A Theoretical Study of Two Stage Thrust Augmenting Ejectors,

Abstract

The results of theoretical assessment of two stage thrust augmenting ejectors are presented and compared with those of single stage ejectors. The mixing ducts were of constant cross sectional area, the flows at the inlet and exit planes of each stage were assumed to be uniform, and friction effects were ignored. It was found that staging the ejector increases thrust augmentation at all primary jet stagnation pressures, but is more effective in the low pressure range and with high ejector area ratios for any gas combination. With a Hot Rocket-Air combination, the benefit of staging is much less than with an unheated Air-Air combination, and does not appear to be of practical use.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1984
Accession Number
ADA158857

Entities

People

  • A. M. Abdel-fattah

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air
  • Air Force
  • Aircrafts
  • Barometric Pressure
  • Computer Programs
  • Department Of Defense
  • Engineering
  • Flow
  • Fluid Dynamics
  • Fluid Mechanics
  • Mach Number
  • Mass Flow
  • Mechanical Engineering
  • Rocket Engines
  • Stagnation Pressure
  • Static Pressure
  • Thrust Augmentation

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.