A Strongly-coupled Non-parametric Integral Boundary Layer Method for Aerodynamic Analysis with Free Transition
© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. The integral boundary layer (IBL) method with viscous-inviscid coupling is an effective tool for rapid aerodynamic design and analysis. However, existing IBL methods remain to be extended to general three-dime...
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| Format: | Article |
| Language: | English |
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American Institute of Aeronautics and Astronautics (AIAA)
2021
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| Online Access: | https://hdl.handle.net/1721.1/137924 |
| _version_ | 1826188556655132672 |
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| author | Zhang, Shun Drela, Mark Galbraith, Marshall C. Allmaras, Steven R. Darmofal, David L. |
| author2 | Massachusetts Institute of Technology. Department of Aeronautics and Astronautics |
| author_facet | Massachusetts Institute of Technology. Department of Aeronautics and Astronautics Zhang, Shun Drela, Mark Galbraith, Marshall C. Allmaras, Steven R. Darmofal, David L. |
| author_sort | Zhang, Shun |
| collection | MIT |
| description | © 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. The integral boundary layer (IBL) method with viscous-inviscid coupling is an effective tool for rapid aerodynamic design and analysis. However, existing IBL methods remain to be extended to general three-dimensional (3D) configurations. To this end, previous work proposed an IBL formulation using the discontinuous Galerkin (DG) finite element method (FEM) with strong viscous-inviscid coupling, which is non-parametric in the sense that the aerodynamic shape is does not have to be explicitly parametrized by curvilinear coordinates. The current work builds on that strongly-coupled non-parametric IBL formulation, and further develops numerical discretization methods to enable flow transition modeling. Both a cut-cell-based fitted transition approach and a simple captured transition approach are presented and compared. In solving the nonlinear system of equations arising from free-transition problems, a strongly-coupled global Newton solver is adopted and augmented for solution robustness. Numerical results demonstrate favorable accuracy and robustness of the cut-cell fitted transition method compared to the captured transition methods. On the other hand, the captured transition approach allows for a more straightforward numerical implementation, but requires further improvement to achieve comparable reliability for aerodynamic analysis with free transition. |
| first_indexed | 2024-09-23T08:01:32Z |
| format | Article |
| id | mit-1721.1/137924 |
| institution | Massachusetts Institute of Technology |
| language | English |
| last_indexed | 2024-09-23T08:01:32Z |
| publishDate | 2021 |
| publisher | American Institute of Aeronautics and Astronautics (AIAA) |
| record_format | dspace |
| spelling | mit-1721.1/1379242023-03-29T19:59:24Z A Strongly-coupled Non-parametric Integral Boundary Layer Method for Aerodynamic Analysis with Free Transition Zhang, Shun Drela, Mark Galbraith, Marshall C. Allmaras, Steven R. Darmofal, David L. Massachusetts Institute of Technology. Department of Aeronautics and Astronautics © 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. The integral boundary layer (IBL) method with viscous-inviscid coupling is an effective tool for rapid aerodynamic design and analysis. However, existing IBL methods remain to be extended to general three-dimensional (3D) configurations. To this end, previous work proposed an IBL formulation using the discontinuous Galerkin (DG) finite element method (FEM) with strong viscous-inviscid coupling, which is non-parametric in the sense that the aerodynamic shape is does not have to be explicitly parametrized by curvilinear coordinates. The current work builds on that strongly-coupled non-parametric IBL formulation, and further develops numerical discretization methods to enable flow transition modeling. Both a cut-cell-based fitted transition approach and a simple captured transition approach are presented and compared. In solving the nonlinear system of equations arising from free-transition problems, a strongly-coupled global Newton solver is adopted and augmented for solution robustness. Numerical results demonstrate favorable accuracy and robustness of the cut-cell fitted transition method compared to the captured transition methods. On the other hand, the captured transition approach allows for a more straightforward numerical implementation, but requires further improvement to achieve comparable reliability for aerodynamic analysis with free transition. 2021-11-09T15:34:53Z 2021-11-09T15:34:53Z 2019-01 2019-10-24T18:32:23Z Article http://purl.org/eprint/type/ConferencePaper https://hdl.handle.net/1721.1/137924 Zhang, Shun, Drela, Mark, Galbraith, Marshall C., Allmaras, Steven R. and Darmofal, David L. 2019. "A Strongly-coupled Non-parametric Integral Boundary Layer Method for Aerodynamic Analysis with Free Transition." en 10.2514/6.2019-1154 Creative Commons Attribution-Noncommercial-Share Alike http://creativecommons.org/licenses/by-nc-sa/4.0/ application/pdf American Institute of Aeronautics and Astronautics (AIAA) Other repository |
| spellingShingle | Zhang, Shun Drela, Mark Galbraith, Marshall C. Allmaras, Steven R. Darmofal, David L. A Strongly-coupled Non-parametric Integral Boundary Layer Method for Aerodynamic Analysis with Free Transition |
| title | A Strongly-coupled Non-parametric Integral Boundary Layer Method for Aerodynamic Analysis with Free Transition |
| title_full | A Strongly-coupled Non-parametric Integral Boundary Layer Method for Aerodynamic Analysis with Free Transition |
| title_fullStr | A Strongly-coupled Non-parametric Integral Boundary Layer Method for Aerodynamic Analysis with Free Transition |
| title_full_unstemmed | A Strongly-coupled Non-parametric Integral Boundary Layer Method for Aerodynamic Analysis with Free Transition |
| title_short | A Strongly-coupled Non-parametric Integral Boundary Layer Method for Aerodynamic Analysis with Free Transition |
| title_sort | strongly coupled non parametric integral boundary layer method for aerodynamic analysis with free transition |
| url | https://hdl.handle.net/1721.1/137924 |
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