Evaluation of a Heat-Flux Measurement System

Abstract

A solid rocket nozzle instrumented with total and radiative heat-flux transducers was test-fired 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. A narrow-view angle radiometer provided radiative heat-flux measurements at the throat. A 6500 degrees F flame temperature uncured propellant was used to provide a 1061-psig maximum chamber pressure for a 54-second total firing duration. A description of the heat-flux measurement system concept, nozzle design, motor preparation, performance, and posttest analysis is included in the report.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1969
Accession Number
AD0865583

Entities

People

  • Harold I. Binder
  • John R. Ellison

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Ablative Materials
  • Air Force
  • Combustion
  • Combustion Products
  • Contracts
  • Corporations
  • Data Analysis
  • Data Reduction
  • Flow
  • High Temperature
  • Measurement
  • Rocket Engines
  • Rocket Propulsion
  • Rockets
  • Solid Propellants
  • Test And Evaluation
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Rocket Propulsion.