Influence of Wall Boundary Layer upon the Performance of an Axial-Flow Fan Rotor

Abstract

An experimental investigation has been conducted to determine the effects of the wall boundary layer upon the performance of an axial flow fan rotor. Tests were conducted at low Mach numbers and at one blade angle on a fan designed to have uniform downstream tangential velocity. The maximum disturbed-flow region of the six boundary-layer configurations tested exceeded one-half of the annular width of the duct and the peak efficiency was reduced 2-1/2% percent for this condition. The over-all loss in efficiency may possibly be reduced by decreasing the blade pitch angle in the boundary-layer region to conform to the upstream velocity profile.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1951
Accession Number
ADA381953

Entities

People

  • Emanuel Boxer

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Air Flow
  • Axial Flow
  • Axial Flow Fans
  • Blades
  • Boundaries
  • Boundary Layer
  • Boundary Layer Flow
  • Clearances
  • Compressors
  • Dynamic Pressure
  • Fans
  • Flow
  • Flow Fields
  • Layers
  • Mach Number
  • Static Pressure

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.
  • Mathematics or Statistics