Accession Number : AD0879697

Title :   Evaluation of a Heat Flux Measurement System (Test No. 2).

Descriptive Note : Technical rept.,

Corporate Author : AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA

Personal Author(s) : Ellison, John R.

Report Date : DEC 1970

Pagination or Media Count : 41

Abstract : 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)

Descriptors :   (*HEAT FLUX, MEASUREMENT), (*NOZZLE INSERTS, THERMAL STRESSES), (*SOLID PROPELLANT ROCKET ENGINES, CAPTIVE TESTS), ROCKET NOZZLES, NOZZLE THROATS, SPECIFIC IMPULSE, COMBUSTION PRODUCTS, INSTRUMENTATION.

Subject Categories : Thermodynamics
      Solid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE