Computations of Three-Dimensional Unsteady Supersonic Cavity Flow to Study the Effect of Different Downstream Geometries

Abstract

Computations of three-dimensional unsteady supersonic cavity flow are performed for a free-stream Mach number of 1.2. Two cavity geometries are considered: (i) a simple rectangular cavity of length-to-depth (L/D) and length-to-width (L/W) ratios of 4.5, and (ii) a cavity with a 450 ramp attached to the downstream wall of the simple rectangular cavity. Two flow models for computing the cavity flow field are assessed: (a) the Reynolds-Averaged Navier-Stokes (RANS) equations with a kappa-omega- turbulence model for the whole flow field, and (b) a combination of an inviscid flow model using the Euler equations for the domain outside the boundary layer and the RANS model for the boundary layer. The structures of the flow fields resulting from the different models are observed. The effect of the different downstream geometries is assessed.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 2003
Accession Number
ADP014111

Entities

People

  • B. I. Soemarwoto
  • J. C. Kok

Organizations

  • National Aerospace Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircraft Equipment
  • Boundary Layer
  • Computational Fluid Dynamics
  • Equations
  • Euler Equations
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Free Stream
  • Frequency
  • Geometry
  • Leading Edges
  • Sound Pressure
  • Static Pressure
  • Three Dimensional
  • Trailing Edges
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.
  • Marine Propulsion Engineering and Naval Architecture

Technology Areas

  • Hypersonics