INVESTIGATION OF A ONE STAGE AXIAL FLOW SUPERSONIC COMPRESSOR, PART 1. GLOBAL PERFORMANCE OF THE BLUNT TRAILING EDGE BLADE ROTOR R 32,

Abstract

Overall performance tests of supersonic rotor with blunt trailing edge blades were carried out at air-equivalent tip speeds up to 430.m/sec. All tests were conducted in Freon-12-air mixture. The rotor has a 40 cm tip diameter and a constant hub-tip ratio of 0.85. No inlet guide vanes or stator were used. The overall performance, as obtained from detailed surveys taken downstream of the rotor, are presented under the form of mass weighted values. (Author)

Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1965
Accession Number
AD0666391

Entities

People

  • Fr. Breugelmans

Organizations

  • von Kármán Institute for Fluid Dynamics

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Axial Flow
  • Compressors
  • Diameters
  • Flow
  • Guide Vanes
  • Inlet Guide Vanes
  • Inlets
  • Performance Tests
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Aerodynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow