Data for Design of Entrance Vanes from Two-Dimensional Tests of Airfoils in Cascade

Abstract

Data obtained from tests of five NACA blower-blade sections and four experimentally driven sections are presented in the form of entrance vane design charts for axial-flow compressors or turbines. These charts give blade section and angle of attack for any turning angle. Blades thus obtained operate with peak-free pressure distributions. These series of blower-blade sections, with relatively high critical speeds, will efficiently turn air flowing in an axial direction from 0 to 80 deg.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1945
Accession Number
ADA800865

Entities

People

  • Charles M. Zimmey
  • Viola M. Lappi

Organizations

  • Langley Research Center

Tags

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aeronautics
  • Air Flow
  • Axial Flow
  • Axial Flow Compressors
  • Boundary Layer
  • Coefficients
  • Dynamic Pressure
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Geometry
  • Measurement
  • Pressure Distribution
  • Static Pressure
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.