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

Abstract

The report describes the test results of a supersonic axial flow compressor stage with a tip Mach number of 2.0. Volume I discusses especially the inlet stall, the associated flow field and the stage performance. Methods are proposed to eliminate the stall problem. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1972
Accession Number
AD0752585

Entities

People

  • Frans A. E. Breugelmans

Organizations

  • von Kármán Institute for Fluid Dynamics

Tags

DTIC Thesaurus Topics

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

Fields of Study

  • Physics

Readers

  • Aerodynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow