Accession Number:

ADA004666

Title:

Specific Impulses Losses in Solid Propellant Rockets

Descriptive Note:

Corporate Author:

FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH

Personal Author(s):

Report Date:

1974-12-17

Pagination or Media Count:

222.0

Abstract:

The discrepancy between experimental and theoretical specific impulses of metallized propellants is partly due to the presence of a condensed phase in combustion products. The theoretical analysis and the experimental study of this condensed phase both indicate a noteworthy increase in size of the particles during their evolution within the motor. The two-phase flow general equations are established and applied to a nozzle flow the loss in specific impulse due to irreversible exchanges between phases is expressed analytically in a few particular cases. The condensed layer forming along the nozzle has little influence on the wall loss. Analytical predictions of the overall specific impulse loss compare well with measurements made on actual rocket motors.

Subject Categories:

  • Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE