Method of Analysis for Compressible Flow Past Arbitrary Turbomachine Blades on General Surface of Revolution

Abstract

A method of obtaining the flow of a nonviscous compressible fluid past arbitrary compressor or turbine blades between two neighboring surfaces of revolution is presented. The equations of continuity and motion obtained for such flow are combined into a nonlinear second- order differential equation in terms of a stream function defined for such flow. Numerical solution by the use of differentiation coefficients for unequally spaced grid points is suggested. Means for satisfying the boundary conditions outside the channel and solutions by the relaxation method with manual computation and by a matrix method with a large-scale digital computing machine are described.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1951
Accession Number
ADA382096

Entities

People

  • Chung-hua Wu
  • Curtis A. Brown

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Axial Flow
  • Compressible Flow
  • Curvature
  • Difference Equations
  • Differential Equations
  • Equations
  • Experimental Data
  • Flow
  • Fluid Flow
  • Gas Turbines
  • Mach Number
  • Mass Flow
  • Shape
  • Trailing Edges
  • Turbine Blades
  • Turbines
  • Two Dimensional

Fields of Study

  • Mathematics

Readers

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

Technology Areas

  • Space
  • Space - Hall-Effect Thruster