Computer Programs to Calculate Chemically Reacting Flow in Axisymmetric Nozzles.

Abstract

This report describes a set of computer programs which calculates the inviscid two-dimensional expansion of gaseous exhaust mixtures through rocket nozzles. Equilibrium chemistry in the combustion chamber and as far as the nozzle throat is assumed, whilst finite rate or frozen chemistry may be applied from the throat onwards. The transonic flow field is calculated by the method of streamline curvature and the flow in the supersonic region of the nozzle is solved by the method of characteristics. The theory on which the programs are based is summarised and a comprehensive user's guide is included. A sample calculation is presented. (Author)

Open PDF

Document Details

Document Type
Technical Report
Publication Date
May 01, 1978
Accession Number
ADA058869

Entities

People

  • Jane M. Cousins

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Chambers
  • Chemical Reactions
  • Chemistry
  • Combustion
  • Computer Programs
  • Equations
  • Flow Fields
  • Geometry
  • Mach Number
  • Method Of Characteristics
  • Nozzles
  • Rocket Engines
  • Rocket Exhaust
  • Rocket Nozzles
  • Supersonic Flow
  • Transonic Flow
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Combustion science or combustion engineering.
  • Computer Science.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight