it is free of coefficients requiring calibration. The equivalence of two formulations of the zonal boundary condition is verified with a model problem. Direct numerical simulations of trailing edges at different Mach numbers are conducted to demonstrate the effectiveness of the novel approach.
9090209700
European Community on Computational Methods in Applied Sciences
Sandberg, R.D.
41d03f60-5d12-4f2d-a40a-8ff89ef01cfa
Jones, L.E.
0a801680-fecd-400f-a771-b0ac1fcd02c6
Sandham, N.D.
0024d8cd-c788-4811-a470-57934fbdcf97
2006
Sandberg, R.D.
41d03f60-5d12-4f2d-a40a-8ff89ef01cfa
Jones, L.E.
0a801680-fecd-400f-a771-b0ac1fcd02c6
Sandham, N.D.
0024d8cd-c788-4811-a470-57934fbdcf97
Sandberg, R.D., Jones, L.E. and Sandham, N.D.
(2006)
A zonal characteristic boundary condition for simulations of aerodynamic sound.
Wesseling, P., Oñate, E. and Périaux, J.
(eds.)
In Proceedings of ECCOMAS CFD 2006, European Conference on Computational Fluid Dynamics.
European Community on Computational Methods in Applied Sciences..
Record type:
Conference or Workshop Item
(Paper)
Abstract
This paper presents a non-reflecting boundary condition that significantly reduces the spurious pressure oscillations that are produced when vortical structures in a compressible flow cross the computational farfield boundaries. The method is based on commonly used characteristic boundary conditions. Here, incoming characteristics are ramped to zero in a buffer region as opposed to merely setting them to zero at the boundary. One of the key features of the approach is that it is free of coefficients requiring calibration. The equivalence of two formulations of the zonal boundary condition is verified with a model problem. Direct numerical simulations of trailing edges at different Mach numbers are conducted to demonstrate the effectiveness of the novel approach.
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More information
Published date: 2006
Venue - Dates:
European Confernce on Computational Fluid Dynamics, ECCOMAS CFD 2006, Egmond aan Zee, The Netherlands, 2006-09-05 - 2006-09-08
Organisations:
Aerodynamics & Flight Mechanics
Identifiers
Local EPrints ID: 43638
URI: http://eprints.soton.ac.uk/id/eprint/43638
ISBN: 9090209700
PURE UUID: d0671d84-2673-4938-ba29-bdce052d6818
Catalogue record
Date deposited: 29 Jan 2007
Last modified: 17 Jan 2024 02:36
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Contributors
Author:
R.D. Sandberg
Author:
L.E. Jones
Author:
N.D. Sandham
Editor:
P. Wesseling
Editor:
E. Oñate
Editor:
J. Périaux
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