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- W2322352207 abstract "Carbon fiber preforms, used as thermal protection materials for planetary entry systems, decompose via oxidation under hypersonic aerothermal conditions. The oxidation process is driven by two competing time-scales: the diffusion of reactants within the porous medium and the reaction speed at the surface of the fibers. A model to simulate this microscale process is proposed to be developed, tailored to the carbon preforms used to build lightweight carbon/phenolic ablators. The use of Direct Simulation Monte Carlo (DSMC) methods enables computation in the rarefied regime using advanced chemistry models for the gas/surface interactions at the fibers’ surface. To enable high fidelity simulations of the fibers decomposition, digitized computational grids are obtained from X-ray microtomography of real material. The recession due to oxidation is tracked using a marchingcube algorithm for surface discretization. Gas-phase and gas-surface chemistry near the surface are coupled and handled by the DSMC. Test cases of oxidation of a cylindrical carbon fiber embedded in a carbon matrix in ∗Postdoctoral Research Associate, Advanced Supercomputing Division, Mail Stop 258-5, NASA Ames Research Center, AIAA Member. †Postdoctoral Scholar, Department of Mechanical Engineering, 261 Ralph G. Anderson Building. Visiting Scientist, Thermal Protection Materials Branch, Mail Stop 234-1, NASA Ames Research Center, Moffett Field, CA, 94035, AIAA Senior Member. ‡Fundamental Modeling and Simulation Branch Chief, Advanced Supercomputing Division, Mail Stop 258-5, AIAA Associate Fellow." @default.
- W2322352207 created "2016-06-24" @default.
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- W2322352207 date "2015-06-18" @default.
- W2322352207 modified "2023-09-28" @default.
- W2322352207 title "DSMC Study of Carbon Fiber Oxidation in Ablative Thermal Protection Systems" @default.
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- W2322352207 doi "https://doi.org/10.2514/6.2015-3370" @default.
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