APPLICATION OF THEORETICAL DESIGN METHODS TO STUDY THE PERFORMANCE LIMITS OF AIRFOILS IN CASCADE

Abstract

A method of designing airfoils in cascade by means of conformal transformations is discussed. Design of these airfoils is regulated by five independent input parameters, with solutions obtained by digital computer. A large number of cascades generated by this method are compared. To evaluate the limits of performance, a parameter to indicate the tendency toward flow separation is introduced, with a limiting value established and verified. Proper solidity is shown to be of great importance in achieving low values of this separation parameter. The value of proper solidity for a given blade thickness is shown to be relatively independent of fairing shape. To increase performance, reducing blade thickness with a corresponding increase in solidity is shown to yield much greater improvement than changes in fairing shape.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1963
Accession Number
AD0481677

Entities

People

  • John E. Jenista

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • C4I
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Computer Programs
  • Computers
  • Diffusion
  • Digital Computers
  • Experimental Data
  • Flow
  • Flow Separation
  • Fluid Dynamics
  • Layers
  • Leading Edges
  • Pressure Distribution
  • Pressure Gradients
  • Stagnation Point
  • Thickness
  • Trailing Edges

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Phased Array Antenna Design.
  • Regression Analysis.