Large-Eddy Simulation of the Tip-Flow of a Rotor in Hover

Abstract

The blade-tip vortex is one of the most important aerodynamic feature of a helicopter rotor wake, The strength, size, location and orientation of the tip vortices affect the blade loads and rotor performance. The overall goal of the current project was to develop a large-eddy simulation (LES) capability to simulate the rotor-tip vortex and use these simulations to perform a detailed analysis of the dynamics of this flow, The specific objectives of this research project are (1) Develop a LES based computational approach for simulating the tip flow of a rotor in hover. (2) Validate the computational approach against PIV measurements of a hovering rotor (3) Use the solver to gain insight into the formation, structure and downstream evolution of the tip-vortex and the dynamics of the turbulence associated with the tip vortex.

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Document Details

Document Type
Technical Report
Publication Date
Oct 28, 2005
Accession Number
ADA440555

Entities

People

  • Rajat Mittal

Organizations

  • George Washington University

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Airfoils
  • Airframes
  • Base Pressure
  • Blade Tips
  • Boundary Layer
  • Compressible Flow
  • Flow
  • Fluid Flow
  • Large Eddy Simulation
  • Mach Number
  • Reynolds Number
  • Simulations
  • Three Dimensional
  • Trailing Edges
  • Turbulent Mixing
  • Two Dimensional
  • Wing Tips

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Computational Fluid Dynamics (CFD)
  • Fluid Mechanics and Fluid Dynamics.