An assessment of the capability to calculate tilting prop-rotor aircraft performance, loads, and stability
Wayne Johnson, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch
National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1984 - Transportation - 25 pages
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30 for key aerodynamic aeroelastic stability airfoil altitude Ames Research Center antisymmetric Bell Helicopter bending modes blade loads blade pitch Calculated performance calculated results cantilever wing Cj/a collective pitch comparison of flight comparison of wind-tunnel CT/a drag coefficient dynamic stall elastic torsion modes empirical factor figure of merit flight test flight-test data frequency and damping function of speed function of thrust gimballed helicopter forward flight helicopter rotors induced power knots 300 Figure lift coefficient mode damping mode shapes nacelle angles NASTRAN Oscillatory beamwise bending oscillatory loads oscillatory pitch-link loads Oscillatory spindle chord parameters pitch pretest radial station results see fig rotor blade rotor loads rotor power Rotor Research Aircraft spindle chord bending stability boundary stall models structural damping test and calculated testing of tilting tilt rotor configuration tilt rotor designs Tilt Rotor Research tilting prop-rotor aircraft tip Mach number torsion deflection V/SIR wind-tunnel test wing modes XV-15 rotor XV-15 Tilt Rotor