Accession Number : ADA004666


Title :   Specific Impulses Losses in Solid Propellant Rockets


Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH


Personal Author(s) : Kuentzmann, Paul


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a004666.pdf


Report Date : 17 Dec 1974


Pagination or Media Count : 222


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.


Descriptors :   *SPECIFIC IMPULSE , *SOLID PROPELLANT ROCKET ENGINES , FRANCE , TRANSLATIONS , SOLID ROCKET PROPELLANTS , TWO PHASE FLOW , COMBUSTION , THESES , COMBUSTION STABILITY


Subject Categories : Solid Propellant Rocket Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE