WIND TUNNEL TESTS OF A FULL-SCALE ROTOR AT HIGH SPEEDS

Abstract

This report summarizes the results of a wind tunnel program conducted to define the effects of compressibility and advance ratio on the performance of a 46-foot diameter, three-bladed rotor. Measured rotor profile power increase with lift coefficient and advance ratio were greater than predicted. Airfoil characteristics were synthesized that improve correlation of Mach number and lift effects on profile power. Preliminary radial flow considerations are presented and discussed. Additional analytical and experimental work is recommended to investigate in more detail the effects of advance ratio on profile power.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1965
Accession Number
AD0619157

Entities

People

  • C. L. Livingston

Organizations

  • Bell Flight

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Actuators
  • Army Aviation
  • Axial Loads
  • Bending Moments
  • Blade Tips
  • Computer Programs
  • Computers
  • Flow
  • Frequency
  • Government Procurement
  • Mach Number
  • Radial Flow
  • Resonant Frequency
  • Test Stands
  • Vibration
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerodynamics/Aeronautics.
  • Systems Analysis and Design