Supersonic Gas-Solid Particle Flow in an Axisymmetric Nozzle by the Method of Characteristics

Abstract

A study was conducted to numerically treat a mixture composed of a gas and solid particles in a supersonic, axisymmetric nozzle. The governing equations are a set of eight first order, quasi-linear, partial differential equations. Seven of these equations are of the hyperbolic type when the flow is supersonic (based on the frozen speed of sound in the gas) and can be solved by the method of characteristics. The eighth equation (the particle continuity equation) is rewritten as an integral equation to be solved. The resulting seven compatibility equations and the seven characteristic equations (only four are distinct; the two gas Mach lines and the gas and particle streamlines) are solved by the modified Euler predictor-corrector algorithm. These equations were programmed for an IBM 1130 computer. A sample nozzle calculation is given and compared with the one-dimensional calculations. These results indicate that the program is working correctly.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1971
Accession Number
AD0890462

Entities

People

  • G. R. Johnson

Organizations

  • von Kármán Institute for Fluid Dynamics

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes
  • Weapons Technologies

DTIC Thesaurus Topics

  • Artificial Intelligence
  • Boundaries
  • Computational Fluid Dynamics
  • Computational Science
  • Differential Equations
  • Equations
  • Flow Fields
  • Flow Rate
  • Fluid Dynamics
  • Fluid Flow
  • Gas Flow
  • Mach Number
  • Mesh
  • Partial Differential Equations
  • Prandtl Number
  • Reynolds Number
  • Specific Heat

Fields of Study

  • Physics

Readers

  • Calculus or Mathematical Analysis
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow