Transonic Noise Generation by Duct and Profile Flow.

Abstract

To study the strong sound generation in the case of helicopter rotor vortex interaction, a vortex profile flow interaction experiment is performed in a transonic duct. Vortices are generated upstream of a NACA 0012 profile and the pressure and density fields are analyzed using digital signals processing methods and digital interferogram evaluation techniques. One of the current results is that a separation bubble is formed at the leading edge of the wing when the vortex passes over the profile. The complicated flow at the boundary of the profile seems to be one of the keys to the understanding of vortex profile interaction. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1983
Accession Number
ADA129367

Entities

People

  • F. Becker
  • G. E. A. Meier
  • R. Timm

Tags

Communities of Interest

  • Energy and Power Technologies
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Data Processing
  • Digital Signal Processing
  • Flow
  • Fluid Flow
  • Frequency
  • Geometry
  • Image Processing
  • Interferograms
  • Leading Edges
  • Measurement
  • Pressure Measurement
  • Pressure Transducers
  • Test And Evaluation
  • Two Dimensional
  • Vortex Generators

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.