INVESTIGATION OF THE THRUST AUGMENTATION CAPABILITY OF A SONIC EJECTOR-AFTERBURNER.

Abstract

The purpose of this investigation was to determine the thrust augmentation capability of a sonic ejector-afterburner. Two hundred and five tests were conducted at static conditions on a nominal 65 pounds thrust rocket engine using gaseous hydrogen and oxygen as the propellants. Afterburner length and diameter, engine chamber pressure, and propellant mixture ratio were varied to determine the conditions under which optimum performance could be achieved. Performance increased with high chamber pressure, large length to diameter ratios, and high secondary inlet flow areas. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1967
Accession Number
AD0817968

Entities

People

  • Kenneth E. Nidiffer

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Afterburners
  • Diameters
  • Engines
  • Hydrogen
  • Propellants
  • Rocket Engines
  • Rockets
  • Thrust
  • Thrust Augmentation

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Propulsion Engineering.
  • Internal Combustion Engine (ICE) Technology.