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Control surfaces

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• Airplanes -- Control surfaces

• Transonic pressure measurements and comparison of theory to experiment for an arrow-wing configuration (National Aeronautics and Space Administration ;, 1976), by Marjorie E. Manro, Langley Research Center, and Boeing Commercial Airplane Company (page images at HathiTrust)
• Free-flight investigation at Mach numbers between 0.5 and 1.7 of the zero-lift rolling effectiveness and drag of various surface, spoiler, and jet controls on an 80° delta-wing missile (National Aeronautics and Space Administration, 1960), by Eugene D. Schult 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)
• Aerodynamic damping at Mach numbers of 1.3 and 1.6 of a control surface on a two-dimensional wing by the free-oscillation method (National Aeronautics and Space Administration, 1960), by W. J. Tuovila, R. W. Hess, and Langley Research Center (page images at HathiTrust)
• An analog study of an airborne automatic landing-approach system (National Aeronautics and Space Administration, 1959), by James J. Adams and Langley Research Center (page images at HathiTrust)

• USAF stability and control datcom (National Technical Information Service, 1975), by Douglas Aircraft Company, R. D. Finck, and D. E. Hoak (page images at HathiTrust)
• Supersonic aeroelastic effects on static stability and control. Flight Control Laboratory. Contract nos. AF33 (616)-3577 and AF33(616)-6067. ARDC Project no. 8219. Task no. 82158. (Wright Air Development Division, Air Research and Development Command., U. S. Air Force, 1958), by Bell Aircraft Corporation and Vincent W. Donato (page images at HathiTrust)
• Control-surface hinge-moment calculations for a high-aspect-ratio supercritical wing (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Boyd Perry, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Effect of aileron deflections on the aerodynamic characteristics of a semispan model of a subsonic energy-efficient transport (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Peter F. Jacobs and Langley Research Center (page images at HathiTrust)
• Stability and control characteristics of a three-surface advanced fighter configuration at angles of attack up to 45? (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by William P. Henderson, Laurence D. Leavitt, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Theoretical study of the effect of wind velocity gradients on longitudinal stability and control in climbing and level flight (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Windsor L. Sherman, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Aerothermal environment in chordwise gaps between split elevons at Mach 6.8 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by L. Roane Hunt, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• NASA TN D-5857 (National Aeronautics and Space Administration ;, 1970), by James P. Shivers, George M. Ware, Marvin P. Fink, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Sonic-boom characteristics in the extreme near field of a complex airplane model at mach numbers of 1.5, 1.8, and 2.5 (National Aeronautics and Space Administration, 1970), by Odell A. Morris, Harry W. Carlson, Milton Lamb, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Exploratory wind-tunnel investigation of deployable flexible ventral fins for use as an emergency spin-recovery device (National Aeronautics and Space Administration, 1971), by Sanger M. Burk, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Summary of spin technology as related to light general-aviation airplanes (National Aeronautics and Space Administration, 1971), by James S. Bowman, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Studies of optimum body shapes at hypersonic speeds (National Aeronautics and Space Administration, 1967), by Louis S. Stivers, Bernard Spender, Langley Research Center, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Load distributions associated with controls at supersonic speeds (National Advisory Committee for Aeronautics, 1953), by K. R. Czarnecki, Douglas R. Lord, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Low-speed wind-tunnel investigation of jet control on a 35° swept wing (National Advisory Committee for Aeronautics, 1953), by John G. Lowry, Thomas R. Turner, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• The effect of a change in airfoil section on the hinge-moment characteristics of a half-delta tip control with a 60° sweep angle at a Mach number of 6.9 (National Advisory Committee for Aeronautics, 1954), by David E. Fetterman, Herbert W. Ridyard, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Exploratory investigation of the moments on oscillating control surfaces at transonic speeds (National Advisory Committee for Aeronautics, 1955), by Dennis J. Martin, C. William Martz, Robert F. Thompson, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Aerodynamic characteristics of a spoiler-slot-deflector control on a 45° sweptback wing at Mach numbers of 1.61 and 2.01 (National Advisory Committee for Aeronautics, 1957), by Douglas R. Lord, Robert Moring, United States. National Adviosry Committee for Aeronautics, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Aerodynamic characteristics of a canard-balanced, free-floating, all-movable stabilizer as obtained from rocket-powered-model flight tests and low-speed wind-tunnel tests (National Advisory Committee for Aeronautics, 1953), by William N. Gardner, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Lateral-control investigation of flap-type controls on a wing with quarter-chord line sweptback 35°, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section. Transonic-bump method (National Advisory Committee for Aeronautics, 1950), by Robert F. Thompson, United States. National Adviosry Committee for Aeronautics, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Theoretical damping in roll and rolling effectiveness of slender cruciform wings (National Advisory Committee for Aeronautics, 1951), by Gaynor J. Adams and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Flight investigation of a mechanical feel device in an irreversible elevator control system of a large airplane (National Advisory Committee for Aeronautics, 1951), by B. Porter Brown, James B. Whitten, Robert G. Chilton, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation at Mach numbers of 0.20 to 3.50 of blended wing-body combinations of sonic design with diamond, delta and arrow plan forms (National Aeronautics and Space Administration, 1960), by George H. Holdaway, Jack A. Mellenthin, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Evaluation of blended wing-body combinations with curved plan forms at Mach numbers up to 3.50 (National Aeronautics and Space Administration, 1960), by George H. Holdaway, Jack A. Mellenthin, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Recent control studies (National Advisory Committee for Aeronautics, 1959), by John G. Lowry and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Wind-tunnel investigation of the effect of aspect ratio and chordwise location on effectiveness of spoiler-slot-deflector controls on thin untapered winds at transonic speeds (National Advisory Committee for Aeronautics, 1957), by Alexander D. Hammond, Jarrett K. Huffman, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Collection and analysis of hinge-moment data on control-surface tabs (National Advisory Committee for Aeronautics, 1947), by Paul E. Purser, Charles B. Cook, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Wind-tunnel investigation of the boundary layer on an NACA 0009 airfoil having 0.25- and 0.50-airfoil chord plain sealed flaps (National Advisory Committee for Aeronautics, 1948), by Jack D. Brewer, Josephine F. Polhamus, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• NACA Wartime Reports. Series L. (National Advisory Committee for Aeronautics, 1945), by Harold I. Johnson, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• NACA Wartime Reports. Series L. (National Advisory Committee for Aeronautics, 1943), by H. Page Hoggard, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• NACA Wartime Reports. Series L. (National Advisory Committee for Aeronautics, 1944), by John G. Lowry, I. Elizabeth Garner, James A. Maloney, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Fundamentals of design of piloted aircraft flight control systems. (U.S. Govt. Print. Off.], 1952), by United States. Navy Department. Bureau of Aeronautics, C. L. Bates, and Duane T. McRuer (page images at HathiTrust)
• Effects of overhang balance on the hinge-moment and effectiveness characteristics of an unswept trailing-edge control on a 60 degree delta wing at transonic and supersonic speeds (Washington, D.C. : National Advisory Committee for Aeronautics, 1954., 1954), by Lawrence D. Guy, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Wing roll control devices for transonic high lift conditions. Part I, Fixed wing configuration (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1970., 1970), by Jack D. McAllister, Perry D. Whitten, David B. Benepe, Air Force Flight Dynamics Laboratory (U.S.), and General Dynamics Corporation. Convair Division (page images at HathiTrust)
• Wing roll control devices for transonic high lift conditions. Part II, Variable sweep configuration (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1971., 1971), by Jack D. McAllister, Perry D. Whitten, David B. Benepe, Air Force Flight Dynamics Laboratory (U.S.), and General Dynamics Corporation. Convair Division (page images at HathiTrust)
• Development of an empirically based computer program to predict the aerodynamic characteristics of aircraft. Volume I, Empirical methods. (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1973., 1973), by Roy T. Schemensky, Air Force Flight Dynamics Laboratory (U.S.), and General Dynamics Corporation. Convair Division (page images at HathiTrust)
• Factors influencing the accuracy of aerodynamic hinge-moment prediction (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1978., 1978), by Wen-Fan Lin, Michael D. Clarke, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Boeing Aerospace Company (page images at HathiTrust)
• Validation of United States Air Force stability and control Datcom methodologies for straight-tapered sweptforward wings (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1985., 1985), by Daniel G. Sharpes, Air Force Flight Dynamics Laboratory (U.S.), and Air Force Wright Aeronautical Laboratories (page images at HathiTrust)
• Pressure and heat transfer measurements for Mach 8 flows over a blunt pryamidal configuration with aerodynamic controls. Part I. Pressure data for delta wing surface (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1964., 1964), by Louis G. Kaufman, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Grumman Aircraft Engineering Corporation. Research Department (page images at HathiTrust)
• Control-surface deflection effects on the innovative control effectors (ICE 101) design (Wright Patterson Air Force Base, Ohio : Air Vehicles Directorte, Air Force Research Laboratory, Air Force Materiel Command, 2000., 2000), by Gregory A. Addington and Ohio). Air Vehicles Directorate Air Force Research Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
• Improving control allocation accuracy for nonlinear aircraft dynamics (Wright Patterson Air Force Base, Ohio : Air Vehicles Directorte, Air Force Research Laboratory, Air Force Materiel Command, 2002., 2002), by David B. Doman, Michael W. Oppenheimer, Inc. Veridian Engineering, and Ohio). Air Vehicles Directorate Air Force Research Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
• Stresses in skin panels subjected to random acoustic loading (Air Force Materials Laboratory, Research and Technology Division, Air Force Systems Command, 1967), by Brian L. Clarkson, University of Southampton, and Wright-Patterson Air Force Base (Ohio) (page images at HathiTrust)
• NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1945), by John A. Zalovcik, Richard B. Skoog, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Noise and sonic fatigue of high lift devices. aeroacoustic loads (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1977., 1977), by H. L. Leve, D. A. Plocher, C. M. Ho, M. A. Yeneriz, Air Force Flight Dynamics Laboratory (U.S.), United States. Air Force. Systems Command, University of Southern California, and Douglas Aircraft Company (page images at HathiTrust)
• Flight control principles for control configured vehicles (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1972., 1972), by Edmund G. Rynaski, Norman C. Weingarten, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Cornell Aeronautical Laboratory (page images at HathiTrust)
• Prediction of unsteady aerodynamic loadings on non-planar wings and wing-tail configurations in supersonic flow. Part II, Computer program description (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1972., 1972), by Gordon D. Kramer, George E. Keylon, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Boeing Company. Commercial Airplane Group (page images at HathiTrust)
• Prediction of unsteady aerodynamic loadings on non-planar wings and wing-tail configurations in supersonic flow. Part I, Theoretical development, program usage, and application (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1972., 1972), by Jack Morito, John R. Hogley, Christopher J. Borland, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Boeing Company. Commercial Airplane Group (page images at HathiTrust)
• An investigation of hypersonic flow separation and control characteristics (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1965., 1965), by Louis G. Kaufman, Daniel Weiss, Stravos Hartofilis, Lawrence Meckler, United States. Air Force. Systems Command. Research and Technology Division, Air Force Flight Dynamics Laboratory (U.S.), and Grumman Aircraft Engineering Corporation (page images at HathiTrust)

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