Response surface model evolution
Response surface model evolution
Methods are presented for reducing time and effort when performing aerodynamic optimisation using response surface models. Significant time savings are made possible by monitoring the convergence of computational fluid dynamics simulations and omitting regions of poor designs. In so doing, optimal regions of the design space can be highlighted and surface refinement commenced early in the convergence of the design point set. A strategy employing surface updates with new data at points of maximum expected improvement is shown to perform more efficiently than reducing the design space to the region of the optimum. The response surface evolution methods are demonstrated through an example two parameter optimisation of a flap track fairing on a commercial airliner wing.
Forrester, Alexander I.J.
176bf191-3fc2-46b4-80e0-9d9a0cd7a572
Bressloff, Neil W.
4f531e64-dbb3-41e3-a5d3-e6a5a7a77c92
Keane, Andy J.
26d7fa33-5415-4910-89d8-fb3620413def
June 2003
Forrester, Alexander I.J.
176bf191-3fc2-46b4-80e0-9d9a0cd7a572
Bressloff, Neil W.
4f531e64-dbb3-41e3-a5d3-e6a5a7a77c92
Keane, Andy J.
26d7fa33-5415-4910-89d8-fb3620413def
Forrester, Alexander I.J., Bressloff, Neil W. and Keane, Andy J.
(2003)
Response surface model evolution.
16th AIAA Computational Fluid Dynamics Conference, Orlando, USA.
21 - 27 Jun 2003.
9 pp
.
Record type:
Conference or Workshop Item
(Paper)
Abstract
Methods are presented for reducing time and effort when performing aerodynamic optimisation using response surface models. Significant time savings are made possible by monitoring the convergence of computational fluid dynamics simulations and omitting regions of poor designs. In so doing, optimal regions of the design space can be highlighted and surface refinement commenced early in the convergence of the design point set. A strategy employing surface updates with new data at points of maximum expected improvement is shown to perform more efficiently than reducing the design space to the region of the optimum. The response surface evolution methods are demonstrated through an example two parameter optimisation of a flap track fairing on a commercial airliner wing.
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RSMevolution.pdf
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Published date: June 2003
Additional Information:
Paper: AIAA 2003-4089
Venue - Dates:
16th AIAA Computational Fluid Dynamics Conference, Orlando, USA, 2003-06-21 - 2003-06-27
Identifiers
Local EPrints ID: 23535
URI: http://eprints.soton.ac.uk/id/eprint/23535
PURE UUID: 1064c69f-884f-4d24-8a41-81dd73893d0c
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Date deposited: 31 Mar 2006
Last modified: 16 Mar 2024 02:53
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