Method of Designing Cascade Blades with Prescribed Velocity Distributions in Compressible Potential Flows,

Abstract

By use of the assumption that the pressure-column relation is linear, a solution to the problem of designing a cascade for a given turning and with a prescribed velocity distribution along the blade in a potential flow of a compressible perfect fluid was obtained by the method of correspondence between potential flows of compressible and incompressible fluids. The designing of an isolated airfoil with a prescribed velocity distribution along the airfoil is considered as a special case of the cascade. If the prescribed velocity distribution is not theoretically attainable, the method provides a means of modifying the distribution so as to obtain a physically significant blade shape. Numerical examples are included.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1950
Accession Number
ADA298728

Entities

People

  • George R. Costello

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aeronautics
  • Aspect Ratio
  • Boundary Layer
  • Coefficients
  • Complex Variables
  • Compressible Flow
  • Dynamic Pressure
  • Equations
  • Flow
  • Free Stream
  • Incompressible Flow
  • Leading Edges
  • Potential Flow
  • Reynolds Number
  • Stagnation Point
  • Trailing Edges

Readers

  • Aerodynamics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)