Wind-Tunnel Investigation of the Effects of Blade Tip Geometry on the Interaction of Torsional Loads and Performance for an Articulated Helicopter Rotor

Abstract

An investigation was conducted in the Langley Transonic Dynamics Tunnel to determine the effects of rotor blade tip geometry on the interaction between torsional loads and performance for an articulated helicopter rotor. Tests were conducted using four tip geometries at advance ratios of 0.20, 0.30, and 0.35. Geometric variations between tips consisted to taper, sweep, and anhedral. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1981
Accession Number
ADA108790

Entities

People

  • Wayne R. Mantay
  • William T. Yeager Jr.

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Actuators
  • Airfoils
  • Army Aviation
  • Blade Tips
  • Blades
  • Coefficients
  • Experimental Data
  • Frequency
  • Geometry
  • Helicopter Rotors
  • Hydraulic Actuators
  • Load Distribution
  • Mach Number
  • Physical Properties
  • Resonant Frequency
  • Strain Gages
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering