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

Abstract

The report describes the test results of a supersonic axial-flow compressor stage with a tip Mach number of 2.0. Volume 2 discusses a method to eliminate the inlet problem. Volume 3 describes the overall and detailed performance of the original model FB III with an interblade row bleed system. The bleed area represents 10% of the inlet area and a minimum bleed flow of 7% of the total inlet flow could be achieved. The stage performance data are presented for the 60% to 107% N over the square root of theta of the nominal speed. (Author)

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1972
Accession Number
AD0770648

Entities

People

  • Frans A. E. Breugelmans

Organizations

  • von Kármán Institute for Fluid Dynamics

Tags

DTIC Thesaurus Topics

  • Axial Flow
  • Axial Flow Compressors
  • Bleed Systems
  • Compressors
  • Flow
  • Hydraulic Equipment
  • Mach Number
  • Mathematics
  • Numbers
  • Pneumatic Equipment
  • Square Roots

Fields of Study

  • Physics

Readers

  • Aerodynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow