An a posteriori error control framework for adaptive precision optimization using discontinuous Galerkin finite element method
Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2005.
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| Format: | Thesis |
| Language: | eng |
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Massachusetts Institute of Technology
2006
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| Online Access: | http://hdl.handle.net/1721.1/34134 |
| _version_ | 1826188976135864320 |
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| author | Lu, James, 1977- |
| author2 | David L. Darmofal. |
| author_facet | David L. Darmofal. Lu, James, 1977- |
| author_sort | Lu, James, 1977- |
| collection | MIT |
| description | Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2005. |
| first_indexed | 2024-09-23T08:07:54Z |
| format | Thesis |
| id | mit-1721.1/34134 |
| institution | Massachusetts Institute of Technology |
| language | eng |
| last_indexed | 2024-09-23T08:07:54Z |
| publishDate | 2006 |
| publisher | Massachusetts Institute of Technology |
| record_format | dspace |
| spelling | mit-1721.1/341342022-01-13T07:54:11Z An a posteriori error control framework for adaptive precision optimization using discontinuous Galerkin finite element method Lu, James, 1977- David L. Darmofal. Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. Massachusetts Institute of Technology. Department of Aeronautics and Astronautics Aeronautics and Astronautics. Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2005. Includes bibliographical references (leaves 169-178). Introduction: Aerodynamic design optimization has seen significant development over the past decade. Adjoint-based shape design for elliptic systems was first proposed by Pironneau and applied to transonic flow by Jameson . A review of the aerodynamic shape optimization literature and a large list of references is given in. Over the years much technology has been developed, allowing engineers to contemplate applying optimization methods to a wide variety of problems. In the context of structured grids, adjoint-based applications include multipoint, multi-objective airfoil design using compressible Navier-Stokes equations and 3D multipoint design of aircraft configurations using inviscid Euler equations. There have also been significant effort in applying adjoint methods to the unstructured grid setting. In this context, Newman et al., Elliot and Peraire were among the first to develop discrete adjoint approaches for the inviscid Euler equations. by James Ching-Chi Ph.D. 2006-09-28T15:06:27Z 2006-09-28T15:06:27Z 2005 2005 Thesis http://hdl.handle.net/1721.1/34134 67769417 eng M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission. http://dspace.mit.edu/handle/1721.1/7582 178 leaves 8646467 bytes 8653948 bytes application/pdf application/pdf application/pdf Massachusetts Institute of Technology |
| spellingShingle | Aeronautics and Astronautics. Lu, James, 1977- An a posteriori error control framework for adaptive precision optimization using discontinuous Galerkin finite element method |
| title | An a posteriori error control framework for adaptive precision optimization using discontinuous Galerkin finite element method |
| title_full | An a posteriori error control framework for adaptive precision optimization using discontinuous Galerkin finite element method |
| title_fullStr | An a posteriori error control framework for adaptive precision optimization using discontinuous Galerkin finite element method |
| title_full_unstemmed | An a posteriori error control framework for adaptive precision optimization using discontinuous Galerkin finite element method |
| title_short | An a posteriori error control framework for adaptive precision optimization using discontinuous Galerkin finite element method |
| title_sort | a posteriori error control framework for adaptive precision optimization using discontinuous galerkin finite element method |
| topic | Aeronautics and Astronautics. |
| url | http://hdl.handle.net/1721.1/34134 |
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