Turbulent Flow Separation Ahead of Forward Facing Steps in Supersonic Two-Dimensional and Axisymmetric Flows

Abstract

Pressure distributions in the separated flow region ahead of forward facing steps and on the step face in supersonic turbulent flows obtained at VKI are compared with those found by previous investigators. Parameters such as step height, unit Reynolds number and Mach number were compared. It was intended, in particular, to relate the axisymmetric results to existing two-dimensional data. A general law relating the variation of the step pressure integral with Mach number was found by analyzing pressure distributions on the step face. The influence of flow inclination, Mach number variation and three-dimensional effects on the characteristic pressures were discussed. The flow has been visualized by schlieren and shadow photographs and by the oil flow technique.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1969
Accession Number
AD0860314

Entities

People

  • H. T. Uebelhack

Organizations

  • von Kármán Institute for Fluid Dynamics

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Angle Of Incidence
  • Boundary Layer
  • Flow Separation
  • Flow Visualization
  • Fluid Dynamics
  • Geometry
  • Mach Number
  • Pressure Distribution
  • Reynolds Number
  • Shock Waves
  • Stagnation Pressure
  • Test Facilities
  • Three Dimensional
  • Turbulent Flow
  • Turbulent Mixing
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.
  • Systems Analysis and Design

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow