Evaluation of Rocket Nozzle Passive Temperature Indicators (Test Nozzle No. 2).
AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
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The objective of this test was to demonstrate a technique for measuring subsurface nozzle material temperatures beyond the range of conventional thermocouples. The objective was achieved by designing and fabricating a 2.3-inch-throat-diameter solid rocket nozzle and instrumenting it with high-temperature indicators, the evaluation and selection of propellant ballistic properties to obtain 6500 degrees F flame temperature, 810-psig maximum chamber pressure, 21.9-sec effective firing duration, and posttest evaluation of the rocket nozzle including X-ray analysis and sectioning. Author
- Test Facilities, Equipment and Methods
- Rocket Engines
- Solid Propellant Rocket Engines