Navier-Stokes Simulation of Unsteady Three-Dimensional Blade-Vortex Interactions

Abstract

The unsteady, viscous, three-dimensional flow field of a helicopter rotor blade encountering a passing vortex is calculated by solving the thin layer Navier-Stokes equations by a finite-difference numerical procedure. A prescribed vortex method is adopted to preserve the structure of the interacting concentrated vortex. The test cases considered correspond to the experimintal model rotor test conditions.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1988
Accession Number
ADA209116

Entities

People

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

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Abstracts
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Differential Equations
  • Engineering
  • Equations
  • Flow
  • Fluid Dynamics
  • Free Stream
  • Grids
  • Navier Stokes Equations
  • Partial Differential Equations
  • Shock Waves
  • Simulations
  • Three Dimensional
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Fluid Mechanics and Fluid Dynamics.