Numerical Modeling of Internal Flow Aerodynamics. Part 2: Unsteady Flows

Abstract

It has been widely reported in the open literature that large segmented and axisymmetric Solid Rocket Motors (SRM) are subject to pressure oscillations caused by vortex shedding at annular restrictors or cavities in the grain, and acoustic feedback resulting from impingement of the vortices on the nozzle or other obstacles. If they are well suited for combustion instabilities studies in tactical rocket motors, acoustic balance methods have proven inefficient in predicting stability of large segmented rocket motors (e.g. Ariane 5 MPS and Titan IV SRMU).

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 2004
Accession Number
ADA425807

Entities

People

  • Jean-francois Guery

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Acoustics
  • Aerodynamics
  • Aluminum Oxides
  • Boundary Layer
  • Burning Rate
  • Combustion
  • Computational Fluid Dynamics
  • Crystal Lattice Vibrations
  • Flow Rate
  • Fluid Flow
  • Frequency
  • Frequency Shift
  • Geometry
  • Rocket Engines
  • Steady State
  • Two Dimensional
  • Two Phase Flow

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Rocket Propulsion.