Pressure Interactions in Supersonic Combustion.

Abstract

A detailed assessment of supersonic combustion was carried out to identify specific research requirements in modeling turbulent reacting supersonic flows. The direct effects of pressure gradients and pressure fluctuations on turbulence were found to be potentially responsible for certain of the trends in turbulent transport and mixing rates that are observed in supersonic flows. An approach to the modeling of these phenomena is delineated, A modular model computer code for the analysis of sudden expansion (dump) combustors was prepared. This modular model is designed to be used parametrically in evaluating effects such as chemical kinetics limitation on flame stabilization and combustion efficiency in integral rocket ramjet and ducted rocket combustors. Keywords: Pressure Interactions, Turbulence modeling, Sudden expansion combustors, Dump combustors.

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Document Details

Document Type
Technical Report
Publication Date
Jun 11, 1986
Accession Number
ADA172711

Entities

People

  • R. B. Edelman
  • W. N. Bragg

Organizations

  • Leidos

Tags

Communities of Interest

  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force Facilities
  • Boundary Layer
  • Burning Rate
  • Chemical Reactions
  • Combustion
  • Computational Fluid Dynamics
  • Fluid Dynamics
  • Heat Transfer
  • Ignition Lag
  • Integral Rocket Ramjets
  • Pressure Distribution
  • Ramjet Engines
  • Rocket Ramjets
  • Supersonic Combustion
  • Supersonic Combustion Ramjet Engines
  • Turbulent Mixing
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Combustion science or combustion engineering.
  • Computational Fluid Dynamics (CFD)

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight