Flowfield of a Lifting Hovering Rotor - a Navier-Stokes Simulation

Abstract

The viscous, three-dimensional flowfield of a lifting helicopter rotor in hover is calculated by using an upwind, implicit, finite-difference numerical method for solving the thin layer Navier-Stokes equations. The induced effects of the wake, including the interaction of blade tip vortices with successive blades, are calculated as a part of the overall flowfield solution without using any ad hoc wake models. Comparison of the numerical results for the subsonic and transonic conditions show good agreement with the experimental data and with the previously published Navier-Stokes calculations using a simple wake model. Some comparisons with Euler calculations are also presented, along with some discussions of the grid refinement studies.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1990
Accession Number
ADA231336

Entities

People

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

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Army Aviation
  • Blade Tips
  • Boundary Layer
  • Coordinate Systems
  • Differential Equations
  • Equations
  • Experimental Data
  • Far Field
  • Flow
  • Free Stream
  • Helicopter Rotors
  • Navier Stokes Equations
  • Potential Flow
  • Pressure Distribution
  • Simulations
  • Three Dimensional
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)