Acoustic Propagation Using Computational Fluid Dynamics,

Abstract

The propagation characteristics of several helicopter airfoil profiles have been investigated using the transonic small disturbance equation. A test case was performed to generate a moving shock that propagated off the airfoil. Various grids were then examined to determine their ability to accurately capture these propagating shock waves. Finally, the case of airfoil vortex interactions was thoroughly studied over a wide range of Mach numbers and airfoil shapes with particular emphasis on the transonic regime; this results in a highly complicated fluctuation of lift, drag, and pitching moment. The calculated acoustic intensity levels, along with the details of the computational flow field, provide new insights into the understanding of transonic airfoil vortex interactions.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1986
Accession Number
ADA172310

Entities

People

  • G. R. Srinivasan
  • J. D. Baeder
  • W. J. Mccroskey

Organizations

  • United States Army Aviation and Missile Command

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Acoustic Propagation
  • Acoustic Waves
  • Acoustics
  • Computational Fluid Dynamics
  • Equations
  • Far Field
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Fluid Mechanics
  • Helicopters
  • Mach Number
  • Near Field
  • Shock Waves
  • Square Roots
  • Three Dimensional
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Acoustical Oceanography.
  • Aerodynamics/Aeronautics.
  • Computational Fluid Dynamics (CFD)