EXPERIMENTAL INVESTIGATION OF TWO BLUNT TRAILING EDGE SUPERSONIC COMPRESSOR ROTORS OF DIFFERENT BLADE THICKNESSES AND WITH CIRCULAR ARC CAMBER LINE

Abstract

Two configurations of blunt-trailing-edge supersonic compressor blades were tested with air in a compressor rig. The performance of these blades was investigated over the speed range from 50 to 100 percent of design speed. The performance of the two blade configurations is compared, and the effect of the modifications between the two configurations is evaluated.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1968
Accession Number
AD0674743

Entities

People

  • A. J. Wennerstrom
  • C. T. Carman
  • J. R. Myers
  • John W. Steurer

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Sensors
  • Space

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Back Pressure
  • Boundary Layer
  • Compressor Blades
  • Compressor Rotors
  • Compressors
  • Engineering
  • Fluid Dynamics
  • Instrumentation
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Static Pressure
  • Three Dimensional
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Aerodynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow