Performance of NACA Eight-Stage Axial-Flow Compressor Designed on the Basis of Airfoil Theory

Abstract

The design basis for each compressor stage was a symmetrical velocity diagram and an axial component of velocity constant with respect to radius. The compressor was tested over range of speeds from 5000 to 14000 rpm with varying air flow at each speed. Adiabatic temperature-rise efficiency of 87% at a pressure ratio of 3.42 and an inlet volume flow of 129 cfs was obtained. Results show that multistage axial-flow compressors can be designed by application of the airfoil theory.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1944
Accession Number
ADB804366

Entities

People

  • John T. Sinnette
  • Julia A. King
  • Oscar W. Schey

Organizations

  • Glenn Research Center

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Air Flow
  • Aircraft Engines
  • Aircrafts
  • Axial Flow
  • Axial Flow Compressors
  • Compressors
  • Engines
  • Flow
  • Fluid Dynamics
  • Gas Turbines
  • Heat Transfer
  • Mach Number
  • Measurement
  • Physical Properties
  • Pressure Distribution
  • Pressure Measurement
  • Static Pressure

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Internal Combustion Engine (ICE) Technology.
  • Materials Science