Research on the Flutter of Axial Turbomachine Blading,

Abstract

The unsteady response of a flat plate airfoil to large nonpotential flow disturbances is evaluated in the form of a translating rectangular grid of eddy-array. The singularity distribution principle in combination with the time-marching technique was used as the method of analysis. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1976
Accession Number
ADA031536

Entities

People

  • F. Sisto
  • P. V. K. Perumal

Organizations

  • Stevens Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Boundary Layer
  • Computer Programs
  • Engineering
  • Engineers
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Kernel Functions
  • Leading Edges
  • Mechanical Engineering
  • Military Research
  • Physics Laboratories
  • Trailing Edges
  • Vortices

Fields of Study

  • Physics

Readers

  • Aerodynamics.