An Investigation of the Static Thrust Augmentation Capabilities of a Divergent Ejector-Afterburner

Abstract

The effects on static thrust augmentation and mass entrainment of various divergent ejector-afterburner configurations were investigated. Static tests were conducted using a gaseous oxygen/hydrogen sonic rocket as the primary gas generator. Configurations included various length mixing ducts, two different size diffusers, burn ducts, and secondary nozzles. Oxydizer-to-fuel mixture ratio was varied from .3 to 1.5 at 80 psia chamber pressure. Results indicated maximum static thrust augmentation (22%0 when the relatively unmixed primary and secondary streams were diffused immediately after the secondary inlet and then allowed to complete mixing in a constant area duct, for a total afterburner length of about six inlet diameters.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1975
Accession Number
ADA017458

Entities

People

  • Carl H. Steiling Jr

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Barometric Pressure
  • Coefficients
  • Combustion
  • Data Reduction
  • Equations
  • Exhaust Gases
  • Measurement
  • Plastic Explosives
  • Pressure Transducers
  • Rocket Engines
  • Rocket Exhaust
  • Secondary Flow
  • Specific Impulse
  • Strain Gages
  • Test Equipment

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.