A COMPACT THRUST AUGMENTING EJECTOR EXPERIMENT.

Abstract

The report briefly reviews the potential momentum thrust performance of ejectors. In addition to thrust performance, an ejector's utility to a V/STOL propulsion system is determined by several other factors including ejector size and airducting requirements. A survey of previous ejector experimental results are presented for ejectors with inlet area ratios in the neighborhood of 15 to 20. A compact two-dimensional ejector experiment with an inlet area ratio of 19 is described. This ejector with a 1.9 area ratio exit diffuser achieved a thrust augmentation ratio of 1.71 and 1.78 for an ejector length to minimum channel width ratio of 3.5 and 5.1 respectively. It is believed that improvements in primary injection techniques were responsible for this favorable thrust performance. (Author)

Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1970
Accession Number
AD0713634

Entities

People

  • Richard B. Fancher

Organizations

  • Air Force Research Laboratory

Tags

DTIC Thesaurus Topics

  • Diffusers
  • Engineering
  • Engines
  • Mechanical Engineering
  • Momentum
  • Physical Properties
  • Propulsion System Components
  • Propulsion Systems
  • Thrust
  • Thrust Augmentation
  • Two Dimensional

Readers

  • Combustion and Flow Dynamics.
  • Systems Analysis and Design