Accession Number:

AD0780532

Title:

High Chamber Pressure Blast Tube and Nozzle Material Evaluation. Volume 2

Descriptive Note:

Final rept.

Corporate Author:

UNITED TECHNOLOGY CENTER SUNNYVALE CA

Personal Author(s):

• Stephen, Wendell A.
• Frakes, T. E.
• O'Hara, T. V.

Report Date:

1974-06-17

Pagination or Media Count:

201.0

Abstract:

The set of Aerotherm computer programs ACE, CMA, ARGEIBL which were validated for charring ablating and carboncarbon materials in conventional and low velocity blast tube nozzles were validated for these same materials for high velocity blast tube nozzles, operation at high chamber pressures up to 3000 psia, and aluminized CTPB propellants which vary in aluminum content from 5 to 18 percent. The validation was determined based on comparisons between measured and predicted surface recession and char depth thickness and between predicted and determined convective heat transfer coefficients. In general, the agreement between the analytical predictions and the surface recession and char depth data was within the experimental accuracy of the measurements with the exception of the throat. The best agreement was obtained for the analysis locations in the blast tube and exit cone. The poorest agreement occured for the pyrolytic graphite washers in the nozzle throat region.

Descriptors:

• *SOLID PROPELLANT ROCKET ENGINES
• *ROCKET NOZZLES
• *NOZZLE THROATS
• *BLAST TUBES
• HEAT FLUX
• AIR LAUNCHED
• CARBON PHENOLIC MATERIALS
• ABLATIVE MATERIALS
• GUIDED MISSILES
• SOLID ROCKET PROPELLANTS
• CONVECTION(HEAT TRANSFER)
• COMPUTER APPLICATIONS
• COMBUSTION CHAMBERS
• THERMAL RADIATION

Subject Categories:

• Air- and Space-Launched Guided Missiles
• Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE