TURBULENT BOUNDARY LAYER SEPARATION AHEAD OF CYLINDRICAL PROTUBERANCES IN SUPERSONIC FLOW

Abstract

The results of an experimental study of separation distances ahead of right circular cylinders mounted perpendicular to a flat plate are presented. The tests were conducted in a supersonic wind tunnel at a nominal test Mach number of 4.8. Turbulent boundary layer conditions existed at the cylinder mounting position. All tests were for single cylinder configurations. The cylinders tested ranged in length from 1/16 in to 1 1/2 in. and in diameter from 3/16 in. to 1 1/2 in. Experimental data were used to determine an empirical correlation between boundary layer separation distance and cylinder length. Comparison of results with other data sources showed the correlation in close agreement with previously observed boundary layer separation phenomena.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1969
Accession Number
AD0690947

Entities

People

  • James H. Mashburn

Organizations

  • University of Texas at Austin

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Dynamic Pressure
  • Fluid Dynamics
  • Fluid Mechanics
  • Free Stream
  • Hydrodynamics
  • Mach Number
  • Physics
  • Physics Laboratories
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Reynolds Number
  • Turbulent Boundary Layer
  • Turbulent Mixing
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow