A wind-tunnel investigation of an unpowered helicopter fuselage model with a V-type empennage
Carl E. Freeman, William T. Yeager, United States. National Aeronautics and Space Administration, U.S. Army Air Mobility Research and Development Laboratory
National Aeronautics and Space Administration, 1977 - Transportation - 52 pages
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Air Mobility R&D Airfoil angle and planform angle chord line angle of 55 angle of attack angle on vehicle Army Air Mobility Available from DDC baseline configuration baseline conventional empennage baseline vehicle configuration directional static stability Effect of angle Effect of V-tail effect on vehicle GRMS ground effect Helicopter Directional Control HELICOPTER FUSELAGE MODEL helicopter of reference horizontal-tail incidence angle Incidence angle chord Langley Directorate Langley Research Center Langley V/STOL tunnel lateral and directional Leading-edge sweep lift coefficient longitudinal characteristics match the trim Mobility R&D Laboratory N-m ft-lb NACA NASA QooAR Rotor and Improved Rotorcraft Flight Simulation shown in figure shows the effect sideslip angle tail balance total planform area trim and static U.S. Army Air U.S. Customary Units UNPOWERED HELICOPTER FUSELAGE V-tail configuration V-tail dihedral angle V-tail empennage V-tail incidence angle V-tail planform area V-type empennage vehicle lateral vehicle longitudinal stability vehicle static WIND-TUNNEL INVESTIGATION yaw angles Yeager