Accession Number:

AD0861814

Title:

Evaluation of Rocket Nozzle Passive Temperature Indicators (Test Nozzle No. 2).

Descriptive Note:

Technical rept.,

Corporate Author:

AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA

Personal Author(s):

Report Date:

1969-09-01

Pagination or Media Count:

60.0

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

Subject Categories:

  • Test Facilities, Equipment and Methods
  • Rocket Engines
  • Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE