Loads and Performance Data from a Wind-Tunnel Test of Model Articulated Helicopter Rotors with two Different Blade Torsional Stiffnesses.

Abstract

An investigation was conducted in the Langley Transonic Dynamics Tunnel to evaluate a passive means of tailoring helicopter rotor blades to improve performance and reduce loads. The parameters investigated were blade torsional stiffness, blade section camber, and distance between blade structural elastic axis and blade-tip aerodynamic center. This offset was accomplished by sweeping the tip. The investigation was conducted at advance ratios of 0.20, 0.03, and 0.04. Data are presented without analysis; however, cross-referencing of performance data and harmonic-loads data may be useful to the analyst for validating aeroelastic theories and design methodologies as well as for evaluating passive aeroelastic tailoring of rotor blade parameters. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1983
Accession Number
ADA128508

Entities

People

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

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Actuators
  • Aeronautics
  • Army Aviation
  • Blade Tips
  • Blades
  • Camber
  • Frequency
  • Geometry
  • Helicopter Rotors
  • Hydraulic Actuators
  • Load Distribution
  • Mach Number
  • Resonant Frequency
  • Strain Gages
  • Structural Properties
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Structural Dynamics.
  • Systems Analysis and Design