Numerical Analysis of an Axisymmetric Thrust Augmenting Ejector

Abstract

Use of an ejector is an effective way to increase the thrust produced by a jet. In this thesis project an axisymmetric ejector concept which had been previously explored by experiment was numerically modeled. An existing axisymmetric, internal flow code based on the explicit MacCormack method was modified to incorporate primary nozzle structure and flow injection within the flowfield. Results were compared qualitatively and quantitatively with experimental results to verify the validity of the model. Internal flow structure, difficult to obtain in experiment, is easily examined. This code may be used for parametric analysis of such ejector performance parameters as primary nozzle location, flow injection angle, diffuser area ratio, and inlet geometry to optimize future hardware configurations.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1990
Accession Number
ADA230555

Entities

People

  • Kenneth R. Gage

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Human Systems

DTIC Thesaurus Topics

  • Air Force
  • Annular Nozzles
  • Axisymmetric
  • Boundaries
  • Boundary Layer
  • Computational Fluid Dynamics
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Jet Flow
  • Nozzle Area Ratio
  • Nozzles
  • Numerical Analysis
  • Parametric Analysis
  • Secondary Flow
  • Short Takeoff Aircraft
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Computational Modeling and Simulation
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)