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Angle of attack (Aerodynamics)

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• Aerodynamics
• Angles (Geometry)

• Angle of attack (Aerodynamics) -- Computer simulation
• Angle of attack (Aerodynamics) -- Mathematical models
• Angle of attack (Aerodynamics) -- Measurement
• Angle of attack (Aerodynamics) -- Testing

• Angle of incidence (Aerodynamics)
• Attack, Angle of (Aerodynamics)
• Incidence, Angle of (Aerodynamics)

• Roll-yaw control at high angle of attack by forebody tangential blowing (Joint Institute for Aeronautics and Acoustics, National Aeronautics and Space Administration, Ames Research Center :, 1995), by Nelson Pedreiro and Joint Institute for Aeronautics and Acoustics (page images at HathiTrust)
• Aerothermal tests of a 12.5⁰ cone at Mach 6.7 for various Reynolds numbers, angles of attack, and nose shapes (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Robert J. Nowak, L. Roane Hunt, Cindy W. Albertson, and Langley Research Center (page images at HathiTrust)
• Separated flow over bodies of revolution using an unsteady discrete-vorticity cross wake. Part 2, Computer program description (National Aeronautics and Space Administration ;, 1974), by F. J. Marshall, F. D. Deffenbaugh, Langley Research Center, and Purdue University. School of Aeronautics and Astronautics (page images at HathiTrust)
• Theoretical study of ducted fan performance (National Aeronautics and Space Administration ;, 1970), by M. R. Mendenhall, Selden B. Spangler, Ames Research Center, and Nielsen Engineering & Research (page images at HathiTrust)
• NASA TR R-146 (National Aeronautics and Space Administration ;, 1962), by Donald M. Kuehn, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• NASA TN D-1980 (National Aeronautics and Space Administration, 1963), by George E. Kaattari, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-4034 (National Aeronautics and Space Administration ;, 1967), by Lawrence E. Putnam, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5251 (National Aeronautics and Space Administration ;, 1969), by James L. Hunt, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5204 (National Aeronautics and Space Administration ;, 1969), by James F. Campbell, Dorothy H. Tudor, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Transonic wind-tunnel investigation of the fin loads of a 1/8-scale model simulating the first stage of the Scout research vehicle (National Aeronautics and Space Administration, 1961), by Thomas C. Kelly and Langley Research Center (page images at HathiTrust)
• Effects of angle of attack and bluntness on laminar heating-rate distributions of a 15 ̊cone at a Mach number of 10.6 (National Aeronautics and Space Administration, 1969), by Joseph W. Cleary, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-6091 (National Aeronautics and Space Administration ;, 1971), by Sue B. Grafton, Charles E. Libbey, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5766 (National Aeronautics and Space Administration :, 1970), by Michael C. Fischer, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5948 (National Aeronautics and Space Administration :, 1970), by Gerard E. Woodbury, W. Douglas Morris, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5951 (National Aeronautics and Space Administration :, 1970), by Joseph W. Cleary, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-5903 (National Aeronautics and Space Administration :, 1970), by Joseph W. Cleary, Charles E. Duller, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-5316 (National Aeronautics and Space Administration ;, 1969), by Francis J. Capone, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-4961 (National Aeronautics and Space Administration ;, 1969), by P. Calvin Stainback, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Jet effects on cylindrical afterbodies housing sonic and supersonic nozzles which exhaust against a supersonic stream at angles of attack from 90 ̊to 180 ̊ (National Aeronautics and Space Administration, 1962), by Lovick O. Hayman, Russell W. McDearmon, and Langley Research Center (page images at HathiTrust)
• Effects of sting-support diameter on the base pressures of an elliptic cone at mach numbers from 0.60 to 1.40. (National Aeronautics and Space Administration :, 1961), by Louis S. Jr Stivers, Lionel L. Jr Levy, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-1793 (National Aeronautics and Space Administration, 1963), by Theodore J. Goldberg, James G. Hondros, George C. Ashby, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Body motions and angles of attack during Project Fire flight II reentry (National Aeronautics and Space Administration ;, 1967), by William I. Scallion, John H. Lewis, and Langley Research Center (page images at HathiTrust)
• Static longitudinal stability and control characteristics at a mach number of 2.01 of a hypersonic missile configuration having all-movable wing and tail surfaces (National Aeronautics and Space Administration, 1961), by Ross B. Robinson, Gerald V. Foster, and Langley Research Center (page images at HathiTrust)
