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Angle of attack

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• Pressure distributions on a rectangular aspect-ratio-6, slotted supercritical airfoil wing with externally blown flaps / (Washington : U.S. National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by William G. Johnson, Langley Research Center, and United States National Aeronautics and Space Administration (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 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Emma Jean Landrum, K. R. Czarnecki, and Langley Research Center (page images at HathiTrust)
• Experimental determination of the effects of frequency and amplitude of oscillation on the roll-stability derivatives for a 60 degree delta-wing airplane model / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Lewis R. Fisher and Langley Research Center (page images at HathiTrust)
• Analysis of flight data on boundary layer transition at high angles of attack / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1972), by Wayne W. Haigh, D. R. S. Ko, B. M. Lake, Langley Research Center, and TRW Systems Group (page images at HathiTrust)
• Effects of canard planform and wing-leading-edge modification on low-speed longitudinal aerodynamic characteristics of a canard airplane configuration / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Bernard Spencer, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• A computer program for the prediction of ducted fan performance / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1970), by M. R. Mendenhall, Selden B. Spangler, Ames Research Center, and Nielsen Engineering & Research (page images at HathiTrust)
• Static aerodynamic characteristics of a model of a typical subsonic jet-transport airplane at Mach numbers from 0.40 to 1.20 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1967), by Eugene N. Brooks, James A. Blackwell, John P. Decker, and Langley Research Center (page images at HathiTrust)
• Flight investigation of an automatic pitchup control / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by George J. Hurt, James B. Whitten, and Langley Research Center (page images at HathiTrust)
• Wind-tunnel and piloted flight simulator investigation of a deflected-slipstream VTOL airplane, the Ryan VZ-3RY / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Harry A. James and Ames Research Center (page images at HathiTrust)
• The effect of angle of attack on the buckling of Mars entry aeroshells / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1973), by Gerald A. Cohen, Langley Research Center, and Structures Research Associates (page images at HathiTrust)
• Aerodynamic loading characteristics at Mach numbers from 0.80 to 1.20 of a 1/10-scale three-stage scout model / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Thomas C. Kelly, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• A simulator study of the effectiveness of a pilot's indicator which combined angle of attack and rate of change of total pressure as applied to the take-off rotation and climbout of a supersonic transport / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Albert W. Hall, Jack E. Harris, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Transonic wind-tunnel tests of an error-compensated static-pressure probe / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Francis J. Capone, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Transonic aerodynamic loading characteristics of a wing-body-tail combination having 52.5° sweptback wing of aspect ratio 3 with conical wing camber and body indentation for a design Mach number [square root of] 2 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Marlowe D. Cassetti, William B. Igoe, Richard J. Re, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Laminar heat-transfer and pressure measurements at a Mach number of 6 on a sharp and blunt 15° half-angle cones at angles of attack up to 90° / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Raul J. Conti, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Effect of ground proximity on the aerodynamic characteristics of aspect-ratio-1 airfoils with and without end plates / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Arthur W. Carter, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Take-off distances of a supersonic transport configuration as affected by airplane rotation during the take-off run / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Albert W. Hall, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Measured and theoretical flow fields behind a rectangular and a triangular wing up to high angles of attack at a Mach number of 2.46 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Frank J. Centolanzi and Ames Research Center (page images at HathiTrust)
• Study of several factors affecting crew escape trajectories from the space shuttle orbiter at low-subsonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985), by William I. Scallion and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• The effect of protuberances, cavities, and angle of attack on the wind-tunnel pressure and heat-transfer distribution for the Apollo command module / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1966), by John J. Bertin and Manned Spacecraft Center (U.S.) (page images at HathiTrust)
• Analytical investigation of effect of spin entry technique on spin and recovery characteristics for a 60 degree delta-wing airplane / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Stanley H. Scher, George F. Lawrence, Ernie L. Anglin, 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 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by William Letko and Langley Research Center (page images at HathiTrust)
• The variation and control of range traveled in the atmosphere by a high-drag variable-lift entry vehicle / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Donald C. Cheatham, John M. Eggleston, John W. Young, and Langley Research Center (page images at HathiTrust)
• The interpretation of nonlinear pitching moments in relation to the pitch-up problem / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by George S. Campbell, Joseph Weil, and Langley 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 / (Washington, [D.C.] : 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 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by James A. Weiberg, V. Robert Page, and Ames Research Center (page images at HathiTrust)
• Full-scale wind-tunnel investigation of the longitudinal characteristics of a tilting-rotor convertiplane / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by David G. Koenig, Mark W. Kelly, Richard K. Greif, and Ames 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 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Ross B. Robinson and Langley Research Center (page images at HathiTrust)
• Low subsonic pressure distributions on three rigid wings simulating paragliders with varied canopy curvature and leading-edge sweep / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Paul G. Fournier, B. Ann Bell, United States National Aeronautics and Space Administration, and Langley 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 / (Washington, [D.C.] : 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)

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