Development of the US3D code for advanced compressible and reacting flow simulations

Research output: Chapter in Book/Report/Conference proceedingConference contribution

133 Scopus citations


Aerothermodynamics and hypersonic flows involve complex multi-disciplinary physics, including finite-rate gas-phase kinetics, finite-rate internal energy relaxation, gas-surface interactions with finite-rate oxidation and sublimation, transition to turbulence, large-scale unsteadiness, shock-boundary layer interactions, fluid-structure interactions, and thermal protection system ablation and thermal response. Many of the flows have a large range of length and time scales, requiring large computational grids, implicit time integration, and large solution run times. The University of Minnesota / NASA US3D code was designed for the simulation of these complex, highly-coupled flows. It has many of the features of the well-established DPLR code, but uses unstructured grids and has many advanced nu- merical capabilities and physical models for multi-physics problems. The main capabilities of the code are described, the physical modeling approaches are discussed, the different types of numerical flux functions and time integration approaches are outlined, and the parallelization strategy is overviewed. Comparisons between US3D and the NASA DPLR code are presented, and several advanced simulations are presented to illustrate some of novel features of the code.

Original languageEnglish (US)
Title of host publication53rd AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103438
StatePublished - 2015
Event53rd AIAA Aerospace Sciences Meeting, 2015 - Kissimmee, United States
Duration: Jan 5 2015Jan 9 2015

Publication series

Name53rd AIAA Aerospace Sciences Meeting


Other53rd AIAA Aerospace Sciences Meeting, 2015
Country/TerritoryUnited States

Bibliographical note

Funding Information:
We would like to thank Joseph Brock, Eric Stern, and Loretta Trevi?o for providing simulation results for the paper. This work was sponsored by the Air Force Office of Scientific Research under grants FA9550-10- 1-0563 and FA9550-12-1-0064, the Department of Defense National Security Science & Engineering Faculty Fellowship, and NASA through the Fundamental Aeronautics Program. The Department of Defense HPCMO PETTT Program supported the development of the node-based partitioning. Model development was supported by the NASA Entry Systems Modeling Project within the Game Changing Development Program. Dr. Barnhardt is supported through NASA Contract NNA10DE12C with ERC Inc. 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 funding agencies or the U.S. Government.

Publisher Copyright:
© 2015 by Graham V. Candler.


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