• Measurements of flow properties in the vicinity of three wing-fuselage combinations at Mach numbers of 1.61 and 2.01 (National Aeronautics and Space Administration, 1959), by Harry W. Carlson and Langley Research Center (page images at HathiTrust)
• Effect of wing pivot location on longitudinal aerodynamic characteristics of a variable-sweep wing having an M planform (National Aeronautics and Space Administration, 1964), by William P. Henderson, Edward J. Ray, and Langley Research Center (page images at HathiTrust)
• Low-speed characteristics of a variable-sweep supersonic transport model with a blended engine fuselage and engine-mounted tails (National Aeronautics and Space Administration, 1964), by Vernard E. Lockwood, Wilson E. Thompson, and Langley Research Center (page images at HathiTrust)
• Static longitudinal aerodynamic characteristics at transonic speeds and angles of attack up to 99 degree of a reentry glider having folding wing-tip panels (National Aeronautics and Space Administration, 1961), by Walter B. Olstad and Langley Research Center (page images at HathiTrust)
• Longitudinal aerodynamic characteristics at transonic speeds of two V/STOL airplane configurations with skewed and variable-sweep wings (National Aeronautics and Space Administration, 1961), by Arvo A. Luoma and Langley Research Center (page images at HathiTrust)
• Aerodynamic characteristics of a tailless fixed-wing supersonic transport configuration at Mach number 2.20 (National Aeronautics and Space Administration, 1964), by Gerald V. Foster, William A. Corlett, and Langley Research Center (page images at HathiTrust)
• Investigation of the static stability characteristics of a reentry spacecraft model in free flight for Mach numbers from 2.62 to 1.11 launched at an angle of attack of 180 degree (National Aeronautics and Space Administration, 1961), by J. W. Usry and Langley Research Center (page images at HathiTrust)
• Low-speed investigation of the aerodynamic characteristics of a variable-sweep supersonic transport configuration having a blended wing and body (National Aeronautics and Space Administration, 1961), by William C. Sleeman, A. Warner Robins, and Langley Research Center (page images at HathiTrust)
• Pressure and heat-transfer measurements on a Mercury capsule model (National Aeronautics and Space Administration, 1962), by John O. Reller, H. Lee Seegmiller, and Ames Research Center (page images at HathiTrust)
• Static longitudinal and lateral aerodynamic characteristics at a Mach number of 2.20 of a V/STOL airplane configuration with a variable-sweep wing and with a skewed wing design (National Aeronautics and Space Administration, 1961), by Odell A. Morris, Gerald V. Foster, and Langley Research Center (page images at HathiTrust)
• Principal results from wind-tunnel stability tests of several proposed space capsule models up to an angle of attack of 33 degree (National Aeronautics and Space Administration, 1959), by Howard S. Carter, Roland D. English, Ronald Kolenkiewicz, and Langley Research Center (page images at HathiTrust)
• Static force tests of a model of a twin-jet fighter airplane for angles of attack from -10⁰ to 110⁰ and sideslip angles from -40⁰ to 40⁰ (National Aeronautics and Space Administration, 1971), by Ernie L. Anglin, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• A theoretical and experimental study of hypersonic flow over flared bodies at incidence (National Aeronautics and Space Administration ;, 1966), by John V. Rakich, Gene P. Menees, and Ames Research Center (page images at HathiTrust)
• NASA TN D-3583 (National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 2215], 1966), by William B. Kemp, W. Pelham Phillips, Vernard E. Lockwood, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-3591 (National Aeronautics and Space Administration ;, 1966), by Joseph R. Chambers, Sue B. Grafton, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-5193 (National Aeronautics and Space Administration ;, 1969), by Barbara J. Short, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• An experimental and theoretical investigation of the pressure distribution and flow fields of blunted cones at hypersonic Mach number (National Aeronautics and Space Administration, 1965), by Joseph W. Cleary and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-1781 (National Aeronautics and Space Administration ;, 1963), by David S. Shaw, C. Donald Babb, Dennis E. Fuller, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Flight evaluation of angle of attack as a control parameter in general-aviation aircraft (National Aeronautics and Space Administration :, 1971), by Shu W. Gee, Einer K. Enevoldson, Harold G. Gaisick, United States National Aeronautics and Space Administration, and Flight Research Center (U.S.) (page images at HathiTrust)
• NASA TN D-1786 (National Aeronautics and Space Administration ;, 1963), by Clarence A. Brown, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-6550 (National Aeronautics and Space Administration :, 1971), by George E. Kaattari, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• High-subsonic-speed investigation of the static longitudinal aerodynamic characteristics of several delta-wing configurations for angles of attack from 0 degree to 90 degree (National Aeronautics and Space Administration, 1959), by Bernard Spencer, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Performance of three isentropic all internal compression axisymmetric inlets designed for Mach 2.5 (National Aeronautics and Space Administration, 1960), by Bernhard H. Anderson, David N. Bowditch, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-6344 (National Aeronautics and Space Administration ;, 1971), by Edwin E. Davenport, Jarrett K. Huffman, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• The aerodynamic characteristics of several thick delta wings at Mach numbers to 6 and angles of attack 50 degree (National Aeronautics and Space Administration, 1960), by John B. McDevitt, John V. Rakich, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Investigation of the subsonic and supersonic release characteristics of an externally carried fuel tank from a 1/40-scale model of a bomber airplane (National Aeronautics and Space Administration, 1961), by William F. Hinson and Langley Research Center (page images at HathiTrust)
• Static longitudinal aerodynamic characteristics at transonic speeds of a lenticular-shaped reentry vehicle (National Aeronautics and Space Administration, 1960), by John P. Mugler, Walter B. Olstad, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• A buffet investigation at high subsonic speeds of wing-fuselage-tail combinations having sweptback wings with NACA 64A thickness distributions, fences, a leading-edge extension, and body contouring (National Advisory Committee for Aeronautics, 1957), by Fred B. Sutton, J. Walter Lautenberger, United States. National Advisory Committee for Aeronautics, and Ames Research Center (page images at HathiTrust)
• Air-flow surveys in the vicinity of representative NACA 1-series cowlings (National Advisory Committee for Aeronautics, 1948), by Robert W. Boswinkle, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Aerodynamic characteristics of several 6-percent-thick airfoils at angles of attack from 0 to 20 degrees at high subsonic speeds (National Advisory Committee for Aeronautics, 1949), by Bernard N. Daley, Douglas R. Lord, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36©� (National Advisory Committee for Aeronautics, 1952), by Morton Cooper, Lowell E. Hasel, John P. Gapcynski, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• The effect of nose radius and shape of the aerodynamic characteristics of a fuselage and a wing-fuselage combination at angles of attack (National Advisory Committee for Aeronautics, 1953), by John P. Gapcynski, A. Warner Robins, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Experimental determination of the effects of frequency and amplitude of oscillation on the roll-stability derivatives for a 60©� delta-wing airplane model (National Advisory Committee for Aeronautics, 1958), by Lewis R. Fisher, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Preliminary investigation of shield to improve angle-of-attack performance of nacelle-type inlet (National Advisory Committee for Aeronautics, 1957), by Milton A. Beheim, Thomas G. Piercy, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Three-degree-of-freedom evaluation of the longitudinal transfer functions of a supersonic canard missile configuration including changes in forward speed (National Advisory Committee for Aeronautics, 1954), by Ernest C. Seaberg, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Wind-tunnel investigation of effect of sweep on rolling derivatives at angles of attack up to 13©� and at high subsonic Mach numbers, including a semiempirical method of estimating the rolling derivatives (National Advisory Committee for Aeronautics, 1954), by James W. Wiggins, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• A modification to thin-airfoil-section theory, applicable to arbitrary airfoil sections, to account for the effects of thickness on the lift distribution (National Advisory Committee for Aeronautics, 1951), by David Graham and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation of the aerodynamic characteristics of a model wing-propeller combination and of the wing and propeller separately at angles of attack up to 90©� (National Advisory Committee for Aeronautics, 1954), by John W. Draper, Richard E. Kuhn, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Effect of longitudinal and lateral controls on winged reentry configuration at mach 1.97 and angles of attack up to 90° (National Aeronautics and Space Administration, 1961), by Gerald V. Foster and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Heat-transfer and pressure measurements of a 1/7-scale model of a Mercury capsule at angles of attack from 0° to ±20° at mach numbers of 3.50 and 4.44 (National Aeronautics and Space Administration, 1961), by Nancy L. Taylor, Paige B. Burbank, Ward F. Hodge, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Subsonic flight tests of a 1/7-scale radio-controlled model of the North American X-15 airplane with particular reference to high angle-of-attack conditions (National Aeronautics and Space Administration, 1960), by Donald E. Hewes, James L. Hassell, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• An investigation at subsonic speeds of aerodynamic charactersitcs at angles of attack from -4⁰ to 100⁰ of a delta-wing reentry configuration having folding wingtip panels (National Aeronautics and Space Administration, Langley Research Center, 1960), by Bernard Spencer and Langley Research Center (page images at HathiTrust)
• Heat transfer to bodies at angles of attack (National Advisory Committee for Aeronautics, 1957), by William V. Feller, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• A pivoting-cowl-and-spike technique for efficient angle-of-attack operation of supersonic inlets (National Advisory Committee for Aeronautics, 1958), by Nick E. Samanich, Robert W. Cubbison, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Experiments with an airfoil model on which the boundary layer is controlled without the use of supplementary equipment (National Advisory Committee for Aeronautics ;, 1931), by I. H. Abbott and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Theoretical investigation at subsonic speeds of the flow ahead of a slender inclinded parabolic-arc body of revolution and correlation with experimental data obtained at low speeds (National Advisory Committee for Aeronautics, 1954), by William Letko, Edward C. B. Danforth, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• NACA Wartime Reports. Series L. (National Advisory Committee for Aeronautics, 1945), by Robert E. Pendley, Langley Aeronautical Laboratory, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Three dimensional flow studies over a spinning cone at angle of attack (Aberdeen Proving Ground, Maryland : USA, Ballistic Research Laboratories, 1974., 1974), by H. A. Dwyer, U.S. Army Ballistic Research Laboratory, and Davis. Department of Mechanical Engineering University of California (page images at HathiTrust)
• Lift-curve slopes determined in flight on a flexible swept-wing jet bomber (Washington, D.C. : National Advisory Committee for Aeronautics, [1956], 1956), by William S. Aiken, Raymond A. Fisher, Langley Aeronautical Laboratory, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• An experimental investigation of the aerodynamic characteristics of slender hypersonic vehicles at high angles of attack (White Oak, Maryland : United States Naval Ordnance Laboratory, 1968., 1968), by Robert H. Feldhuhn, Lionel Pasiuk, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Calculation of magnus forces on axisymmetric bodies at small angles of attack with incompressible turbulent boundary layers (White Oak, Maryland : United States Naval Ordnance Laboratory, 1972., 1972), by Neal Tetervin and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Prediction of normal force, pitching moment, and yawing force on bodies of revolution at angles of attack up to 50 degrees using a concentrated vortex flow-field model (White Oak, Maryland : United States Naval Ordnance Laboratory, 1973., 1973), by Andrew B. Wardlaw, W. J. Glowacki, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Surface flow angles on an ogive cylinder at angle of attack in supersonic flow (Albuquerque, New Mexico : Sandia Laboratories, 1971., 1971), by Harold R. Vaughn, Oscar L. George, Sandia Corporation, and U.S. Atomic Energy Commission (page images at HathiTrust)
• The characteristics of a laminar boundary layer on a spinning tangent ogive cylinder at angle of attack (Albuquerque, New Mexico : Sandia Laboratories, 1972., 1972), by H. R. Vaughn, Oscar L. George, Sandia Corporation, and U.S. Atomic Energy Commission (page images at HathiTrust)
• An Investigation of the damping in pitch characteristics of a ten degree cone (Silver Spring, Maryland : Naval Surface Weapons Center, White Oak Laboratory, 1975., 1975), by A. M. Morrison, W. R. Lawrence, J. E. Holmes, and Naval Surface Weapons Center. White Oak Laboratory (page images at HathiTrust)
• Experimental study of forces and moments on circular bodies at high angle of attack (Silver Spring, Maryland : Naval Surface Weapons Center, White Oak Laboratory, 1975., 1975), by Jr. Wardlaw and Naval Surface Weapons Center. White Oak Laboratory (page images at HathiTrust)
• Induced side forces on bodies of revolution at high angle of attack (Silver Spring, Maryland : Naval Surface Weapons Center, White Oak Laboratory, 1975., 1975), by Jr. Wardlaw, A. M. Morrison, and Naval Surface Weapons Center. White Oak Laboratory (page images at HathiTrust)
• Transonic flow past a wedge at zero angle of attack (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1952., 1952), by Leon Trilling, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Massachusetts Institute of Technology. Aeronautical Engineering Department (page images at HathiTrust)
• A method for predicting three-degree-of-freedom store separation trajectories at speeds up to the critical speed (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1974., 1974), by Frederick K. Goodwin, Marnix F. E. Dillenius, Jack Norman Nielsen, Air Force Flight Dynamics Laboratory (U.S.), and Nielsen Engineering & Research (page images at HathiTrust)
• Hypersonic boundary layer transition experiments (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1980., 1980), by Kenneth F. Stetson, Air Force Wright Aeronautical Laboratories, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Mass injection and jet flow simulation effects on transonic afterbody drag (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 Wladimiro Calarese, Ronald E. Walterick, United States. Air Force. Systems Command, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• High angle of attack missile aerodynamics at Mach numbers 0.30 to 1.5 (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1980., 1980), by Valentine Dahlem, Christian E. G. Przirembel, Donald E. Shereda, Jack I. Flaherty, Air Force Wright Aeronautical Laboratories, Air Force Flight Dynamics Laboratory (U.S.), and Rutgers University (page images at HathiTrust)
• Investigation of flying qualities of military aircraft at high angles of attack. Volume I, Technical results (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1974., 1974), by Donald E. Johnston, Jeffrey R. Hogge, Irving L. Ashkenas, Air Force Flight Dynamics Laboratory (U.S.), and Inc Systems Technology (page images at HathiTrust)
• Investigation of flying qualities of military aircraft at high angles of attack. Volume II, Appendices (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1974., 1974), by Donald E. Johnston, Gary L. Teper, Jeffrey R. Hogge, Air Force Flight Dynamics Laboratory (U.S.), and Inc Systems Technology (page images at HathiTrust)
• Investigation of high-AOA flying qualities : criteria and design guides (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1981., 1981), by Donald D. Johnston, Robert K. Heffley, Air Force Flight Dynamics Laboratory (U.S.), Air Force Wright Aeronautical Laboratories, and Inc Systems Technology (page images at HathiTrust)
• Inlet technology for air-launched missiles. Volume II. Forebody flow field test results (Wright-Patterson Air Force Base, Ohio : Air Force Aero Propulsion Laboratory, Air Force Systems Command, United States Air Force, 1972., 1972), by Francis R. Zumpano, United Aircraft Corporation. Research Laboratories, United States. Air Force. Systems Command, and Air Force Aero Propulsion Laboratory (U.S.) (page images at HathiTrust)
• Effects of mass transfer into laminar and turbulent boundary layers over cones at angle of attack (Blacksburg, Virginia : Virginia Polytechnic Institute and State University, 1975., 1975), by Michael C. Frieders, United States. Air Force. Systems Command. Arnold Engineering Development Center, and Virginia Polytechnic Institute and State University (page images at HathiTrust)
• Development of a computer program for store airloads prediction technique (Eglin Air Force Base, Florida : Air Force Armament Laboratory, Armamanet Development and Test Center, Air Force Systems Command, United States Air Force, 1976., 1976), by A. R. Rudnicki, C. J. Neitzel, M. H. McCloskey, United States. Air Force. Systems Command, Air Force Armament Laboratory, and Vought Corporation (page images at HathiTrust)
• Pressure test of three elliptic missile body configuratins (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1985., 1985), by Marvin E. Sellers, Calspan Corporation, and United States. Air Force. Systems Command. Arnold Engineering Development Center (page images at HathiTrust)
• An algorithm for computing the range of trimable angle of attack for aircraft experiencing effector failures (Wright Patterson Air Force Base, Ohio : Air Vehicles Directorte, Air Force Research Laboratory, Air Force Materiel Command, 2002., 2002), by Joseph Kaloust, David B. Doman, Hope College, and Ohio). Air Vehicles Directorate Air Force Research Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
• Calculation of high angle of attack aerodynamics of fighter configurations. Vol. II, User manual for VORSTAB-II (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Directorate, Wright Laboratory, Air Force Systems Command, United States Air Force, 1991., 1991), by C. Edward Lan, R. K. Tripathi, S. C. Mehrotra, P. Sundaram, Suei Chin, H. Emdad, Vigyan Research Associates, Air Force Flight Dynamics Laboratory (U.S.), Ohio) Wright Laboratory (Wright-Patterson Air Force Base, and United States. Air Force. Systems Command (page images at HathiTrust)
• Calculation of high angle of attack aerodynamics of fighter configurations. Vol. I, Steady (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Directorate, Wright Laboratory, Air Force Systems Command, United States Air Force, 1991., 1991), by C. Edward Lan, R. K. Tripathi, S. C. Mehrotra, P. Sundaram, Suei Chin, H. Emdad, Vigyan Research Associates, Air Force Flight Dynamics Laboratory (U.S.), Ohio) Wright Laboratory (Wright-Patterson Air Force Base, and United States. Air Force. Systems Command (page images at HathiTrust)
• Select means for determining unsteady aerodynamic response characteristics from static data (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)
• Controlled experiments on instabilities and transition to turbulence on elliptic cones at hypersonic mach numbers (Arlington, Virginia : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 2002., 2002), by Thomas C. Corke, University of Notre Dame, and United States. Air Force. Office of Scientific Research (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)
• Calculation of high angle of attack aerodynamics of fighter configurations. Vol. III, Unsteady (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Directorate, Wright Laboratory, Air Force Systems Command, United States Air Force, 1991., 1991), by C. Edward Lan, R. K. Tripathi, S. C. Mehrotra, P. Sundaram, Suei Chin, H. Emdad, Vigyan Research Associates, Air Force Flight Dynamics Laboratory (U.S.), Ohio) Wright Laboratory (Wright-Patterson Air Force Base, and United States. Air Force. Systems Command (page images at HathiTrust)
• Nonlinear normal and axial force indicial responses for a two dimensional airfoil (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 1991., 1991), by G. M. Graham, K. C. Fang, M. Islam, Ohio University, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Static and rotational aerodynamic data from O° to 90° angle of attack for a series of basic and altered forebody shapes (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Wright Research and Development Center, Air Force Systems Command, United States Air Force, 1989., 1989), by William Bihrle, E. Dickes, B. Barnhart, Inc Bihrle Applied Research, Wright Research and Development Center, Air Force Flight Dynamics Laboratory (U.S.), and United States. Air Force. Systems Command (page images at HathiTrust)
• The Influence of high angle of attack flow pheomena on the dynamic stability of slender missiles (Eglin Air Force Base, Florida : Air Force Armament Laboratory, Armamaent Division, Air Force Systems Command, United States Air Force, 1983., 1983), by James M. Jenista, Robert C. Nelson, United States. Air Force. Systems Command, Air Force Armament Laboratory, and University of Notre Dame. |b Department of Aerospace and Mechanical Engineering (page images at HathiTrust)
• A Selective bibliography on high-angle-of-attack aerodynamics of aircraft and aircraft components at subsonic speeds (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Control Criteria Branch, Flight Control Division, Air Force Systems Command, United States Air Force, 1974., 1974), by Henry W. Woolard and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Aircraft motion sensitivity to dynamic stability derivatives (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1980., 1980), by T. F. Langham, Inc ARO, United States. Air Force. Arnold Air Force Base, and United States. Air Force. Systems Command. Arnold Engineering Development Center (page images at HathiTrust)
• Captive aircraft testing at high angles of attack (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1981., 1981), by R. W. Butler, J. P. Christopher, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Comments on the use of measurements of the effective moment parameter (C m alpha) (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1981., 1981), by C. J. Welsh, Calspan Field Services, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Operational utility survey: supermaneuverability (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1984., 1984), by William L. Hamilton, Andrew M. Skow, Air Force Wright Aeronautical Laboratories, Air Force Flight Dynamics Laboratory (U.S.), and Eidetics Incorporated (page images at HathiTrust)
• An Investigation of the effects of nose geometry on the aerodynamic characteristics of a full scale vertical launch ASROC forebody at M₀₀ = 0.30 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1987., 1987), by R. M. Vaeth, Calspan Corporation, Naval Ocean Systems Center (U.S.), and United States. Air Force. Systems Command. Arnold Engineering Development Center (page images at HathiTrust)
• Static stability test of three elliptic missile body configurations (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1985., 1985), by Marvin E. Sellers, Calspan Corporation, and United States. Air Force. Systems Command. Arnold Engineering Development Center (page images at HathiTrust)

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