Accession Number:

AD0843201

Title:

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

Descriptive Note:

Technical rept. Oct 67-Jun 68,

Corporate Author:

AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA

Personal Author(s):

• Zorich, David R.
• Bassoni, Attilio A.

Report Date:

1968-09-01

Pagination or Media Count:

82.0

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 galmin 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 galmin are easily attainable and inlet pressure may be varied from 250 psi to 900 psi. Author

Descriptors:

• *REGENERATIVE COOLING)
• (*ROCKET NOZZLES
• SOLID PROPELLANT ROCKET ENGINES
• TEST FACILITIES
• REFRACTORY COATINGS
• NOZZLE THROATS
• HEAT TRANSFER
• CAPTIVE TESTS
• CHECKOUT PROCEDURES
• INSTRUMENTATION
• COMBUSTION DEPOSITS
• TEST EQUIPMENT
• SPECIFICATIONS

Subject Categories:

• Air Conditioning, Heating, Lighting and Ventilating
• Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE