The Online Books Page

Pitching moments

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• Low speed aerodynamic characteristics of NACA 6716 and NACA 4416 airfoils with 35 percent-chord single-slotted flaps (National Aeronautics and Space Administration ;, 1974), by Gene J. Bingham, Kevin W. Noonan, and Langley Research Center (page images at HathiTrust)
• The interpretation of nonlinear pitching moments in relation to the pitch-up problem (National Aeronautics and Space Administration, 1959), by George S. Campbell, Joseph Weil, and Langley Research Center (page images at HathiTrust)
• Full-scale wind-tunnel investigation of the effects of a target-type thrust reverser on the low-speed aerodynamic characteristics of a single-engine jet airplane (National Aeronautics and Space Administration, 1959), by William H. Tolhurst, Richard K. Greif, Mark W. Kelly, and Ames Research Center (page images at HathiTrust)
• Effectiveness of an all-movable horizontal tail on an unswept-wing and body combination for Mach numbers from 0.60 to 1.40 (National Aeronautics and Space Administration, 1959), by Louis S. Stivers and Ames Research Center (page images at HathiTrust)
• Large-scale wind-tunnel tests of an airplane model with an unswept, aspect-ratio-10 wing, four propellers, and blowing flaps (National Aeronautics and Space Administration, 1959), by James A. Weiberg, V. Robert Page, and Ames Research Center (page images at HathiTrust)
• Rapid-transition tests of a 1/4-scale model of the VZ-2 tilt-wing aircraft (National Aeronautics and Space Administration, 1961), by Louis P. Tosti, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Effects of jet billowing on stability of missile-type bodies at Mach 3.85 (National Aeronautics and Space Administration, 1960), by Reino J. Salmi and Lewis Research Center (page images at HathiTrust)
• Pressure distributions and aerodynamic characteristics of several spoiler controls on a 40 degree sweptback wing at a Mach number of 1.61 (National Aeronautics and Space Administration, 1960), by Emma Jean Landrum, K. R. Czarnecki, and Langley Research Center (page images at HathiTrust)
• Incipient- and developed-spin and recovery characteristics of a modern high-speed fighter design with low aspect ratio as determined from dynamic-model tests (National Aeronautics and Space Administration, 1961), by Henry A. Lee, Charles E. Libbey, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Experimental investigation at a Mach number of 3.11 of the lift, drag, and pitching-moment characteristics of five blunt lifting bodies (National Aeronautics and Space Administration, 1960), by William Letko and Langley Research Center (page images at HathiTrust)
• Flight investigation of an automatic pitchup control (National Aeronautics and Space Administration, 1960), by George J. Hurt, James B. Whitten, and Langley Research Center (page images at HathiTrust)
• An analysis of incremental horizontal-tail loads measured on a swept-wing bomber airplane in sideslip maneuvers (National Aeronautics and Space Administration, 1959), by William A. McGowan and Langley Research Center (page images at HathiTrust)
• Flight investigation of stability and control characteristics of a 1/8-scale model of a tilt-wing Vertical-Take-Off-and-Landing (VTOL) airplane (National Aeronautics and Space Administration, 1960), by Louis P. Tosti and Langley Research Center (page images at HathiTrust)
• Effects of body and fin deflections on the aerodynamic characteristics in pitch of a 0.065-scale model of a four-stage rocket configuration at Mach numbers of 1.41 and 1.82 (National Aeronautics and Space Administration, 1959), by Ross B. Robinson and Langley Research Center (page images at HathiTrust)
• Low-speed wind-tunnel investigation of blowing boundary-layer control on leading- and trailing-edge flaps of a full-scale, low-aspect-ratio, 42° swept-wing airplane configuration (National Aeronautics and Space Administration, 1959), by Ralph L. Maki, Demo J. Giulianetti, and Ames Research Center (page images at HathiTrust)
• Wind-tunnel investigation of effect of ratio of wing chord to propeller diameter with addition of slats on the aerodynamic characteristics of tilt-wing VTOL configurations in the transition speed range (National Aeronautics and Space Administration, 1959), by Robert T. Taylor, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)

Items below (if any) are from related and broader terms.