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)


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    Title :

    Evaluation of a Heat-Flux Measurement System


    Contributors:

    Publication date :

    1969


    Size :

    46 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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