Solid Propellant Test Evaluation of Water-Cooled Nozzle

Abstract

The objective of this test program was to evaluate the feasibility of using a water-cooled nozzle on large solid propellant motors. The coolant requirement for this test was 1200 gal/min water flow rate with an inlet coolant pressure of 850 psi. The flow was reduced during the test with a minimum water flow rate of 560 gal/min. The nozzle performed successfully with no indication of tube burnthrough or film boiling occurring. Test duration was 62 seconds at an average chamber pressure of 380 psi. Results of this test indicated the entire system operated satisfactorily at maximum operating conditions.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1969
Accession Number
AD0854548

Entities

People

  • Attilio A. Bassoni
  • David R. Zorich

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Burnthrough
  • Checkout Procedures
  • Combustion
  • Film Boiling
  • Flow Rate
  • Heat Transfer
  • Instrumentation
  • Intercontinental Ballistic Missiles
  • Materials
  • Propellants
  • Rocket Propulsion
  • Solid Propellants
  • Tank Vents
  • Test And Evaluation
  • Test Facilities
  • Water Flow

Fields of Study

  • Physics

Readers

  • Combustion science or combustion engineering.
  • Electrical Engineering
  • Internal Combustion Engine (ICE) Technology.