Isolated and Cascade Airfoils with Prescribed Velocity Distribution

Abstract

The problem of increasing the output per stage in axial flow compressors and turbines involves the use of high-solidity (closely spaced blades) stages of highly cambered blades. In addition, the velocity distribution must be carefully selected as a function of arc length along the airfoil (blade section) boundary in order to avoid flow separation or excessively high local velocities. Several methods are available for obtaining an airfoil with a prescribed velocity distribution. The methods that lead to theoretically exact results are based on conformal-mapping theory.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1947
Accession Number
ADA298727

Entities

People

  • Arthur W. Goldstein
  • Meyer Jerison

Organizations

  • Glenn Research Center

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aeronautics
  • Air Force
  • Aircrafts
  • Aspect Ratio
  • Axial Flow Compressors
  • Conformal Mapping
  • Flow
  • Leading Edges
  • Mechanics
  • New York
  • Potential Flow
  • Pressure Distribution
  • Reynolds Number
  • Stagnation Point
  • Trailing Edges
  • United States

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Educational Psychology
  • Fluid Dynamics.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster