Permeability of ablative materials under rarefied gas conditions

White, C. , Scanlon, T. J. and Brown, R. E. (2016) Permeability of ablative materials under rarefied gas conditions. Journal of Spacecraft and Rockets, 53(1), pp. 134-142. (doi: 10.2514/1.A33279)

111765.pdf - Accepted Version



Numerical meshes of both cork and carbon fiber ablative materials in their virgin and pyrolized states, with realistic porosity and tortuosity, have been created from microcomputed tomography scans. The porosity of each material has been calculated from the microcomputed scans and used to extract smaller representative sample volumes to perform numerical simulations on. Direct simulation Monte Carlo simulations of rarefied gas flow through these materials have been performed to find the permeability of each material to argon gas and to a gas mixture. The method has been validated by comparing the measured permeability for a Berea sandstone material with previously published experimental values. For the specific pressure conditions investigated here, the cork-phenolic material becomes around 10 times more permeable after being pyrolized, whereas the carbon-phenolic material only becomes five times more permeable than its virgin form. The permeability to the gas mixture is found to be greater than to argon for most of the samples, showing the importance of choosing the correct gas for rarefied permeability studies. The form of the pressure and Mach number profiles through the materials is independent of the applied pressure gradient.

Item Type:Articles
Glasgow Author(s) Enlighten ID:White, Dr Craig
Authors: White, C., Scanlon, T. J., and Brown, R. E.
College/School:College of Science and Engineering > School of Engineering > Autonomous Systems and Connectivity
Journal Name:Journal of Spacecraft and Rockets
Publisher:American Institute of Aeronautics and Astronautics, Inc.
ISSN (Online):1533-6794
Copyright Holders:Copyright © 2016 American Institute of Aeronautics and Astronautics, Inc.
First Published:First published in Journal of Spacecraft and Rockets 53(1): 134-142
Publisher Policy:Reproduced in accordance with the publisher copyright policy

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