A Computational Study of a Supersonic Mixer-Ejector Exhaust System

Abstract

An analytical model of the mixer ejector based on a PNS solver approach has been applied to analyze the flowfield downstream of a supersonic mixer-ejector exhaust system. The method has been used previously to analyze the plume flowfield of unshrouded mixer-type nozzles as well as the flowfield within the mixing duct of a mixer-ejector exhaust system. Calculations are presented for a model-scale exhaust system operating at takeoff flight conditions. Favorable comparisons with total temperature and pressure experimental data are presented in the text. In addition parametric studies are presented examining the importance of turbulence level, streamwise vorticity, grid resolution, etc. on the downstream plume mixing characteristics. Finally, a series of calculations examining the effect of engine power setting (operating condition) and exhaust system size (full scale) axe analyzed.

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Document Details

Document Type
Technical Report
Publication Date
Nov 10, 1992
Accession Number
ADA258456

Entities

People

  • T. J. Barber

Organizations

  • United Technologies Corporation

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Creep
  • Cross Flow
  • Equations
  • Exhaust Nozzles
  • Exhaust Systems
  • Experimental Data
  • Flow
  • Flow Fields
  • Free Stream
  • Layers
  • Mach Number
  • Secondary Flow
  • Static Pressure
  • Turbulent Mixing
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Computational Fluid Dynamics (CFD)
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow