Development of Commercially Useable Codes to Simulate Aluminized Propellant Combustion and Related Issues

Abstract

We have modified and developed a large number of codes relevant to the task including: a packing code to generate propellant morphology models; a homogenization code to predict homogenized properties of a heterogeneous propellant; a combustion code that predicts fluctuations in the hot gases coming off the propellant surface; and fluids codes that describe the rocket chamber flow, the rocket nozzle flow, aluminum transport, and nozzle erosion. The packing code is marketable; the homogenization code will be available as an addendum to the packing code in a few months; a fluids code that simulates the chamber flow using approximations valid for slender chambers is marketable, albeit without a user manual at this time; and further development of a nozzle code that accounts for nonuniform inlet conditions (at the nozzle inlet) is under further development under a recently awarded SBIR contract.

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Document Details

Document Type
Technical Report
Publication Date
Nov 03, 2009
Accession Number
ADA564789

Entities

People

  • John Buckmaster

Tags

Communities of Interest

  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Combustion
  • Computational Fluid Dynamics
  • Computational Science
  • Fluid Dynamics
  • Fluid Flow
  • Materials Laboratories
  • Materials Processing
  • Materials Science
  • Materials Testing
  • Mechanical Properties
  • Numerical Methods And Procedures
  • Physics Laboratories
  • Rocket Engines
  • Test And Evaluation
  • Three Dimensional
  • X-Ray Computed Tomography

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computational Fluid Dynamics (CFD)
  • Rocket Propulsion.