SUMMARY TECHNICAL REPORT, ROTOR/WING CONCEPT STUDY. VOLUME 2. APPENDIXES A, B, C, D, E AND F

Abstract

Research work including wind tunnel and whirl test of the Rotor/Wing is described. The Rotor/Wing is a dual-purpose lifting device that is a rotor with an unusually large hub. It acts as a tip-jet powered helicopter for low- speed flight and stops in flight to become a tapered and sweptback low-aspect ratio wing for cruise. Stopping the rotor in flight removes the speed limitations of the helicopter rotor and permits flight speeds up to 500 knots. Research work was supported by the U. S. Navy Office of Naval Research and Bureau of Naval Weapons. Three series of wind tunnel tests demonstrated that the powered-rotor and autorotating-rotor characteristics are similar to those of a high-performance helicopter; that the stopped-rotor characteristics are similar to a conventional low-aspect ratio wing with sweep and taper, and maximum lift/ drag ratios of 12 or more should be achievable for full-scale aircraft; and that conversion from stopped- to running- rotor and vice versa is a simple and straightforward procedure.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1965
Accession Number
AD0473864

Entities

People

  • Robert E. Head

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Configurations
  • Aircraft Equipment
  • Aircrafts
  • Airfoils
  • Airframes
  • Aspect Ratio
  • Computer Programs
  • Control Systems
  • Helicopter Rotors
  • Helicopters
  • Horizontal Stabilizers
  • Military Research
  • Model Basins
  • Test Facilities
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

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