Experimental Investigation of Effects of Blade Section Camber and Planform Taper on Rotor Hover Performance

Abstract

An experimental and analytical investigation was conducted to determine the effects of blade section camber and blade planform taper on helicopter rotor hover performance and to assess the accuracy of several theoretical methods in predicting such performance. The tests were conducted using small scale model rotors (nominally 4 feet in diameter) operating in and out of ground effect at full-scale tip speeds. The NACA 23112 airfoil, which is a section specifically designed to produce very low pitching moments such as required for helicopter blade applications, was selected for the cambered blade. A nominal taper ratio of 2:1 was selected for the tapered blade tests.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1972
Accession Number
AD0743232

Entities

People

  • E. Dean Bellinger

Organizations

  • United Technologies Corporation

Tags

DTIC Thesaurus Topics

  • Accuracy
  • Aerodynamic Characteristics
  • Aircrafts
  • Blade Tips
  • Computer Programs
  • Contracts
  • Experimental Data
  • Flow Visualization
  • Geometry
  • Helicopter Rotors
  • Mach Number
  • Measurement
  • Strain Gages
  • Test And Evaluation
  • Test Equipment
  • Test Facilities
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Tribology (the study of the boundary interaction between sliding surfaces, lubrication, wear and friction).