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Effects of Non-Equilibrium Chemistry and Darcy-Forchheimer Flow of Pyrolysis Gas for a Charring AblatorThe Fully Implicit Ablation and Thermal Response code, FIAT, simulates pyrolysis and ablation of thermal protection materials and systems. The governing equations, which include energy conservation, a three-component decomposition model, and a surface energy balance, are solved with a moving grid. This work describes new modeling capabilities that are added to a special version of FIAT. These capabilities include a time-dependent pyrolysis gas flow momentum equation with Darcy-Forchheimer terms and pyrolysis gas species conservation equations with finite-rate homogeneous chemical reactions. The total energy conservation equation is also enhanced for consistency with these new additions. Parametric studies are performed using this enhanced version of FIAT. Two groups of analyses of Phenolic Impregnated Carbon Ablator (PICA) are presented. In the first group, an Orion flight environment for a proposed Lunar-return trajectory is considered. In the second group, various test conditions for arcjet models are examined. The central focus of these parametric studies is to understand the effect of pyrolysis gas momentum transfer on PICA material in-depth thermal responses with finite-rate, equilibrium, or frozen homogeneous gas chemistry. Results are presented, discussed, and compared with those predicted by the baseline PICA/FIAT ablation and thermal response model developed by the Orion Thermal Protection System Advanced Development Project.
Document ID
20160000306
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Chen, Yih-Kanq
(NASA Ames Research Center Moffett Field, CA United States)
Milos, Frank S.
(NASA Ames Research Center Moffett Field, CA United States)
Date Acquired
January 6, 2016
Publication Date
June 27, 2011
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
ARC-E-DAA-TN3683
Report Number: ARC-E-DAA-TN3683
Meeting Information
Meeting: AIAA Thermophysics Conference
Location: Honolulu, HI
Country: United States
Start Date: June 27, 2011
End Date: June 30, 2011
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 599489.02.07.01.02.21.21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
Ablation
Thermal Protection
Computation
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