Unsteady Interaction of a Rotor with a Vortex

Abstract

The unsteady, three-dimensional flow field of a helicopter rotor blade encountering a passing vortex is calculated by solving the Euler/thin layer Navier-Stokes equations by a finite difference numerical procedure. A prescribed vortex method is adopted to preserve the structure of the interacting vortex. The cases considered for computation correspond to the experimental model rotor test conditions and consist of parallel and oblique interactions. Comparison of the numerical results with test data show good agreement for both parallel and oblique interactions at subsonic and transonic tip speeds. Keywords; Unsteady; Euler; Navier Stokes; Oblique blade vortex interaction; Reprints.

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Document Details

Document Type
Technical Report
Publication Date
Jun 14, 1989
Accession Number
ADA211180

Entities

People

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

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Airfoils
  • Airframes
  • Boundary Layer
  • Computational Fluid Dynamics
  • Differential Equations
  • Equations
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Helicopter Rotors
  • Helicopters
  • Navier Stokes Equations
  • Partial Differential Equations
  • Pressure Distribution
  • Three Dimensional
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Computational Fluid Dynamics (CFD)
  • Fluid Mechanics and Fluid Dynamics.