A Compressible-Flow Plotting Device and Its Application to Cascade Flows

Abstract

A simplified method has been devised for the solution of two- dimensional compressible flows through well-defined passages. This method makes use of plastic cams which automatically set the length-to-width ratio of rectangles formed by streamlines and equipotential lines represented by spring-steel wires. Pressure distributions around four cascades of turbine blades and along the surface of a choked nozzle determined by this method are shown to compare well with experimental results.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1952
Accession Number
ADA380522

Entities

People

  • James C. Dunavant
  • Willard R. Westphal

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Boundary Layer
  • Compressible Flow
  • Dynamic Pressure
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Gas Turbines
  • Incompressible Flow
  • Mach Number
  • Potential Flow
  • Pressure Distribution
  • Shape
  • Trailing Edges
  • Turbine Blades
  • Turbines
  • Two Dimensional

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.