Separation Ahead of Protuberances in Supersonic Turbulent Boundary Layers.

Abstract

The data were obtained using the optical-surface indicator technique of visualizing the flow; its accuracy and reproducibility are discussed. The protuberances are immersed in the boundary layer on the wall of a supersonic wind tunnel. The relative importance of various non-dimensional groups is evaluated. The variation of primary separation distance is presented as a function of obstacle dimensions, Mach number, and Reynolds number, the last being the least significant. These results do not support some scaling laws found in the literature. An alternative correlation is proposed which applies to both small and large cylindrical protuberances. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1977
Accession Number
ADA037347

Entities

People

  • Clarence W. Kitchens Jr.
  • Raymond Sedney

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Aircrafts
  • Boundary Layer
  • Bow Shock
  • Engineering
  • Flow Visualization
  • Fluid Dynamics
  • Free Stream
  • Heat Transfer
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Turbulent Boundary Layer
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow