Investigation of the Mechanism of Transonic Shock Wave/Boundary Layer Interactions Using a Navier-Stokes Analysis.

Abstract

The present report discusses the development of a time-dependent Navier-Stokes code for use in predicting transonic shock-wave boundary layer interaction. In addition, various test cases which have been performed are discussed. The algorithm used to solve the equations is based upon the consistently split linearized block implicit method of Briley and McDonald (15, 16). The philosophy and use of a solution adaptive mesh is also described. The test cases studied in this report are: normal shock wave boundary layer interaction in a constant area circular pipe, steady transonic flow over an axisymmetric bump, unsteady flow over an axisymmetric bump, supersonic flow over an axisymmetric compression corner and oblique shock wave impingement on a flat plate boundary layer. (Author)

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1984
Accession Number
ADA141551

Entities

People

  • D. V. Roscoe
  • H. J. Gibeling
  • H. Mcdonald
  • S. J.. Shamroth

Tags

Communities of Interest

  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boltzmann Equation
  • Boundary Layer
  • Boundary Layer Flow
  • Computational Fluid Dynamics
  • Convection
  • Coordinate Systems
  • Flow Fields
  • Fluid Dynamics
  • Geometry
  • Heat Transfer
  • Navier Stokes Equations
  • Pressure Distribution
  • Pressure Gradients
  • Shock
  • Steady Flow
  • Two Dimensional
  • Viscous Flow

Fields of Study

  • Physics

Readers

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

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers