Evaluation of a Heat Flux Measurement System (Test No. 2).
AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
Pagination or Media Count:
A solid rocket nozzle instrumented with total and radiative heat flux transducers was test fired 6 February 1970 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. Two narrow-view-angle radiometers provided radiative heat flux measurements at the throat and at a supersonic area ratio of 3.0. A 6500 degrees F flame temperature uncured propellant was used to provide 930 psia maximum chamber pressure for a 58-second total firing duration. A description of the heat flux measurement system concept, nozzle design, motor preparation, performance, and post-test analysis is included in the report. Author
- Solid Propellant Rocket Engines