Experimental Investigation of the Effects of Helicopter Rotor Design Parameters on Forward Flight Stall Characteristics

Abstract

An experimental investigation was conducted to determine the effects of number of blades, twist, aspect ratio, camber, taper ratio, and torsional frequency on helicopter rotor stall characteristics in forward flight. The tests were conducted in the low-speed UARL 4- x 6-ft wind tunnel with 4.7-ft- diameter model rotors having flapping articulation. Stall conditions were approached by means of increasing rotor shaft angle at fixed collective pitch. Torsional frequency was varied by using a special blade root flexure which would produce the required rigid blade torsional frequencies. Rotor performance, blade response, and boundary layer separation data were acquired to determine the occurrence and extent of blade stall.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1974
Accession Number
AD0783440

Entities

People

  • A. J. Landgrebe
  • E. D. Bellinger
  • L. E. Greenwald
  • W. P. Patrick

Organizations

  • United Technologies Corporation

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aspect Ratio
  • Boundary Layer
  • Boundary Layer Flow
  • Boundary Layer Transition
  • Fittings
  • Flow Fields
  • Flow Visualization
  • Free Stream
  • Frequency
  • Heat Flux
  • Helicopter Rotors
  • Measurement
  • Rotary Wing Aircraft
  • Test Equipment
  • Turbulent Boundary Layer
  • Turbulent Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.