Summary of Design Studies and Results of Model Tests of the Folding-Proprotor Aircraft Concept

Abstract

Design studies and wind-tunnel test investigations were conducted to define preliminary designs of folding-proprotor VTOL aircraft for USAF rescue and transport missions and to identify and investigate technical risk areas. The aircraft had gross weights of 66,000 pounds and extended hover capability to 7000 feet. Convertible fan-jet engines provided forward flight speeds to 452 knots with blades folded. Technical risk areas associated with the aircraft designs were found to be in areas of mechanisms, aerodynamics, stability and control, and dynamics. A dynamic wind-tunnel investigation, conducted with a semispan aeroelastic model, demonstrated successful continuous stop/fold/unfold/ start sequences, and freedom from proprotor/pylon stability and blade flutter.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1972
Accession Number
AD0759534

Entities

People

  • E. L. Brown
  • J. A. Detore

Organizations

  • Bell Flight

Tags

Communities of Interest

  • Air Platforms
  • Ground and Sea Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Configurations
  • Aircraft Equipment
  • Aircrafts
  • Airframes
  • Composite Materials
  • Flight Speeds
  • Fuselages
  • Geometry
  • Horizontal Stabilizers
  • Measurement
  • Short Takeoff Aircraft
  • Spars
  • Stabilization Systems
  • Tilt Rotor Aircraft
  • Two Dimensional

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering