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A cooled-gas pyrometer for use in hypersonic engine testingA cooled-gas pyrometer designed for application in a hypersonic research engine program was fabricated and tested. Design and operational considerations and calibration data are presented. The probe was tested in a rocket-engine exhaust stream operating at Mach 2 and 2300 K. Test temperature measurements agreed to within 2 percent with a radiation shielded thermocouple probe.
Document ID
19730007769
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Glawe, G. E. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
February 1, 1973
Subject Category
Instrumentation And Photography
Report/Patent Number
E-7214
NASA-TM-X-2715
Report Number: E-7214
Report Number: NASA-TM-X-2715
Accession Number
73N16496
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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