An Investigation of the Flow in Turbojet Test Cell Augmenters

Abstract

A two-dimensional elliptic computer model was adapted to the solution of the flow field in a turbojet test cell section which contained the engine exhaust duct and augmenter tube. Various engine power settings, augmentation ratios, and augmenter geometries were investigated. Flow visualization and static pressure recovery were primary objectives subject to specified engine power settings and augmentation ratios. Capabilities and limitations of the model are discussed.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1975
Accession Number
ADA018193

Entities

People

  • Jack D. Hayes

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Dielectric Gases
  • Differential Equations
  • Exhaust Gases
  • Flow Fields
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Jet Engines
  • Payload
  • Pressure Gradients
  • Secondary Flow
  • Static Pressure
  • Turbojet Engines
  • Two Dimensional

Readers

  • Aerospace Test and Evaluation
  • Combustion and Flow Dynamics.