MODEL ENGINE FLAME SPECTRAL STUDIES VOLUME III. ENGINE PERFORMANCE COMPUTER STUDIES,

Abstract

As thermodynamic information on the performance of specific engines using specific fuels was found to be inadequate. A computer program was developed for combustion studies of liquid rocket propellants. These included UDMH-N2 04, hydrazine-N2 O4. and RP-1-LOX fuel-oxidiza combinations. Results are tabulated. A brief analysis was made of some of the more important performance perameters for the three fuel-oxidizer combinations. Studies of mixing ratio against temperature, and composition of certain key exhaust constituents, such as H2O, CO, and CO2 reveal many features of importance to the propulsion engineer, as well as to the spectrosopist. Also considered was the study of expansion ratio with mixing ratio. (Author)

Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1963
Accession Number
AD0427354

Entities

People

  • H. J. Hemesath

Organizations

  • Lockheed Martin Missiles and Space

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Combustion
  • Computer Programs
  • Computers
  • Energetic Materials
  • Engineers
  • Hydrazines
  • Liquid Propellants
  • Liquid Rocket Propellants
  • Materials
  • Propellants
  • Rocket Propellants

Readers

  • Combustion science or combustion engineering.
  • Computational Modeling and Simulation