An Experimental Investigation of the Aeromechanical Stability of a Hingeless Rotor in Hover and Forward Flight.

Abstract

Analysis and testing were conducted in the Langley Transonic Dynamics Tunnel to investigate the aeromechanical stability of a soft inplane hingeless rotor model. Rotor stability data were obtained in hover and in forward flight up to an advanced ratio of 0.35. Model rotor parameters evaluated were blade sweep and droop, pre-cone of the blade feathering axis, and blade pitch-flap coupling. Data obtained during these tests are presented without analysis. Keywords: Hovering; Hingeless helicopter rotor dynamics; Helicopter rotor blades; Ground resonance.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1987
Accession Number
ADA182140

Entities

People

  • M-nabil H. Hamouda
  • Wayne R. Mantay
  • William T. Yeager Jr.

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Assembly
  • Center Of Gravity
  • Control Systems
  • Couplings
  • Flight
  • Frequency
  • Helicopter Rotors
  • Helicopters
  • Hingeless
  • Mach Number
  • Modulus Of Elasticity
  • Oscillation
  • Stiffness
  • Strain Gages
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Structural Dynamics.