Supersonic Turbulent Fuel-Air Mixing and Evaporation

Abstract

This report results from a contract tasking American University of Beirut as follows: The contractor will numerically investigate turbulent fuel- air mixing in a supersonic stream. The fuel injection angle will be varied from 0 to go degrees (relative to the air stream) and the air stream Mach number will be varied from 2 to 5. A finite volume pressure based method capable of modeling turbulent multi-phase flow at all speeds will be developed and used. The convergence rate will be accelerated using a full non-linear multi-grid method. The discretization will use a second order scheme for diffusion and a pseudo-third order bounded scheme for convection. Turbulence will be modeled using two-equation models (k-e. k-w, and SST) with suitable modifications to account for interaction between the phases. A comparison with available experimental and numerical results will be performed.

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Document Details

Document Type
Technical Report
Publication Date
Oct 20, 2003
Accession Number
ADA426899

Entities

People

  • Fadi Moukalled

Organizations

  • American University

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Boltzmann Equation
  • Boundary Layer
  • Computational Fluid Dynamics
  • Convection
  • Differential Equations
  • Diffusion
  • Equations
  • Fluid Dynamics
  • Fluid Flow
  • Gas Flow
  • Heat Of Vaporization
  • Heat Transfer
  • Latent Heat
  • Mach Number
  • Physical Properties
  • Pressure Distribution
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow