Numerical Studies of the Radiation Condition at the Inlet of a Transonic Compressor Blade Row.

Abstract

Finite-difference calculations of the flow in a transonic compressor blade row were carried out, using a radiation boundary condition at a plane upstream of the blades. These results show essentially no difference from a comparable set that were done using a uniform-flow approximation as the inlet boundary condition. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1980
Accession Number
ADA085978

Entities

People

  • Gregory F. Homicz
  • William J. Rae

Organizations

  • Calspan

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Boundaries
  • Coefficients
  • Compressor Blades
  • Compressors
  • Computational Fluid Dynamics
  • Flow Fields
  • Gas Turbines
  • Geometry
  • Grids
  • Leading Edges
  • Mach Number
  • Propulsion Systems
  • Radiation
  • Shock Waves
  • Three Dimensional
  • Turbines
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.