Application of Multigrid Computational Fluid Dynamics (CFD) Methods to Rotor Analysis.

Abstract

The TLNS3DR code is applied to various advanced rotor blades to study tip vortex and to investigate the general capabilities of the code. For nonrotating flows, the solutions in terms of the tip vortex and surface pressure coefficients are obtained for realistic helicopter rotor-tip configurations to study effects of blade planforms on the tip vortex under incompressible flow condition. Calculated results are compared with experimentally obtained data at NASA-Langley's Basic Aerodynamic Research Wind Tunnel (BART). A Berp-type tip, a swept-type tip and its equivalent taper-type tip configurations are investigated. For both nonrotating and rotating flows, the Berp-type blade, the swept-type blade, and its equivalent taper-type and rectangle-type blades with zero twist are considered under compressible flow condition. Solutions are presented. (AN)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1995
Accession Number
ADA293012

Entities

People

  • Hong Hu

Organizations

  • Hampton University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Blade Tips
  • Boundary Layer
  • Coefficients
  • Compressible Flow
  • Computational Fluid Dynamics
  • Computational Science
  • Dynamics
  • Experimental Data
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Helicopter Rotors
  • Helicopters
  • Incompressible Flow
  • Mach Number
  • Planform
  • Three Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.