Numerical Investigation of Multi-Plume Rocket Phenomenology

Abstract

The Generalized Implicit Flow Solver (GIFS) computer program has been modified and used for three-dimensional reacting two-phase flow problems. The intent of the original GIFS development effort was to provide the JANNAF community with a standard computational methodology to simulate multiple nozzle/plume flow-field phenomena and other three-dimensional effects. Recent development efforts have concentrated on improving the run time and robustness of the algorithm. The GIFS computer program was originally released as an untested research version. Since that time, several corrections and enhancements have been made to the model. The Van Leer Flux Splitting option has been successfully implemented into the existing GIFS model and provides a more robust solution scheme, A Parabolized Navier-Stokes (PNS) version of the GIFS algorithm is currently under development and is intended to substantially improve the run-time requirements for flow fields dominated by supersonic flow regimes. This paper reports the significant results of several applications of the GIFS model. Specifically, three separate 3D calculations of the Minuteman III first and third stage solid rocket motors with and without the base region were completed to assess the effect of the base in multiple nozzle/plume flow-field simulations. One additional 2D and two 3D calculations simulating the exhaust flow field of the Titan and the generic Ariane were completed to determine the three-dimensional effects and the impact of the single equivalent nozzle assumption in these flow environments. The results of these calculations indicate that the base region effect is significant for up to 14 nozzle exit diameters in axial plume length. In addition, three-dimensional effects are important in the plume near-field domain, and the equivalent single nozzle assumption is shown to be inaccurate in this region.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1997
Accession Number
ADA345900

Entities

People

  • Houshang B. Ebrahimi

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Chemistry
  • Computational Fluid Dynamics
  • Computer Programs
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Geometry
  • Intercontinental Ballistic Missiles
  • Propulsion Systems
  • Rocket Engines
  • Rockets
  • Simulations
  • Supersonic Flow
  • Three Dimensional
  • Turbulent Mixing
  • Two Dimensional

Readers

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

Technology Areas

  • Hypersonics