Published January 5, 2015
| Accepted Version
Book Section - Chapter
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Towards direct simulations of counterflow flames with consistent differential-algebraic boundary conditions
Abstract
A new approach for the formulation of boundary conditions for the counterflow configuration is presented. Upon discretization of the steady-state Navier-Stokes equations at the inflow boundaries, numerically algebraic equations are imposed as boundary conditions, while upon discretization of the unsteady Navier-Stokes equations at the outflow, differential boundaries result. It is demonstrated that the resulting numerical differential-algebraic boundary conditions are suitable to account for the multi-directional character of the flow at the boundaries of the counterflow configuration.
Additional Information
© 2015 American Institute of Aeronautics and Astronautics. This work was performed at the California Institute of Technology and the Jet Propulsion Laboratory Division of the California Institute of Technology, and was sponsored by United States Army Research Office, with Dr. Ralph Anthenien as contract monitor. Supercomputing time from the DoD HPCMP Open Research Systems and JPL/NASA is gratefully acknowledged.Attached Files
Accepted Version - DTIC_ADA625948.pdf
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Additional details
- Eprint ID
- 97977
- Resolver ID
- CaltechAUTHORS:20190816-144341538
- Army Research Office (ARO)
- NASA/JPL/Caltech
- Created
-
2019-08-21Created from EPrint's datestamp field
- Updated
-
2021-11-16Created from EPrint's last_modified field
- Other Numbering System Name
- DTIC
- Other Numbering System Identifier
- ADA625948