Monte Carlo Simulation of a Rarefied Multiphase Plume Flow

Abstract

Exhaust flows from solid propellant rockets are characterized by a number of complex and often overlooked phenomena which should be considered for accurate numerical modeling. In a typical solid rocket motor (SRM), a 10 to 20% mass fraction of aluminum powder is used to reduce combustion instabilities and increase specific impulse. Within the combustion chamber, this aluminum content undergoes a complicated process of melting, heretogenous combustion, evaporation, agglomeration, and breakup.

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Document Details

Document Type
Technical Report
Publication Date
Dec 20, 2004
Accession Number
ADA433852

Entities

People

  • Iain D. Boyd
  • Jonathan Burt

Organizations

  • University of Michigan

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Chambers
  • Combustion
  • Combustion Chambers
  • Elements
  • Information Operations
  • Military Research
  • Monte Carlo Method
  • Payload
  • Rocket Engines
  • Simulations
  • Solid Propellants
  • Specific Impulse

Fields of Study

  • Physics

Readers

  • Aerosol Science/Aerosol Physics
  • Computational Modeling and Simulation
  • Rocket Propulsion.