Evaluation of water cooled supersonic temperature and pressure probes for application to 1366 K flowsWater cooled supersonic probes are developed to investigate total pressure, static pressure, and total temperature in high-temperature jet plumes and thereby determine the mean flow properties. Two probe concepts, designed for operation at up to 1366 K in a Mach 2 flow, are tested on a water cooled nozzle. The two probe designs - the unsymmetric four-tube cooling configuration and the symmetric annular cooling design - take measurements at 755, 1089, and 1366 K of the three parameters. The cooled total and static pressure readings are found to agree with previous test results with uncooled configurations. The total-temperature probe, however, is affected by the introduction of water coolant, and effect which is explained by the increased heat transfer across the thermocouple-bead surface. Further investigation of the effect of coolant on the temperature probe is proposed to mitigate the effect and calculate more accurate temperatures in jet plumes.
Document ID
19910067243
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lagen, Nicholas (George Washington University Hampton, VA, United States)
Seiner, John M. (NASA Langley Research Center Hampton, VA, United States)