COMPUTER CALCULATIONS OF ROCKET ENGINE COMBUSTION PROPERTIES

Abstract

The scope of this paper is limited to the equilibrium calculations of combustion products and the resulting adiabatic flame temperature. The problem of attempting to determine the equilibrium constituents as the gases progress through the rocket nozzle is not attempted here. A solution of a relatively simple combustion problem consisting of only six products of combustion is presented. By understanding and following the illustrated procedures a problem consisting of any number of products of combustion may be computed and solved to any desired degree of accuracy.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
May 01, 1963
Accession Number
AD0407450

Entities

People

  • Roy C. Robinette Jr.

Organizations

  • University of Wyoming

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Adiabatic Flames
  • Air Force
  • Chemical Equilibrium
  • Chemical Reactions
  • Combustion
  • Combustion Chambers
  • Combustion Products
  • Computer Programs
  • Computers
  • Equations
  • Exothermic Reactions
  • Heat Of Formation
  • Liquid Oxygen
  • Mechanical Engineering
  • Partial Pressure
  • Rocket Engines
  • Thermodynamics

Fields of Study

  • Physics

Readers

  • Petroleum Engineering
  • Theoretical Analysis.
  • Thermal Physics or Thermal Science.