INVESTIGATION OF THE THERMODYNAMIC PROPERTIES OF ROCKET COMBUSTION PRODUCTS

Abstract

The accurate theoretical evaluation of new propellant systems in terms of specific impulse, range and similar parameters, requires a knowledge of the thermodynamic properties of the reactants and the thermodynamic and physical properties of the possible products. Among the values required are heat of formation, entropy, heat capacity, melting point, and heats of vaporization, fusion and sublimation. Since rocket exhaust temperature are in the range 2000- 5000 K, generally, the thermodynamic properties of the exhaust products must be known in this temperature range. A research program has been undertaken to determine the physical and thermodynamic properties of those species expected to be formed by the combustion of propellants.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1968
Accession Number
AD0835398

Entities

People

  • Margaret A. Frisch
  • Milton Farber

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Chemistry
  • Combustion Products
  • Electron Energy
  • Electrons
  • Enthalpy
  • Heat Energy
  • Heat Of Formation
  • Heat Of Reaction
  • Heat Of Vaporization
  • Mass Spectrometers
  • Measurement
  • Phase Diagrams
  • Physical Properties
  • Thermodynamic Properties
  • Vapor Pressure
  • X Rays
  • X-Ray Diffraction

Fields of Study

  • Physics

Readers

  • Combustion science or combustion engineering.
  • Rocket Propulsion.