Agglomeration of Alumina Particles in the Flow of a Metallized Propellant Rocket Nozzle

Abstract

The agglomeration of liquid alumina particles takes place in the convergent region and at the throat of the nozzle; it leads to an increase of performance losses related to the velocity and temperature differences between the condensed and gaseous phases. The problem is first schematized; then the fundamental equations of the problem are established that give the evolution of the distribution law of the particle population, and of the variables induced by the collisions.

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Document Details

Document Type
Technical Report
Publication Date
Sep 11, 1974
Accession Number
ADA000135

Entities

People

  • P. Kuentzmann

Organizations

  • National Air and Space Intelligence Center

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boltzmann Equation
  • Chambers
  • Collisions
  • Combustion
  • Combustion Chambers
  • Differential Equations
  • Equations
  • Flow
  • Foreign Technology
  • Gas Turbine Nozzles
  • Nozzles
  • Payload
  • Propellants
  • Rocket Nozzles
  • Rockets
  • Standards

Fields of Study

  • Physics

Readers

  • Aerosol Science/Aerosol Physics
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Rocket Propulsion.