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Nonequilibrium Ablation of Phenolic Impregnated Carbon AblatorIn previous work, an equilibrium ablation and thermal response model for Phenolic Impregnated Carbon Ablator was developed. In general, over a wide range of test conditions, model predictions compared well with arcjet data for surface recession, surface temperature, in-depth temperature at multiple thermocouples, and char depth. In this work, additional arcjet tests were conducted at stagnation conditions down to 40 W/sq cm and 1.6 kPa. The new data suggest that nonequilibrium effects become important for ablation predictions at heat flux or pressure below about 80 W/sq cm or 10 kPa, respectively. Modifications to the ablation model to account for nonequilibrium effects are investigated. Predictions of the equilibrium and nonequilibrium models are compared with the arcjet data.
Document ID
Acquisition Source
Ames Research Center
Document Type
Reprint (Version printed in journal)
External Source(s)
Milos, Frank S.
(NASA Ames Research Center Moffett Field, CA, United States)
Chen, Yih K.
(NASA Ames Research Center Moffett Field, CA, United States)
Gokcen, Tahir
(Eloret Corp. Sunnyvale, CA, United States)
Date Acquired
August 25, 2013
Publication Date
October 1, 2012
Publication Information
Publication: Journal of Spacecraft and Rockets
Publisher: American Inst. of Aeronautics and Astronautics
Volume: 49
Issue: 5
Subject Category
Composite Materials
Report/Patent Number
Funding Number(s)
Distribution Limits
Public Use Permitted.
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