Large Eddy Simulation of Supersonic Compression Corner Using ENO Scheme

Abstract

A Large Eddy Simulation of a 25 deg compression corner at M = 2.88 and Re(delta) - 2 x 10(exp 4) is performed using an Essentially Non Oscillatory (ENO) scheme. The Favre filtered compressible Navier-Stokes equations are solved using a Monotone Integrated Large Eddy Simulation (MILES) technique on an unstructured grid of tetrahedral cells. The mean flow variables and turbulent shear stress at the incoming flow are in good agreement with experiment and DNS. The separation length scaled by the characteristic scale shows agreement with the experiment. No pronounced pressure plateau is observed compared with experiment at higher Reynolds number.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 2001
Accession Number
ADP013655

Entities

People

  • Alexander A. Zheltovodov
  • Doyle Knight
  • Hong Yan

Organizations

  • Rutgers University Department of Mechanical and Aerospace Engineering

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Applied Mechanics
  • Boundary Layer
  • Coefficients
  • Computational Fluid Dynamics
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Large Eddy Simulation
  • Layers
  • Mechanical Properties
  • Mechanics
  • Reynolds Number
  • Shock Waves
  • Skin Friction
  • Turbulent Boundary Layer
  • Turbulent Flow
  • Two Dimensional

Fields of Study

  • Physics

Readers

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

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow