The Low Hub-Tip Ratio Supersonic Axial-Flow Compressor. Volume II.

Abstract

The report describes the test results of a supersonic axial-flow compressor stage with a tip Mach number of 2.0. This volume discusses a method to eliminate the inlet problem. (Author)

Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1972
Accession Number
AD0757217

Entities

People

  • Frans A. E. Breugelmans

Organizations

  • von Kármán Institute for Fluid Dynamics

Tags

DTIC Thesaurus Topics

  • Axial Flow
  • Axial Flow Compressors
  • Compressors
  • Flow
  • Mach Number
  • Pneumatic Equipment
  • Rotary Compressors

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Business Analytics

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow