The Structure of Three-Dimensional Separated Flows in Obstacle-Boundary Layer Interactions.

Abstract

The subject is investigated with flow visualization techniques; the turbulent boundary layer on the wall of a continuous supersonic wind tunnel is used. Sizeable separated flow regions can be studied since the wall width is 38cm and the boundary layer is typically 2.5cm thick. The large scale of the experiment is required to resolve the fine details of the flow structure. The flow visualization techniques are discussed. The structure of the separated flow upstream of the obstacle is seen to change with relatively small changes in Reynolds number R; the number of vortices varies from 6 to 4 to 2 as R changes. Data are presented for large and small protuberances, but the latter are emphasized.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1975
Accession Number
ADA011254

Entities

People

  • Clarence W. Kitchens Jr.
  • Raymond Sedney

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Flow
  • Flow Visualization
  • Fluid Dynamics
  • Hydrodynamics
  • Jet Propulsion
  • Layers
  • Mach Number
  • Physics Laboratories
  • Reynolds Number
  • Supersonic Wind Tunnels
  • Three Dimensional
  • Turbulent Boundary Layer
  • Turbulent Mixing
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Atmospheric Science / Meteorology, specifically Wind Wave Turbulence.
  • Fluid Dynamics.
  • Systems Analysis and Design

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow