WIND TUNNEL TESTS AND FURTHER ANALYSIS OF THE FLOATING WING FUEL TANKS FOR HELICOPTER RANGE EXTENSION. VOLUME 5. ANALYSIS OF STABILITY, CONTROL AND PERFORMANCE CHARACTERISTICS

Abstract

An analytical investigation of the stability and performance of a Boeing-Vertol H-21 tandem rotor helicopter equipped with floating wing fuel cells as a means of ferry range extension is described. The stability of the total system was studied with the wing located forward and directly under the helicopter center-of-gravity (cg). Two methods of stabilizing the wing oscillations about the hinge were studied: (a) A skewed hinge line, introducing a change in angle of attack as a function of the flapping disturbance; and (b) a geared trailing edge flap, mechanically linked to deflect when the wing flaps. Satisfactory stability was obtained with the wing positioned directly beneath the helicopter cg, using an unskewed hinge line, and geared flaps. The forward wing location was unsatisfactory from the standpoint of longitudinal stability for the light wing case. Flight simulator studies emphasize the need for additional lateral control to supplement that produced by the basic aircraft.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1961
Accession Number
AD0267350

Entities

People

  • D. Lawrence
  • H. Neeb
  • R. Johnstone

Organizations

  • Boeing Rotorcraft Systems

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Aircrafts
  • Center Of Gravity
  • Computers
  • Equations
  • Flight Simulators
  • Fuel Cells
  • Fuel Tanks
  • Helicopters
  • Simulators
  • Steady State
  • Trailing Edges
  • Transportation
  • United States
  • Wind Tunnel Tests
  • Wind Tunnels
  • Wing Flaps

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Electrical Engineering

Technology Areas

  • Biotechnology