Wind Tunnel Test of the Conversion Process of a Folding Tilt Rotor Aircraft Using a Semispan Unpowered Model. Volume 4. Part 1. Analysis and Results

Abstract

Wind tunnel test data obtained with a 33.75-inch diameter nonarticulated folding tilt rotor mounted on a semispan wing show the effects of collective pitch schedule variations on transient lift, drag, and pitching moment of the aircraft. Blade loads data presented show that loads do not limit the conversion process. The model was configured with prop/rotor blades which had an in-plane natural frequency of less than 1.0/rev. The testing included study of the aerodynamics and dynamics of rotor spin-up, spin-down, stopping, and steady windmilling. Correlation with predictions of transient aerodynamic performance static derivatives of the prop/rotor, and blade loads are included.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1971
Accession Number
AD0735632

Entities

People

  • John Magee
  • Robert William Taylor

Organizations

  • Boeing Rotorcraft Systems

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force Facilities
  • Aircrafts
  • Angular Motion
  • Autorotation
  • Bench Tests
  • Design Criteria
  • Dynamics
  • Frequency
  • Measurement
  • Mechanics
  • Modulus Of Elasticity
  • Resonant Frequency
  • Short Takeoff Aircraft
  • Test Facilities
  • Tilt Rotor Aircraft
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Control Systems Engineering.