Evaluation of Rocket Nozzle Passive Temperature Indicators (Test Nozzle No. 2).
Abstract
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1969
- Accession Number
- AD0861814
Entities
People
- Harold I. Binder
- John R. Ellison
Organizations
- Air Force Research Laboratory