Two-Dimensional, Two-Phase Flow Through a Rocket Exhaust Nozzle: A Progress Report,

Abstract

This memorandum describes progress in the development of a set of computer programs which solve the equations of gas/particle flow throgh an axisymmetric nozzle. Tow programs have been writtern to solve the equations in the transonic throat region of the nozzle. The first treats the two-phase fluid as a heavy perfect gas with modified isentropic exponent and molecular weight, and solves the equations of isentropic transonic flow. An initial flow field configuration is obtained for input to the second program, which incorporates non-equilibrium effects of the gas/particle mixture. The programs provide accurate initial line data for starting a supersonic calculation, and will be used as input to a third program, soon to be written, for solving the two-phase flow equations in the supersonic region of the nozzle. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1976
Accession Number
ADA038151

Entities

People

  • Jane M. Cousins

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Chemical Reactions
  • Coefficients
  • Computer Programs
  • Curvature
  • Differential Equations
  • Equations
  • Exhaust Nozzles
  • Flow Fields
  • Geometry
  • Heat Transfer
  • Mach Number
  • Molecular Weight
  • Reynolds Number
  • Rocket Exhaust
  • Static Pressure
  • Transonic Flow
  • Two Phase Flow

Fields of Study

  • Physics

Readers

  • Calculus or Mathematical Analysis
  • Computer Science.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight