A solid rocket nozzle instrumented with total and radiative heat-flux transducers was test-fired on the AFRPL 36-inch Char motor. The nozzle was a conventional heavyweight test configuration. The test objective was to measure the total and radiative heat-flux components incident on the nozzle ablative liners. Thermocouple instrumented plugs of ablative material comprised the total heat-flux measurement system. Plugs were placed in the entrance cap, throat, throat extension, and exit sections of the nozzle. A narrow-view angle radiometer provided radiative heat-flux measurements at the throat. A 6500 degrees F flame temperature uncured propellant was used to provide a 1061-psig maximum chamber pressure for a 54-second total firing duration. A description of the heat-flux measurement system concept, nozzle design, motor preparation, performance, and posttest analysis is included in the report. (Author)
Evaluation of a Heat-Flux Measurement System
1969
46 pages
Report
No indication
English
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