BLUNT TRAILING EDGE BLADING STUDIES IN LOW AND HIGH SPEED FLOWS.

Abstract

The report covers first cascade calculations and testing on blunt trailing edge blades in the subsonic range. First, improvement on a potential flow method is described, and the results of calculations are compared with cascade tunnel data. Fair agreement is obtained. A boundary layer correction was also applied with moderate success. Exploratory studies of the dump diffusion region are reported. Application of the blunt trailing edge blade concept to the low Re number range is then discussed, and the first experimental data bearing on pitch chord ratio optimization are reported. Finally, the essential features of two supersonic compressor stages are discussed. (Author)

Document Details

Document Type
Technical Report
Publication Date
Mar 31, 1970
Accession Number
AD0709472

Entities

People

  • F. Breugelmans
  • H. Griepentrog
  • H. Rottiers
  • Joë-Marc Chauvin

Organizations

  • von Kármán Institute for Fluid Dynamics

Tags

DTIC Thesaurus Topics

  • Agreements
  • Boundaries
  • Boundary Layer
  • Compressors
  • Diffusion
  • Experimental Data
  • Flow
  • Layers
  • Potential Flow
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.
  • Systems Analysis and Design

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow