Large Eddy Simulation of a Supersonic Cavity Flow with an Unstructured Grid Flow Solver

Abstract

Large Eddy Simulation methods were implemented in a hexahedral based unstructured grid flow solver and tested for the analysis of transonic flow over an open cavity. This approach was developed for efficient application of Computational Fluid Dynamics methods to the highly unsteady flows in a geometrically complex weapons bay. A compressible sub grid scale model was implemented. The compressible flow solver uses an upwind flux difference splitting scheme. A Mach 1.2 flow over an open cavity was simulated. Comparisons of computed and experimental spectra of the sound pressure level at several locations in the cavity are presented. Good agreements between the simulations and test were obtained.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 2001
Accession Number
ADP013701

Entities

People

  • Brian R. Smith

Organizations

  • Lockheed Martin Aeronautics

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes
  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Acoustic Waves
  • Boundaries
  • Boundary Layer
  • Channel Flow
  • Computational Science
  • Demographic Cohorts
  • Flow
  • Flow Fields
  • Large Eddy Simulation
  • Layers
  • Leading Edges
  • Reynolds Number
  • Simulations
  • Turbulent Boundary Layer
  • Turbulent Mixing
  • Walls

Fields of Study

  • Physics

Readers

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

Technology Areas

  • Hypersonics