AN INVESTIGATION OF THE EFFECTS OF SECONDARY STREAM TURBULATION ON THE THRUST AUGMENTATION OF AN EJECTOR-AFTERBURNER.

Abstract

Secondary stream turbulation of a supersonic ejector-afterburner was investigated using a nominal 65 pounds thrust gaseous hydrogen-oxygen rocket engine. The afterburner had a length-to-diameter ratio of 9 and an afterburner exit to nozzle-exit area ratio of 5.1. Several turbulator configurations, with aerodynamic blockage ratios from 0.123 to 0.516, were tested at three locations relative to the secondary stream inlet. Results showed that at mixture ratios less than 0.8, the performance of the ejector-afterburner could be improved with secondary stream turbulation. (Author)

Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1968
Accession Number
AD0832454

Entities

People

  • Wallace B. Adam

Organizations

  • Air Force Institute of Technology

Tags

DTIC Thesaurus Topics

  • Afterburners
  • Diameters
  • Engineering
  • Engines
  • Hydrogen
  • Mechanical Engineering
  • Propulsion System Components
  • Propulsion Systems
  • Rocket Engines
  • Rockets
  • Thrust
  • Thrust Augmentation
  • Thrusters

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow