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Oscillating wings (Aerodynamics)

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• Aerofoils
• Flutter (Aerodynamics)
• Oscillations

• Airplanes -- Wings

• Oscillating wings (Aerodynamics) -- Computer programs
• Oscillating wings (Aerodynamics) -- Computer simulation
• Oscillating wings (Aerodynamics) -- Mathematical models

• Wings, Oscillating (Aerodynamics)

• Investigation of a method for the measurement of subsonic oscillatory aerodynamic influence coefficients (Wright Air Development Center, Air Research and Development Command, U.S. Air Force, 1957), by H. Norman Abramson and Paul A. Beckmann (page images at HathiTrust)
• Calculation of viscous effects on transonic flow for oscillating airfoils and comparisons with experiment (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1987), by James T. Howlett, Samuel R. Bland, and Langley Research Center (page images at HathiTrust)
• Computer program for supersonic kernel-function flutter analysis of thin lifting surfaces (National Aeronautics and Space Administration ;, 1974), by Herbert J. Cunningham and Langley Research Center (page images at HathiTrust)
• Application of Zimmerman flutter-margin criterion to a wind-tunnel model (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Robert M. Bennett and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Analysis of oscillatory motion of a light airplane at high values of lift coefficient (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by James G. Batterson, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
• Flutter of a low-aspect-ratio rectangular wing (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1989), by Stanley R. Cole and Langley Research Center (page images at HathiTrust)
• Influence of display and control compatibility on pilot-induced oscillations (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Marvin C. Waller, Lee H. Person, Randall L. Harris, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Application of model control to wing-flutter suppression (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Aaron J. Ostroff, Samuel Pines, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Analysis of oscillatory pressure data including dynamic stall effects (National Aeronautics and Space Administration ;, 1974), by F. O. Carta, Langley Research Center, and United Aircraft Corporation. Research Laboratories (page images at HathiTrust)
• NASA TR R-150 (National Aeronautics and Space Administration ;, 1962), by Robert G. Thomson, Edwin T. Kruszewski, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-2360 (National Aeronautics and Space Administration :, 1964), by Robert C. Goetz, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-3501 (National Aeronautics and Space Administration :, 1966), by M. C. Sandford, Irving Abel, Charles L. Ruhlin, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Flight investigation of XB-70 structural response to oscillatory aerodynamic shaker excitation and correlation with analytical results (National Aeronautics and Space Administration ;, 1973), by James M. McKay, John H. Wykes, Eldon E. Kordes, United States National Aeronautics and Space Administration, and Flight Research Center (U.S.) (page images at HathiTrust)
• Analysis of the development of dynamic stall based on oscillating airfoil experiments (National Aeronautics and Space Administration ;, 1977), by Lawrence W. Carr, William J. McCroskey, Kenneth W. McAlister, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Some effects of tip fins of wing flutter characteristics (National Aeronautics and Space Administration ;, 1974), by Robert C. Goetz, Robert V. Doggett, and Langley Research Center (page images at HathiTrust)
• NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1945), by Theodore Theodorsen, Arthur A. Regier, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Historical background and design evolution of the transonic aircraft technology supercritical wing (National Aeronautical and Space Administration, Scientific and Technical Information Branch ;, 1981), by Theodore G. Ayers, James B. Hallissy, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Hugh L. Dryden Flight Research Center (page images at HathiTrust)
• A theoretical and experimental study of wind-tunnel-wall effects on oscillating air forces for two-dimensional subsonic compressible flow (National Advisory Committee for Aeronautics, 1953), by Harry L. Runyan, A. Gerald Rainey, Donald S. Woolston, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Some measurements of aerodynamic forces and moments at subsonic speeds on a rectangular wing of aspect ratio 2 oscillating about the midchord (National Advisory Committee for Aeronautics, 1953), by Edward Widmayer, Sumner A. Leadbetter, Sherman A. Clevenson, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (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)
• 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, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• On the theory of oscillating airfoils of finite span in subsonic compressible flow (National Advisory Committee for Aeronautics, 1949), by Eric Reissner and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Extension of the theory of oscillating airfoils of finite span in subsonic compressible flow (National Advisory Committee for Aeronautics, 1951), by Eric Reissner and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Experimental aerodynamic derivatives of a sinusoidally oscillating airfoil in two-dimensional flow (National Advisory Committee for Aeronautics, 1951), by Robert L. Halfman and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• On the kernel function of the integral equation relating the lift and downwash distributions of oscillating finite wings in subsonic flow (National Advisory Committee for Aeronautics, 1954), by Charles E. Watkins, Donald S. Woolston, Harry L. Runyan, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Theoretical and experimental investigation of the effect of tunnel walls on the forces on an oscillating airfoil in two-dimensional subsonic compressible flow (National Advisory Committee for Aeronautics, 1955), by Harry L. Runyan, A. Gerald Rainey, Donald S. Woolston, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Lift and moment on oscillating triangular and related wings with supersonic edges (National Advisory Committee for Aeronautics, 1951), by Herbert C. Nelson and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Theoretical and experimental pressure distributions on low aspect ratio wings oscillating in an incompressible flow. (M.I.T. Aeroelastic and Structures Research Laboratory, 1954), by William R. Laidlaw (page images at HathiTrust)
• Experimental verification of the theory of oscillating airfoils (1940), by Abe Silverstein, U. T. Joyner, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Transonic wind tunnel tests on an oscillating wing with external stores. Part II, The clean wing (Wright-Patterson Air Force Base : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1979., 1979), by H. Tijdeman, C. M. Siebert, P. Schippers, R. Roos, R. Poestkoke, A. J. Persoon, A. N. Kraan, J. W. G. van Nunen, Nationaal Lucht- en Ruimtevaartlaboratorium (Netherlands), and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Small disturbance transonic flows about oscillating airfoils (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1974., 1974), by R. M. Traci, H. K. Cheng, J. L Farr, E. D. Albano, Air Force Flight Dynamics Laboratory (U.S.), and inc Science Applications (page images at HathiTrust)
• Simulation of the transient aeroelastic response of a realistic aircraft configuration during three-dimensional high G maneuvers (Arlington, Virginia. : Air Force Office of Scientific Research, 2001., 2001), by Charbel Farhat, University of Colorado Boulder. Department of Aerospace Engineering, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• The oscillating airfoil in compressible flow. Part II, A review of graphical and numerical data (Wright-Patterson Air Force Base, Ohio : Air Documents Division, Intelligence Dept., Air Materiel Command, [1948?], 1948), by Samuel Noah Karp, Herschel Weil, and United States. Army Air Forces. Air Matériel Command (page images at HathiTrust)
• Limit Cycle Oscillations (LCO) and nonlinear aeroelastic wing response (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, United States Air Force, 1996., 1996), by E. H. Dowell, United States. Air Force. Office of Scientific Research, and Duke University. Office of Research Administration and Policy (page images at HathiTrust)
• Coupling linearized far-field boundary conditions with nonlinear near-field solutions in transonic flow (Bolling Air Force Base, D. C. : Air Force Office of Scientific Research, United States Air Force, 1988., 1988), by William Rowe, F. Edward Ehlers, Boeing Commercial Airplane Company, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Flexible-wing manned test vehicle (Fort Eustis, Virginia : U.S. Army Transportation Research Command, 1962., 1962), by Ryan Aeronautical Company and United States. Army. Transportation Research Command (page images at HathiTrust)
• Measurement of aerodynamic forces on an oscillating airfoil (Fort Eustis, Virginia : U.S. Army Aviation Materiel Laboratories, 1970., 1970), by Richard I. Windsor, U.S. Army Aviation Materiel Laboratories, and University of Maryland at College Park (page images at HathiTrust)

• Computer programs for calculating small disturbance transonic flows about oscillating airfoils (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1974., 1974), by J. L. Farr, E. D. Albano, R. M. Traci, Air Force Flight Dynamics Laboratory (U.S.), and Inc Systems Technology (page images at HathiTrust)

• Computation of the transonic perturbation flow fields around two- and three-dimensional oscillating wings (National Aeronautics and Space Administration ;, 1975), by W. H. Weatherill, James D. Sebastian, F. Edward Ehlers, Langley Research Center, and Boeing Commercial Airplane Company (page images at HathiTrust)
• A finite difference method for the solution of the transonic flow around harmonically oscillating wings (National Aeronautics and Space Administration ;, 1974), by F. Edward Ehlers, Langley Research Center, and Boeing Commercial Airplane Company (page images at HathiTrust)
• Calculation of unsteady transonic aerodynamics for oscillating wings with thickness (National Aeronautics and Space Administration ;, 1975), by S. Y. Ruo, J. G. Theisen, Langley Research Center, and Lockheed-Georgia Company (page images at HathiTrust)

• An analytical technique for predicting the characteristics of a flexible wing equipped with an active flutter-suppression system and comparison with wind-tunnel data (National Aeronautics and Space Administration, Scientific and Technical Information Office, 1979), by Irving Abel (page images at HathiTrust)

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

• Linearized theory of conical supersonic flow with application to triangular wings (North American Aviation, Engineering Dept., 1947), by North American Aviation and Wallace D. Hayes (page images at HathiTrust)
• Basic wing and airfoil theory. (McGraw-Hill, 1951), by Alan Pope (page images at HathiTrust)
• Spanwise air-load distribution. War Department, Air Corps. Navy Department, Bureau of Aeromautics. Department of Commerce, Bureau of Air Commerce. (U.S. Govt. Print. Off., 1938), by United States. Army-Navy-Commerce Committee on Aircraft Requirements (page images at HathiTrust)
• A Study of unsymmetrical-loading conditions (Washington D.C. : National Advisory Committee for Aeronautics, 1940., 1940), by Henry A. Pearson and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Distribution of temperatures over an airplane wing with reference to the phenomena of ice formation (National Advisory Commitee for Aeronautics, 1938), by Edmond Brun and United States. National Advisory Commitee for Aeronautics (page images at HathiTrust)
• The use of plywood in airplane wing beams (1925), by George Emil Heck (page images at HathiTrust)
• The flutter of aeroplane wings. (H. M. Stationery Off., 1929), by R. A. Frazer (page images at HathiTrust)
• Recent research on the determination of natural modes and frequencies of aircraft wing structures (National Advisory Committee for Aeronautics, 1956), by Langley Aeronautical Laboratory, John M. Hedgepeth, and United States. National Advisory Committee for Aeronautics. Advisory Group for Aeronautical Research and Development (page images at HathiTrust)
• Caratteristiche aerodinamiche di ali. (Tipografia Befani, 1925), by Italy. Direzione generale del genio aeronautico (page images at HathiTrust)
• Thermal effects on static aeroelastic stability and control. (Wright Air Development Center, Air Research and Development Command, U. S. Air Force, 1959), by Bell Aircraft Corp (page images at HathiTrust)
• Effect of thermal stresses on the aeroelastic stability of supersonic wings. (Cornell Aeronautical Laboratory, Inc., 1956), by Maurice A. Biot (page images at HathiTrust)
• Response of a cantilever beam to non-stationary and stationary random excitation (Air Force Materials Laboratory, Air Force Systems Command, 1968), by P. Y. Wang and Masanobu Shinozuka (page images at HathiTrust)
• Subsonic longitudinal and lateral-directional characteristics of a forward-swept-wing fighter configuration at angles of attack up to 47⁰ (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1987), by Michael J. Mann, Charles H. Fox, Jarrett K. Huffman, and Langley Research Center (page images at HathiTrust)
• Natural laminar flow experiments on modern airplane surfaces (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by Bruce J. Holmes, Long P. Yip, Clifford J. Obara, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Planform curvature effects on flutter characteristics of a wing with 56 ̊leading-edge sweep and panel aspect ratio of 1.14 (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ;, 1991), by Donald F. Keller, Theresa L. Pinkerton, M. C. Sandford, and Langley Research Center (page images at HathiTrust)
• Loading tests of a wing structure for a hypersonic aircraft (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Roger A. Fields, William H. Siegel, Lawrence F. Reardon, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Supersonic wings with significant leading-edge thrust at cruise (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by A. Warner Robins, Robert J. Mack, Harry W. Carlson, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Transonic aerodynamic damping and oscillatory stability in yaw and pitch for a model of a variable-sweep supersonic transport airplane (National Aeronautics and Space Administration ;, 1966), by Bruce R. Wright, Benjamin T. Averett, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Transonic aerodynamic characteristics of a tailless fixed-wing supersonic transport model (National Aeronautics and Space Administration ;, 1966), by Edward J. Ray, Robert T. Taylor, and Langley Research Center (page images at HathiTrust)
• Investigation of the static lift capability of a low-aspect-ratio wing operating in a powered ground-effect mode (National Aeronautics and Space Administration ;, 1974), by Jarrett K. Huffman, Charlie M. Jackson, and Langley Research Center (page images at HathiTrust)
• Aerothermal analysis of a wing-elevon cove with variable leakage (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)
• Estimation of wing nonlinear aerodynamic characteristics at supersonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Harry W. Carlson, Robert J. Mack, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Wind-tunnel investigation of aerodynamic loading on a 0.237-scale model of a remotely piloted research vehicle with a thick, high-aspect-ratio supercritical wing (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Thomas A. Byrdsong, Cuyler W. Brooks, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Effects of winglets on a first-generation jet transport wing. VII, Sideslip effects on winglet loads and selected wing loads at subsonic speeds for a full-span model (National Aeronautics and Space Administration ;, 1986), by Robert R. Meyer, Peter F. Covell, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Experimental results of winglets on first, second, and third generation jet transports (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Stuart G. Fletcher, Peter F. Jacobs, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Dynamic response of a forward-swept-wing model at angles of attack up to 15 at a Mach number of 0.8 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Robert V. Doggett, Rodney H. Ricketts, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Aerodynamic characteristics of a high-wing transport configuration with an over-the-wing Nacelle-pylon arrangement (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by William P. Henderson, William Kelly Abeyounis, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Experimental investigation of leading-edge thrust at supersonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Richard M. Wood, D. S. Miller, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Spin-tunnel investigation of a 1/13-scale model of the NASA AD-1 oblique-wing research aircraft (U.S. National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by William L. White, James S. Bowman, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Low-speed wind-tunnel investigation of forward-located spoilers and trailing splines as trailing-vortex hazard-alleviation devices on an aspect-ratio-8 wing model (National Aeronautics and Space Administration ;, 1975), by Delwin R. Croom and Langley Research Center (page images at HathiTrust)
• Aileron and Kruger nose flap effectiveness measured on an oblique wing (National Aeronautics and Space Administration ;, 1977), by Edward J. Hopkins, George H. Lovette, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effect of wing flexibility on the experimental aerodynamic characteristics of an oblique wing (National Aeronautics and Space Administration, 1977), by Edward J. Hopkins, Sam C. Yee, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Transonic wind-tunnel investigation of the maneuver potential of the NASA supercritical wing concept : phase I (National Aeronautics and Space Administration ;, 1977), by James B. Hallissy, Theodore G. Ayers, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Stability characteristics for a full-span model at Mach 0.30 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Robert R. Meyer, Langley Research Center, United States Air Force, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Correlation of laser velocimeter measurements over a wing with results of two prediction techniques (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Danny R. Hoad and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Comparison of theoretical and experimental steady wing loads on a space shuttle configuration at Mach numbers of 0.6 and 1.4 (National Aeronautics and Space Administration ;, 1976), by John S. Preisser, Harold E. Lowder, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Flight measurements of lifting pressures for a thin low-aspect-ratio wing at subsonic, transonic, and low supersonic speeds (National Aeronautics and Space Administration ;, 1977), by Thomas A. Byrdsong and United States National Aeronautics and Space Administration (page images at HathiTrust)
• An experimental study of tip shape effects on the flutter of aft-swept, flat-plate wings (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Bryan E. Dansberry, Moses G. Farmer, Jose A. Rivera, and Langley Research Center (page images at HathiTrust)
• Theoretical parametric study of the relative advantages of winglets and wing-tip extensions (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1977), by Harry H. Heyson, Cynthia L. Fulton, Gregory D. Riebe, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Flap effectiveness on subsonic longitudinal aerodynamic characteristics of a modified arrow wing (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by P. Frank Quinto, John W. Paulson, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• In-flight investigation of shuttle tile pressure orifice installations (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Timothy R. Moes, Robert R. Meyer, and Ames Research Center (page images at HathiTrust)
• Theoretical estimation of the transonic aerodynamic characteristics of a supercritical-wing transport model with trailing-edge controls (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by James M. Luckring, Michael J. Mann, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Estimation of leading-edge thrust for supersonic wings of arbitrary planform (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Harry W. Carlson, Robert J. Mack, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Langley Research Center (page images at HathiTrust)
• Pressure and force data for a flat wing and a warped conical wing having a shockless recompression at Mach 1.62 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by David S. Miller, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
• Experimental aerodynamic characteristics for slender bodies with thin wings at angles of attack from 0 ̊to 58 ̊and Mach numbers from 0.6 to 2.0 (National Aeronautics and Space Administration ;, 1976), by Leland H. Jorgensen, Michael H. Howell, and Ames Research Center (page images at HathiTrust)
• Fluctuating loads measured on an over-the-wing supersonic jet model (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by Conrad M. Willis, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Langley Research Center (page images at HathiTrust)
• Optimization and performance calculation of dual-rotation propellers (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Robert E. Davidson and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Experimental and theoretical supersonic lateral-directional stability characteristics of a simplified wing-body configuration with a series of vertical-tail arrangements (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Milton Lamb, James L. Thomas, Wallace C. Sawyer, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
• Effects of wing-leading-edge modifications on a full-scale, low-wing general aviation airplane : wind-tunnel investigation of high-angle-of-attack aerodynamic characteristics (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by William A. Newsom, Dale R. Satran, Langley Research Center, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Joseph L. Johnson (page images at HathiTrust)
• An Analytical procedure for computing smooth transitions between two specified cross sections with applications to blended wing-body configurations (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Raymond L. Barger, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Experimental and analytical study of the longitudinal aerodynamic characteristics of analytically and empirically designed strake-wing confirurations at subcritical speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by John E. Lamar, Neal T. Frink, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
• Wing-alone aerodynamic characteristics for high angles of attack at supersonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Robert L. Stallings, Milton Lamb, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Wind-tunnel investigation of leading-edge thrust on arrow wings in supersonic flow (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Robert J. Mack and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Investigation of the applicability of the free-wing principle to light, general aviation aircraft (National Aeronautics and Space Administration ;, 1972), by Richard F. Porter, Joe H. Brown, Ross G. Luce, Langley Research Center, and Battelle Memorial Institute. Columbus Laboratories (page images at HathiTrust)
• High Reynolds number tests of a C141A aircraft semispan model to investigate shock-induced separation (National Aeronautics and Space Administration ;, 1975), by W. T. Blackerby, J. F. Cahill, Ames Research Center, and Lockheed-Georgia Company (page images at HathiTrust)
• Application of active controls technology to the NASA JetStar airplane (National Aeronautics and Space Administration ;, 1975), by R. H. Lange, Flight Research Center (U.S.), and Lockheed-Georgia Company (page images at HathiTrust)
• A general method for calculating three-dimensional compressible laminar and turbulent boundary layers on arbitrary wings (National Aeronautics and Space Administration ;, 1977), by Tuncer Cebeci, Judy A. Ramsey, Kalle Kaups, McDonnell Douglas Corporation, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• The inviscid pressure field on the tip of a semi-infinite wing and its application to the formation of a tip vortex (National Aeronautics and Space Administration ;, 1976), by G. F. Hall and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Wind tunnel and analytical investigation of over-the-wing propulsion/air frame interferences for a short-haul aircraft at Mach numbers from 0.6 to 0.78 (National Aeronautics and Space Administration ;, 1977), by O. D. Wells, Douglas Aircraft Company, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Hypersonic cruise vehicle wing structure evaluation (National Aeronautics and Space Administration, 1970), by Kenneth A. Mason, P. P. Plank, United States National Aeronautics and Space Administration, Langley Research Center, and Lockheed Missiles and Space Company (page images at HathiTrust)
• Analysis of wing slipstream flow interaction (National Aeronautics and Space Administration, 1970), by Antony Jameson, United States National Aeronautics and Space Administration, Ames Research Center, and Grumman Aerospace Corporation (page images at HathiTrust)
• A design summary of stall characteristics of straight wing aircraft (National Aeronautics and Space Administration ;, 1971), by M. A. McVeigh, E. Kisielowski, United States National Aeronautics and Space Administration, Langley Research Center, and Dynasciences Corporation. Scientific Systems Division (page images at HathiTrust)
• NASA CR-1523 (National Aeronautics and Space Administration ;, 1970), by Richard F. Porter, Joe H. Brown, United States National Aeronautics and Space Administration, Ames Research Center, and Battelle Memorial Institute (page images at HathiTrust)
• Wind tunnel interference factors for high-lift wings in closed wind tunnels (National Aeronautics and Space Administration, 1973), by Robert G. Joppa, Langley Research Center, and University of Washington (page images at HathiTrust)
• A System for aerodynamic design and analysis of supersonic aircraft. (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by R. G. Coleman, J. L. Lundry, W. D. Middleton, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Analytical study of a free-wing/free-trimmer concept (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Richard F. Porter, Battelle Memorial Institute. Columbus Laboratories, Hugh L. Dryden Flight Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Subsonic panel method for designing wing surfaces from pressure distribution (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by D. R. Bristow, J. Dennis Hawk, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• A method for computing the leading-edge suction in a higher-order panel method (National Aeronautical and Space Administration, Scientific and Technical Information Office ;, 1984), by F. Edward Ehlers, Marjorie E. Manro, Boeing Commercial Airplane Company, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Langley Research Center (page images at HathiTrust)
• A unified viscous theory of lift and drag of 2-D thin airfoils and 3-D thin wings (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ;, 1991), by John E. Yates and Titan Corporation. California Research & Technology Division. A.R.A.P. Group (page images at HathiTrust)
• Aeroelastic loads prediction for an arrow wing (National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1983), by Christopher J. Borland, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
• Study of supersonic wings employing the attainable leading-edge thrust concept (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by W. D. Middleton, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Boeing Commercial Airplane Company, and Langley Research Center (page images at HathiTrust)
• Numerical optimization techniques for bound circulation distribution for minimum induces drag of nonplanar wings : basic formulations (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by John Kuhlman, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Rotary balance data for a single-engine general aviation design having a high aspect-ratio canard for an angle-of-attack range of 30 ̊to 90 ̊ (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by William Mulcay, Robert A. Rose, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Extended analytical study of the free-wing/free-trimmer concept (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by Richard F. Porter, Rodolfo D. Vergara, David W. Hall, Battelle Memorial Institute. Columbus Laboratories, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Hugh L. Dryden Flight Research Center (page images at HathiTrust)
• Correlation of data related to shock-induced trailing-edge separation and extrapolation to flight Reynolds number (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by J. F. Cahill, P. C. Connor, Ames Research Center, and Lockheed-Georgia Company (page images at HathiTrust)
• A systematic kernel function procedure for determining aerodynamic forces on oscillating or steady finite wings at subsonic speeds (Langley Research Center ;, 1959), by Charles E. Watkins, Herbert J. Cunningham, Donald S. Wooston, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Theoretical pressure distributions on wings of finite span at zero incidence for mach numbers near 1 (U.S. G.P.O., 1961), by Alberta Y. Alksne, John R. Spreiter, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• Extension of leading-edge-suction analogy to wings with separated flow around the side edges at subsonic speeds (National Aeronautics and Space Administration ;, 1974), by John E. Lamar and Langley Research Center (page images at HathiTrust)
• Theoretical aerodynamics of upper-surface-blowing jet-wing interaction (National Aeronautics and Space Administration ;, 1975), by C. Edward Lan, James F. Campbell, and Langley Research Center (page images at HathiTrust)
• Pressure distributions on a cambered wing-body configuration at subsonic Mach numbers (National Aeronautics and Space Administration ;, 1975), by William P. Henderson (page images at HathiTrust)
• An improved method for optimum design of mechanically and thermally loaded structures (National Aeronautics and Space Administration ;, 1975), by Howard M. Adelman, R. Narayanaswami, Joanne L. Walsh, and Langley Research Center (page images at HathiTrust)
• NASA TN D-2492 (National Aeronautics and Space Administration ; [For sale by the Office of Technical Services, Department of Commerce, Washington, D.C. 20230], 1965), by Joseph L. Johnson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Subsonic roll-damping characteristics of a series of wings (National Aeronautics and Space Administration ;, 1974), by Richmond P. Boyden and Langley Research Center (page images at HathiTrust)
• Flight investigation of V/STOL height-control requirements for hovering and low-speed flight under visual conditions (National Aeronautics and Space Administration, 1967), by James R. Kelly, Perry L. Deal, John F. Garren, and Langley Research Center (page images at HathiTrust)
• NASA TN D-4401 (National Aeronautics and Space Administration ;, 1968), by K. R. Czarnecki, Russell B. Sorrells, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-4436 (National Aeronautics and Space Administration ;, 1968), by Cuyler W. Brooks, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Calculation of the dynamic longitudinal stability of a tilt-wing V/STOL aircraft and correlation with model flight tests (National Aeronautics and Space Administration, 1968), by Joseph R. Chambers, Sue B. Grafton, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Some divergence characteristics of low-aspect-ratio wings at transonic and supersonic speeds (National Aeronautics and Space Administration :, 1960), by Donald S. Woolston, Herbert J. Cunningham, Frederick W. Gibson, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Simplified lifting-surface theory for flaps on wings of low and moderate aspect ratios (National Aeronautics and Space Administration ;, 1975), by Bradford H. Wick and Ames Research Center (page images at HathiTrust)
• Effects of wing elevation, incidence, and camber on the aerodynamic characteristics of a representative hypersonic cruise configuration at Mach numbers from 0.65 to 10.70 (National Aeronautics and Space Administration; [for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], 1970), by Walter P. Nelms and John A. Axelson (page images at HathiTrust)
• NASA TN D-5856 (National Aeronautics and Space Administration :, 1970), by James P. Peterson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• A high subsonic speed wind-tunnel investigation of winglets on a representative second-generation jet transport wing (National Aeronautics and Space Administration ;, 1976), by Stuart G. Flechner, Richard T. Whitcomb, Peter F. Jacobs, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Low-speed wind-tunnel investigation of span load alteration, forward-located spoilers, and splines as trailing-vortex-hazard alleviation devices on a transport aircraft model (National Aeronautics and Space Administration ;, 1975), by Delwin R. Croom, R. Earl Dunham, and Langley Research Center (page images at HathiTrust)
• Wing-surface-jet interaction characteristics of an upper-surface blown model with rectangular exhaust nozzles and a radius flap (National Aeronautics and Space Administration ;, 1976), by Alvin M. Bloom, William C. Sleeman, William C. Hohlweg, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Theoretical and experimental study of twisted and cambered delta wings designed for a mach number of 3.5 (National Aeronautics and Space Administration ;, 1976), by Russell B. Sorrells, Emma Jean Landrum, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Theoretical and experimental analysis of longitudinal and lateral aerodynamic characteristics of skewed wings at subsonic speeds to high angles of attack (National Aeronautics and Space Administration ;, 1977), by James M. Luckring and United States National Aeronautics and Space Administration (page images at HathiTrust)
• A numerical method for evaluation and utilization of supersonic nacelle-wing interference (National Aeronautics and Space Administration :, 1969), by Robert J. Mack, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• A design approach and selected wind-tunnel results at high subsonic speeds for wing-tip mounted winglets (National Aeronautics and Space Administration ;, 1976), by Richard T. Whitcomb, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Aerodynamic characteristics of a parasol-wing--body combination utilizing favorable lift interference at Mach numbers from 3.00 to 4.63 (National Aeronautics and Space Administration ;, 1968), by Odell A. Morris, Robert J. Mack, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Investigation of lateral-directional dynamic stability of a tilt-wing V/STOL transport (National Aeronautics and Space Administration :, 1970), by Joseph R. Chambers, Sue B. Grafton, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Analytical heat transfer investigation of insulated liquid methane wing tanks for supersonic cruise aircraft (National Aeronautics and Space Administration :, 1970), by Eugene J. Pleban, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
• NASA TN D-4726 (National Aeronautics and Space Administration ;, 1968), by Delma C. Freeman, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Wind-tunnel investigation of V/STOL transport model with six wing-mounted lift fans (National Aeronautics and Space Administration, 1970), by William A. Newsom, Frederick L. Moore, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Lifting-surface theory for calculating the loading induced on a wing by a flap (National Aeronautics and Space Administration ;, 1972), by Wayne Johnson, United States National Aeronautics and Space Administration, Ames Research Center, and U.S. Army Air Mobility Research and Development Laboratory (page images at HathiTrust)
• Investigation of sonic boom generated by thin, nonlifting, rectangular wings (National Aeronautics and Space Administration ;, 1971), by Sanford S. Davis, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5409 (National Aeronautics and Space Administration :, 1969), by Joseph R. Chambers, Ernie L. Anglin, James S. Bowman, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Aerodynamic data on large semispan tilting wing with 0.4-diameter chord, single-slotted flap, and single propeller 0.22 chord below wing (National Aeronautics and Space Administration ;, 1969), by Marvin P. Fink, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Data from a static-thrust investigation of a large-scale general research vtol-stol model in ground effect (National Aeronautics and Space Administration :, 1960), by Robert J. Huston and Matthew M. Winston (page images at HathiTrust)
• Effect of winglets on a first-generation jet transport wing : II, pressure and spanwise load distributions for a semispan model at high subsonic speeds (National Aeronautics and Space Administration ;, 1977), by Lawrence C. Montoya, Peter F. Jacobs, Stuart G. Flechner, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Wind-tunnel investigation of a variable camber and twist wing (National Aeronautics and Space Administration ;, 1977), by James C. Ferris and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effect of winglets on a first-generation jet transport wing : III, pressure and spanwise load distributions for a semispan model at Mach 0.30 (National Aeronautics and Space Administration ;, 1977), by Lawrence C. Montoya, Peter F. Jacobs, Stuart G. Flechner, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-1867 (National Aeronautics and Space Administration :, 1964), by Emma Jean Landrum, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Comparison of several methods for estimating low-speed stability derivatives for two airplane configurations (National Aeronautics and Space Administration ;, 1971), by Herman S. Fletcher, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Contribution to methods for calculating the flow about thin lifting wings at transonic speeds : Analytic expressions for the far field (National Aeronautics and Space Administration ;, 1971), by E. B. Klunker, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• NASA TN D-1815 (National Aeronautics and Space Administration, 1963), by Kenneth P. Spreemann, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Aerodynamic and development characteristics of multistage canopy and suspension-line reefing systems for a twin-keel all-flexible parawing (National Aeronautics and Space Administration ;, 1971), by Harry L. Morgan, Austin D. McHatton, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Low subsonic flight and force investigation of a supersonic transport model with a double-delta wing (National Aeronautics and Space Administration, 1968), by Delma C. Freeman, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-3501 (National Aeronautics and Space Administration :, 1966), by M. C. Sandford, Irving Abel, Charles L. Ruhlin, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Investigation at transonic speeds of loading over a 30 deg sweptback wing of aspect ratio 3, taper ratio 0.2, and NACA 65A004 airfoil section mounted on a body (National Aeronautics and Space Administration :, 1960), by Donald D. Arabian and United States National Aeronautics and Space Administration (page images at HathiTrust)
• A method for calculating aerodynamic loadings on thin wings at a Mach number of 1 (National Aeronautics and Space Administration, 1959), by John L. Crigler and Langley Research Center (page images at HathiTrust)
• Wind-tunnel investigation of a deflected-slipstream cruise-fan V/STOL aircraft wing (National Aeronautics and Space Administration, 1967), by William A. Newsom and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Large-scale wind-tunnel investigation of a model with an external jet-augmented flap (National Aeronautics and Space Administration, 1967), by Jerry V. Kirk, Kiyoshi Aoyagi, David H. Hickey, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Wind-tunnel investigation of sonic-boom characteristics of two simple wing models at Mach numbers from 2.3 to 4.63 (National Aeronautics and Space Administration, 1971), by Davis S. Miller, Odell A. Morris, Harry W. Carlson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Low-speed static wind-tunnel investigation of a half-span fuselage and variable-sweep pressure wing model (National Aeronautics and Space Administration, 1971), by John E. Lamar, L. Wayne McKinney, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• NASA TN D-6234 (National Aeronautics and Space Administration ;, 1971), by Stanley O. Dickinson, Brent K. Hodder, Leo P. Hall, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• Stability and control characteristics of a large-scale deflected slipsteam STOL model with a wing of 5.7 aspect ratio (National Aeronautics and Space Administration, 1971), by V. Robert Page, Thomas N. Aiken, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• Flight loads measurements obtained from calibrated strain-gage bridges mounted externally on the skin of a low-aspect-ratio wing (National Aeronautics and Space Administration ;, 1976), by Clinton V. Eckstrom, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by W. F. Lindsey, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Lift on a bent, flat plate (NACA, 1952), by F. Keune and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Nonlinear theory of a hot-wire anemometer (NACA, 1952), by R. Betchov and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Report on the special field "interference" to the wind tunnel committee in February 1945 (National Advisory Commitee for Aeronautics, 1953), by Hermann Schlichting and United States. National Advisory Commitee for Aeronautics (page images at HathiTrust)
• Experimental pressure distributions over two wing-body combinations at Mach number 1.9 (NACA, 1951), by Barry Moskowitz, Stephen H. Maslen, United States National Advisory Committee for Aeronautics, and Lewis Research Center (page images at HathiTrust)
• Static aerodynamic characteristics of a typical single-engine low-wing general aviation design for an angle-of-attack range of - 8 ̊to 90 ̊ (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by William Bihrle, Paul Pantason, Billy Barnhart, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• An experimental and theoretical investigation of thick wings at various sweep angles in and out of ground effect (National Aeronautics and Space Adminstration, Scientific and Technical Information Branch ;, 1982), by John W. Paulson, Scott O. Kjelgaard, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Theoretical and experimental investigation of the subsonic-flow fields beneath swept and unswept wings with tails of vortex-induced velocities (National Advisory Committee for Aeronautics, 1956), by William J. Alford and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• A comparison at mach numbers up to 0.92 of the calculated and experimental downwash and wake characteristics at various horizonatl tail heights behind a wing with 45 degrees of sweepback (National Advisory Committee for Aeronautics, 1955), by Jack D. Stephenson, Angelo Bandettini, Ralph Selan, and Ames Research Center (page images at HathiTrust)
• Flight tests of a leading-edge area suction on a fighter-type airplane with a 35 degree swept-back wing. (National Advisory Committee for Aeronautics, 1955), by Richard S. Bray, Robert C. Innis, and Ames Research Center (page images at HathiTrust)
• Velocity distributions on two-dimensional wing-duct inlets by conformal mapping (National Advisory Committee for Aeronautics, 1947), by W. Perl, H. E. Moses, and Aircraft Engine Research Laboratory (page images at HathiTrust)
• Influence of the body flow field on the zero-lift wave drag of wing-body combinations modified in accordance with the transonic area rule (National Advisory Committee for Aeronautics, 1956), by William A. Page and Ames Research Center (page images at HathiTrust)
• Development of flow distortions in a full-scale nacelle inlet at mach numbers 0.63 and 1.6 to 2.0 (National Advisory Committee for Aeronautics, 1956), by Thomas G. Piercy, Bruce G. Chiccine, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Effects of aspect ratio on air flow at a high subsonic mach numbers (National Advisory Committee for Aeronautics, 1948), by W. F. Lindsey, Milton D. Humphreys, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Aerodynamic characteristics of a wing with quarter-chord line swept back 35°, aspect ratio 6, taper ratio 0.6, and NACA 65A006 airfoil section. Transonic-bump method (National Advisory Committee for Aeronautics, 1949), by William C. Sleeman, William D. Morrison, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Investigation of the fatigue strength of a full-scale airplane wing structures (National Advisory Committee for Aeronautics, 1951), by Dwight O. Fearnow, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Preliminary study of some factors which affect the stall-flutter characteristics of thin wings (National Advisory Committee for Aeronautics, 1952), by A. Gerald Rainey, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Some effects of external wing tip stores on the rolling effectiveness and drag of plain and half-delta tip ailerons on a 4-percent-thick tapered, unswept wing (National Advisory Committee for Aeronautics, 1954), by Roland D. English, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Effects of wing-body geometry on the lateral-flow angularities at subsonic speeds (National Advisory Committee for Aeronautics, 1956), by Frank S. Malvestuto, William J. Alford, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• A simplified mathematical model for calculating aerodynamic loading and downwash for midwing wing-fuselage combinations with wings of arbitrary plan form (National Advisory Committee for Aeronautics, 1953), by Martin Zlotnick, Samuel W. Robinson, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Transonic wind-tunnel investigation of an unswept wing in combination with a systematic series of four bodies (National Advisory Committee for Aeronautics, 1953), by Bruce B. Estabrooks, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Wind-tunnel investigation of the static lateral stability characteristics of wing-fuselage combinations at high supersonic speeds. Aspect-ratio series (National Advisory Committee for Aeronautics, 1953), by Paul G. Fournier, Andrew L. Byrnes, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Some effects of tail height and wing plan form on the static longitudinal stability characteristics of a small-scale model at high subsonic speeds (National Advisory Committee for Aeronautics, 1954), by Albert G. Few, Thomas J. King, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Experimental determination of effect of structural rigidity on rolling effectiveness of some straight and swept wings at Mach numbers from 0.7 to 1.7 (National Advisory Committee for Aeronautics, 1950), by H. Kurt Strass, Paul E. Purser, E. M. Fields, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Some low-speed wind-tunnel experiments pertaining to the longitudinal stability characteristics of a 35° swept-wing model and an unswept-wing model (National Advisory Committee for Aeronautics, 1953), by Byron M. Jaquet, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Drag due to lift at Mach numbers up to 2.0 (National Advisory Committee for Aeronautics, 1953), by Edward C. Polhamus, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Aerodynamic characteristics at small scale and a Mach number of 1.38 of untapered wings having M and W plan forms (National Advisory Committee for Aeronautics, 1954), by William B. Kemp, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Some theoretical low-speed span loading characteristics of swept wings in roll and sideslip (National Advisory Committee for Aeronautics, 1949), by John D. Bird and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• The effect of torsional flexibility on the rolling characteristics at supersonic speeds of tapered unswept wings (National Advisory Committee for Aeronautics, 1949), by Warren A. Tucker, Robert L. Nelson, 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)
