Description of a Gas-Pressurized Water-Flow System for the NASA Water-Cooled Nozzle Program.

Abstract

The objective of this facilities buildup was the support of a NASA Lewis Research Center Program dealing with a water-cooled nozzle concept for solid propellant rocket motors. The support requirements for cooling the second-stage Titan II nozzle employed in the project are 1080 gal/min flow rate at 750 psi, which may be varied during the test program. Results of the flow tests indicate that instrumentation has been calibrated and its accuracy is within plus or minus F. Flow rates from 600 to 1266 gal/min are easily attainable and inlet pressure may be varied from 250 psi to 900 psi. (Author)

Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1968
Accession Number
AD0843201

Entities

People

  • Attilio A. Bassoni
  • David R. Zorich

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Flow
  • Flow Rate
  • Instrumentation
  • Intercontinental Ballistic Missiles
  • Measuring Instruments
  • Propellants
  • Rocket Engines
  • Rockets
  • Solid Propellants
  • Water Flow

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.
  • Rocket Propulsion.