Abstract
An implementation of adaptive mesh refinement (AMR) in the parallel unstructured implicit compressible flow solver US3D is presented. Building on previous work by Schwing [1], we have implemented AMR in the US3D software as a plugin with minimal modifications to the core solver. In this paper, we summarize the numerical methods used to accommodate grids with hanging nodes, discuss the architecture of the AMR plugin and how it interfaces with the flow solver, present a predictive load balancing method, and demonstrate the benefit of AMR in two cases: refinement in the wake of a Mach 15 waverider geometry and refinement of stationary vortices on a slender cone with a highly swept fin. The results show that one level of refinement significantly changes the waverider wake structure, causing the streak of high temperature air to split into two distinct streaks due to roll-up in the far wake. For the fin-cone case, results show that two levels of refinement are necessary to resolve the stationary vortices on the fin-cone geometry and match heat flux measurements from experiments.
| Original language | English (US) |
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| Title of host publication | AIAA Scitech 2021 Forum |
| Publisher | American Institute of Aeronautics and Astronautics Inc, AIAA |
| Pages | 1-13 |
| Number of pages | 13 |
| ISBN (Print) | 9781624106095 |
| State | Published - 2021 |
| Event | AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021 - Virtual, Online Duration: Jan 11 2021 → Jan 15 2021 |
Publication series
| Name | AIAA Scitech 2021 Forum |
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Conference
| Conference | AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021 |
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| City | Virtual, Online |
| Period | 1/11/21 → 1/15/21 |
Bibliographical note
Funding Information:The authors would like to thank Dr. Alan Schwing of NASA Johnson Space Center for numerous helpful discussions about adaptive mesh refinement, Dr. Matthew Bartkowicz of GoHypersonic, Inc. for the waverider grids used in Sections III.D and IV.A, and F. Drew Turbeville of Purdue University for providing the experimental data used in Section IV.B. This work was sponsored by the Office of Naval Research (ONR) under grant number N00164-20-1-2004. The views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of the ONR or the US Government.
Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.