It is critical to understand how hypersonic simulation tools perform on a range of computational platforms. This information will aid in the acquisition of appropriate hardware and the potential refactoring of hypersonic codes to run on different systems. In this paper, we consider two representative high-speed reacting flow cases: a model Mach 8 hypersonic waverider glide vehicle and a model hydrocarbon-fueled hypersonic ramjet propulsion system. In both scenarios, the flow fields are in chemical non-equilibrium and are modeled by the multi-species reacting Navier-Stokes equations. For these simulations we use several hypersonic simulation tools, including US3D, Kestrel, FUN3D, and the JENRER○ flow solver. We explore several high performance computing systems containing IntelR○ XeonR○ Platinum processors, AMD EPYCTM 7702 processors, and NVIDIAR○ Tesla V100 devices. We compare performance and strong scaling between the different systems.
|Original language||English (US)|
|Title of host publication||AIAA Scitech 2021 Forum|
|Publisher||American Institute of Aeronautics and Astronautics Inc, AIAA|
|Number of pages||20|
|State||Published - 2021|
|Event||AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021 - Virtual, Online|
Duration: Jan 11 2021 → Jan 15 2021
|Name||AIAA Scitech 2021 Forum|
|Conference||AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021|
|Period||1/11/21 → 1/15/21|
Bibliographical noteFunding Information:
This work was supported in part by the DoD HPCMP, through Naval Sea System Command Award # N00024-19-D-6400, task order N00024-19-F-8814 and Air Force Research Labs Directed Energy Division Award # FA9451-20-D-0004, task order FA9451-20-f-0004, to the Maui High Performance Computing Center (MHPCC), which is operated by the University of Hawaii. Additional support was also provided through DoD HPCMP’s Productivity Enhancement and Training (PET) program. Computing resources were provided by the DoD HPCMP. The NASA participants in this study would like to acknowledge the support of the NASA Langley Research Center CIF/IRAD program and the NASA Transformational Tools and Technologies (TTT) Project of the Transformative Aeronautics Concepts Program under the Aeronautics Research Mission Directorate. We also thank Dr. Gabriel Goodwin (Naval Research Laboratory) for providing the ramjet combustion test case.
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