Abstract
Advances in computational capabilities have allowed for the calculation of canonical hypersonic flows using the direct molecular simulation method. DMS is a particle method that uses quantum mechanically derived interaction potentials to simulate molecular collisions within a flow field. Since these interaction potentials are the only modeling inputs used in the simulation, all flow features can solely be attributed to the ab initio potential energy surfaces. The fundamental nature of these simulations lends to be used as benchmarks to assess lower fidelity models. In this work we investigated two canonical hypersonic flows, where the dominant gas-phase chemical activity was the dissociation of free stream diatomic species: (a) Mach 21 nitrogen flow over a blunt wedge and (b) Mach 8.2 oxygen flow over a double cone geometry. For the comparative analysis we consider seven actively used CFD codes and five thermochemical models. It is observed that new generation of thermochemistry models based in ab initio provide solutions that are more physical and compare favorably to the first principles DMS.
| Original language | English |
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| Title of host publication | AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025 |
| DOIs | |
| State | Published - 2025 |
| Event | AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025 - Orlando, United States Duration: Jan 6 2025 → Jan 10 2025 |
Publication series
| Name | AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025 |
|---|
Conference
| Conference | AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025 |
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| Country/Territory | United States |
| City | Orlando |
| Period | 1/6/25 → 1/10/25 |
Bibliographical note
Publisher Copyright:© 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
Funding
MSG, NJB, and PV would like to thank the Air Force Research Laboratory for funding this work under grant FA8650-16-2-2605. Computational resources for this work were provided at the Argonne Leadership Computing Facility, which is a DoE Office of Science User Facility supported under Contract DE-AC02-06CH11357 under the Innovative and Novel Computational Impact on Theory and Experiment (INCITE) program and the DoD HPCMP AFRL DSRC. We would like to thank the participants of this study and the AIAA-Thermophysics Technical Committee for facilitating discussion groups that lead to this study. AN and MP gratefully acknowledge funding for this work through ONR MURI grant N000142112475. SM and MP gratefully acknowledge funding for this work through AFOSR grant FA9550-22-1-0039. The University of Kentucky work was sponsored by DEVCOM-ARL and was accomplished under Cooperative Agreement Number W911NF-21-2-0075 and W911NF-19-2-0152. The views and conclusions contained in this document are those of the authors and should not be interpreted as representing the official policies, either expressed or implied, of the ARL or the U.S. Government. The U.S. Government is authorized to reproduce and distribute reprints for Government purposes notwithstanding any copyright notation herein. DA gratefully acknowledges funding for this work through the U.S. Air Force Office of Scientific Research Grant FA9550-23-1-0274 and the Office of Naval Research Grant N00022-1-2488.
| Funders | Funder number |
|---|---|
| DEVCOM Army Research Laboratory | |
| U.S. Department of Defense | |
| Air Force Office of Scientific Research, United States Air Force | FA9550-23-1-0274, FA9550-22-1-0039 |
| Office of Naval Research Naval Academy | N00022-1-2488 |
| DEVCOM-ARL | W911NF-19-2-0152, W911NF-21-2-0075 |
| Multidisciplinary University Research Initiative | N000142112475 |
| Office of Science Programs | DE-AC02-06CH11357 |
| Air Force Research Laboratory | FA8650-16-2-2605 |
ASJC Scopus subject areas
- Aerospace Engineering