Internal Aerodynamics of Turbojet Test Cells

Abstract

Elliptic computer codes have been developed (including plot routines) which can be used to study the flow field in test cells and exhaust stacks and in the augmenter tube for low thrust operation. The effects of engine-augmenter spacing, augmenter diameter and inlet design, aft cell wall location, test cell by-pass ratio, cell inlet conditions and stack-augmenter geometry on the flow field and augmenter pressure rise have been calculated. The models appear to be qualitatively correct and adequate for their intended purposes but model validation with experiment is required. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1976
Accession Number
ADA035253

Entities

People

  • David W. Netzer
  • Glendon C. Speakman
  • Jack D. Hayes

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Afterburners
  • Boundary Layer
  • Cellular Structures
  • Chemical Reactions
  • Equations
  • Exhaust Gases
  • Flow Fields
  • Flow Rate
  • Geometry
  • Jet Aircraft
  • Jet Engines
  • Kinetic Energy
  • Mass Flow
  • Navy
  • Payload
  • Turbofan Engines
  • Two Dimensional

Readers

  • Combustion and Flow Dynamics.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster