NASA NTRS · 19730007769
A cooled-gas pyrometer for use in hypersonic engine testing
Abstract
A 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.
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Glawe, G. E.. 1973-02-01. A cooled-gas pyrometer for use in hypersonic engine testing. https://ntrs.nasa.gov/citations/19730007769
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