Low Reynolds Number Turbine Blade Cascade Calculations.

Abstract

Computations of the velocity fields for Langston turbine blade cascades with solidities of 1.075 and 0.84 have been carried out at Reynolds numbers of 50K, 100K, 200K, 441K, 1000K, and 2000K. A second cascade investigated at Reynolds numbers of 50K and 100K uses the Langston airfoil which has been modified by extending the trailing edge, resulting in a solidity of 0.786. The computations were performed with Allison's Blade Vanc Interaction code. Computational results are presented for transition, separation, and reattachment.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1996
Accession Number
ADA312466

Entities

People

  • Elizabeth Ervin
  • Michael Dahlstrom
  • Richard Rivir
  • Rolf Sondergaard

Organizations

  • Wright Laboratory

Tags

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Computational Fluid Dynamics
  • Engines
  • Flow
  • Fluid Dynamics
  • Governments
  • Mechanical Engineering
  • Reynolds Number
  • Skin Friction
  • Steady State
  • Trailing Edges
  • Transitions
  • Turbine Blades
  • Turbines
  • Turbomachinery
  • United States Government

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Mechanics and Fluid Dynamics.