Technology for Sustained Supersonic Combustion Task Order 0006: Scramjet Research with Flight-Like Inflow Conditions

Abstract

This report focuses on the impact of shock distortion on various high-speed flows for scramjet applications. Simulations consist of shocked sonic injection into a supersonic crossflow, shock distorted cavity-assisted fuel mixing and combustion, and novel experimental designs. Hybrid large eddy simulation/Reynolds-averaged Navier-Stokes (LES/RANS) turbulence modeling techniques are highlighted and their ability to capture the unsteady nature of high-speed turbulent flows is investigated. This task provided extended experience and knowledge of using hybrid LES/RANS techniques for internal high-speed flows. These results also will provide valuable information for better understanding the complicated physics of shock boundary layer interactions and mixing in high-speed flows in detail that experiments cannot easily provide.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 2013
Accession Number
ADA586382

Entities

People

  • John Boles
  • Ryan O Milligan

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Boundary Layer
  • Chemical Reactions
  • Combustion
  • Computational Fluid Dynamics
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Generators
  • Ignition
  • Large Eddy Simulation
  • Laser Induced Fluorescence
  • Simulations
  • Supersonic Combustion
  • Supersonic Combustion Ramjet Engines
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

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

Technology Areas

  • Hypersonics