Application of S1BYL2 to the AGARD WG18 Compressor Test Cases

Abstract

S1BYL2 is an inviscid-viscous blade-to-blade method for calculating the detailed aerodynamics and overall performance of compressor blades. It may be applied either on its own to predict the flow for individual blade sections, such as the mid span of a linear cascade, or in conjunction with a throughflow calculation to predict the performance of a complete axial compressor. A previous AGARD paper by the author described applications of S1BYL2 to most of the compressor cascade test cases which have subsequently been selected by AGARD Working Group 18: generally good agreement was obtained. This current paper presents new predictions for the V2 and ARL SL19 cascades and for the high speed compressor cases.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1991
Accession Number
ADA237559

Entities

People

  • W. J. Calvert

Organizations

  • Royal Aircraft Establishment

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Aspect Ratio
  • Boundary Layer
  • Compressor Blades
  • Computational Fluid Dynamics
  • Curvature
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Geometry
  • Layers
  • Leading Edges
  • Mach Number
  • Mass Flow
  • Shock Waves
  • Static Pressure
  • Trailing Edges
  • Viscous Flow

Readers

  • Academic Conference Management
  • Aerodynamics.
  • Computational Modeling and Simulation