Specific Impulses Losses in Solid Propellant Rockets

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.

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Document Details

Document Type
Technical Report
Publication Date
Dec 17, 1974
Accession Number
ADA004666

Entities

People

  • Paul Kuentzmann

Organizations

  • National Air and Space Intelligence Center

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aluminum Oxides
  • Ammonium Perchlorate
  • Boundary Layer
  • Chemical Reactions
  • Chemistry
  • Combustion
  • Composite Propellants
  • Computer Programs
  • Differential Equations
  • Equations Of Motion
  • Heat Energy
  • Heat Transfer
  • Materials Laboratories
  • Measurement
  • Mechanical Properties
  • Rocket Engines
  • Thermal Conductivity

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Rocket Propulsion.
  • Theoretical Analysis.