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Thermal protection for hypervelocity flight in earth's atmosphere by use of radiation backscattering ablating materialsA heat-shield-material response code predicting the transient performance of a material subject to the combined convective and radiative heating associated with the hypervelocity flight is developed. The code is dynamically interactive to the heating from a transient flow field, including the effects of material ablation on flow field behavior. It accomodates finite time variable material thickness, internal material phase change, wavelength-dependent radiative properties, and temperature-dependent thermal, physical, and radiative properties. The equations of radiative transfer are solved with the material and are coupled to the transfer energy equation containing the radiative flux divergence in addition to the usual energy terms.
Document ID
19910058769
Document Type
Conference Paper
Authors
Howe, John T. (NASA Ames Research Center Moffett Field, CA, United States)
Yang, Lily (Sterling Software, Inc. Palo Alto, CA, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1991
Subject Category
FLUID MECHANICS AND HEAT TRANSFER
Report/Patent Number
AIAA PAPER 91-1321
Distribution Limits
Public
Copyright
Other