Experimental Investigation of a Supersonic Compressor Cascade

Abstract

This report describes in detail the experimental investigation of a stationary, linear, supersonic compressor cascade with blades of constant spanwise geometry and constant thickness linear sidewalls. The selected blade element was representative of streamline 19 of an advanced compressor configuration resulting from the Aerospace Research Laboratories axial compressor research program. The investigation covered the range of inlet relative Mach numbers of 1.535 - 1.683 and a range of static pressure ratios of approximately 1.1 - 2.3 and included laser velocimeter measurements of the flow within and around the cascade at the design Mach number.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1975
Accession Number
ADA014395

Entities

People

  • George T. Sinnet
  • Robert B. Mcclure
  • Robert L. Holtman
  • Sanford Fleeter

Organizations

  • General Motors

Tags

Communities of Interest

  • Air Platforms
  • Human Systems
  • Space

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Boundary Layer
  • Computers
  • Data Reduction
  • Data Sets
  • Dynamic Pressure
  • Experimental Data
  • Fluid Dynamics
  • Fluid Mechanics
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Static Pressure
  • Supersonic Wind Tunnels
  • Three Dimensional
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering
  • Fluid Dynamics.

Technology Areas

  • Directed Energy
  • Hypersonics
  • Space
  • Space - Hall-Effect Thruster