Friction in Pipes at Supersonic and Subsonic Velocities

Abstract

Apparent friction coefficient in pipes at subsonic and supersonic velocities was experimentally determined. In supersonic flow, results were found to be strongly influenced by presence of oblique shocks formed at junction of nozzle and pipe. Nozzle forms were devised which eliminated shocks and their effects. At distance from inlet greater than 50 diameters, apparent friction coefficient for compressible flow at Mach numbers greater than 1 is approximately equal, and for equal Reynolds Numbers, coefficient of friction for incompressible flow with completely developed boundary layer is equal.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1945
Accession Number
ADA801266

Entities

People

  • Ernest Neumann
  • Joseph. H. Keenan

Organizations

  • Massachusetts Institute of Technology

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Coefficients
  • Compressible Flow
  • Fluid Dynamics
  • Fluid Flow
  • Hydrodynamics
  • Incompressible Flow
  • Layers
  • Mach Number
  • Measurement
  • Mechanical Engineering
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Subsonic Flow
  • Supersonic Flow

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow