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Temperature Histories in Ceramic-Insulated Heat-Sink NozzleTemperature histories were calculated for a composite nozzle wall by a simplified numerical integration calculation procedure. These calculations indicated that there is a unique ratio of insulation and metal heat-sink thickness that will minimize total wall thickness for a given operating condition and required running time. The optimum insulation and metal thickness will vary throughout the nozzle as a result of the variation in heat-transfer rate. The use of low chamber pressure results in a significant increase in the maximum running time of a given weight nozzle. Experimentally measured wall temperatures were lower than those calculated. This was due in part to the assumption of one-dimensional or slab heat flow in the calculation procedure.
Document ID
19980227786
Acquisition Source
Headquarters
Document Type
Other - NASA Technical Note (TN)
Authors
Ciepluch, Carl C. (NASA Lewis Research Center Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1960
Subject Category
Nonmetallic Materials
Report/Patent Number
NASA-TN-D-300
E-774
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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