DESIGN AND WIND TUNNEL TEST OF A MODEL HELICOPTER ROTOR HAVING AN INDEPENDENTLY MOVABLE INBOARD BLADE PANEL

Abstract

Wind tunnel tests of a rotor having an independently movable inboard blade panel were conducted at an advance ratio of 0.6. It was demonstrated that this design resulted in a major advance in propulsive capability over the conventional type of rotor. Test results are presented in nondimensional plots of lift, power, and propulsive force versus control axis angle, and in cross- plotted contours of constant power of lift versus propulsive force axes.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1965
Accession Number
AD0623129

Entities

People

  • Donald G. Ekquist

Organizations

  • Boeing Rotorcraft Systems

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Blade Tips
  • Blades
  • Data Reduction
  • Dynamic Pressure
  • Free Stream
  • Helicopter Rotors
  • Helicopters
  • Mach Number
  • Propellers
  • Propulsion Systems
  • Short Takeoff Aircraft
  • Test Equipment
  • Test Stands
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Structural Dynamics.