COMPUTER ANALYSIS OF THE RELATIVE FLOW IN THE BLUNT-TRAILING-EDGE SUPERSONIC COMPRESSOR BLADING.

Abstract

The computer program presented was designed specifically for the analysis of the blunt-trailing-edge supersonic compressor. Beginning with flow property measurements obtained in a nonrotating coordinate system, streamtube boundaries are determined at each measuring plane. Then mass-averaged values of the flow properties in each streamtube are translated to a coordinate system rotating with the compressor rotor, and a particular one-dimensional flow model is imposed on each streamtube to describe the flow process through the rotor. The flow model includes analysis of shock loss and sudden expansion loss leading to an estimate of the additional loss occurring within the flow field of the rotor. Various other calculations are presented which are aimed at the analysis of data for accuracy and consistency.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1969
Accession Number
AD0686406

Entities

People

  • J. W. Salvage

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Compressors
  • Computers
  • Coordinate Systems
  • Diffusion
  • Enthalpy
  • Equations
  • Flow
  • Geometry
  • Mach Number
  • Mass
  • Measurement
  • Specific Heat
  • Static Pressure
  • Trailing Edges
  • Virtual Reality

Fields of Study

  • Physics

Readers

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

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow