Investigation of the Effects of Blade Structural Design Parameters on Helicopter Stall Boundaries

Abstract

An experimental and analytical study was conducted to determine the effects of blade structural design parameters on the stall-related operating boundaries of helicopter main rotors. Emphasis was placed on the effects of blade torsional properties on the buildup of vibratory control loads in stall. The analytical methods used in the study were evaluated through correlation with data for two full-scale rotors and data obtained on a two-dimensional airfoil system whose torsional dynamics simulated those of a rotor blade.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1974
Accession Number
AD0784594

Entities

People

  • G. L. Commerford
  • R. H. Blackwell

Organizations

  • United Technologies Corporation

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Acoustics
  • Aerodynamic Characteristics
  • Aircrafts
  • Bending Moments
  • Boundaries
  • Boundary Layer
  • Dynamic Response
  • Helicopter Rotors
  • Helicopters
  • Mach Number
  • Moment Of Inertia
  • Resonant Frequency
  • Test And Evaluation
  • Test Facilities
  • Two Dimensional
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.