• Theoretical symmetric span loading due to flap deflection for wings of arbitrary plan form at subsonic speeds (National Advisory Committee for Aeronautics, 1951), by John DeYoung and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Method for calculating lift distribtutions for unswept wings with flaps or ailerons by use of nonlinear section lift data (National Advisory Committee for Aeronautics, 1951), by James C. Sivells, Gertrude C. Westrick, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Lift, pitching moment, and span load characteristics of wings at low speed as affected by variations of sweep and aspect ratio (National Advisory Committee for Aeronautics, 1951), by Edward J. Hopkins and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Chordwise and compressibility corrections to slender-wing theory (National Advisory Committee for Aeronautics, 1951), by Harvard Lomax, Loma Sluder, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Applications of Von Karman's integral method in supersonic wing theory (National Advisory Committee for Aeronautics, 1951), by Chieh-Chien Chang and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Analysis of the effects of wing interference on the tail contributions to the rolling derivatives (National Advisory Committee for Aeronautics, 1951), by William H. Michael and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Some theoretical characteristics of trapezoidal wings in supersonic flow and a comparison of several wing-flap combinations (National Advisory Committee for Aeronautics, 1951), by Robert O. Piland and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Effect of aspect ratio on the low-speed lateral control characteristics of unswept untapered low-aspect-ratio wings (National Advisory Committee for Aeronautics, 1951), by Rodger L. Naeseth, William M. O'Hare, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Spin-tunnel investigation of the effects of mass and dimensional variations on the spinning characteristics of a low-wing single-vertical-tail model typical of personal-owner airplanes (National Advisory Committee for Aeronautics, 1951), by Walter J. Klinar, Jack H. Wilson, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Charts and approximate formulas for the estimation of aeroelastic effects on the loading of swept and unswept wings (National Advisory Committee for Aeronautics, 1952), by Franklin W. Diederich, Kenneth A. Foss, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Experimental investigation of base pressure on blunt-trailing-edge wings at supersonic velocities (National Advisory Committee for Aeronautics, 1952), by Dean R. Chapman, Robert H. Kester, William R. Wimbrow, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Deflection and stress analysis of thin solid wings of arbitrary plan form with particular reference to delta wings (National Advisory Committee for Aeronautics, 1952), by Manuel Stein, John M. Hedgepath, J. Edward Anderson, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Charts and approximate formulas for the estimation of aeroelastic effects on the lateral control of swept and unswept wings (National Advisory Committee for Aeronautics, 1952), by Kenneth A. Foss, Franklin W. Diederich, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Lift developed on unrestrained rectangular wings entering gusts at subsonic and supersonic speeds (National Advisory Committee for Aeronautics, 1953), by Harvard Lomax and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Method for calculating the rolling and yawing moments due to rolling for unswept wings with or without flaps or ailerons by use of nonlinear section lift data (National Advisory Committee for Aeronautics, 1953), by Albert P. Martina and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Correlation of calculation and flight studies of the effect of wing flexibility on structural response due to gusts (National Advisory Committee for Aeronautics, 1953), by John C. Houbolt and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Measurement and analysis of wing and tail buffeting loads on a fighter-type airplane (National Advisory Committee for Aeronautics, 1954), by Wilber B. Huston, T. H. Skopinski, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Effect of wing thickness and sweep on the oscillating hinge-moment and flutter characteristics of a flap-type control at transonic speeds (National Aeronautics and Space Administration, 1959), by William C. Moseley, Thomas G. Gainer, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Wind-tunnel investigation of the static and dynamic-rotary stability derivatives of a flat-top wing-body model at Mach numbers of 2.5, 3.0 and 3.5 (National Aeronautics and Space Administration, 1960), by Bedford A. Lampkin, Kenneth C. Endicott, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• The effects of wing plan form on the static longitudinal aerodynamic characteristics of a flat-top hypersonic aircraft at Mach numbers from 0.6 to 1.4 (National Aeronautics and Space Administration, 1960), by Stuart L. Treon, Ames Research Center, and United States National Aeronautics and Space Administration (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)
• Recent information on flap and tip controls (National Advisory Committee for Aeronautics, 1953), by Douglas R. Lord, K. R. Czarnecki, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Longitudinal characteristics of wings (National Advisory Committee for Aeronautics, 1958), by Thomas A. Toll (page images at HathiTrust)
• Theoretical prediction of the side force on stores attached to configurations traveling at supersonic speeds (National Advisory Committee for Aeronautics, 1956), by Percy J. Bobbitt, Kenneth Margolis, Frank S. Malvestuto, Langley Aeronautical Laboratory, and United States. National Adviosry 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)
• Effect of wing-mounted external stores on the lift and drag of the Douglas D-558-II research airplane at transonic speeds (National Advisory Committee for Aeronautics, 1957), by Jack Nugent, Flight Research Center (U.S.), and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• The proper combination of lift loadings for least drag on a supersonic wing (National Advisory Committee for Aeronautics, 1955), by Frederick C. Grant and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Theoretical span load distributions and rolling moments for sideslipping wings of arbitrary plan form in incompressible flow (National Advisory Committee for Aeronautics, 1955), by M. J. Queijo and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Torsion in box wings (National Advisory Committee for Aeronautics, 1931), by John B. Wheatley and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• The Effect of variations in moments of inertia on spin and recovery characteristics of a single-engine low-wing monoplane with various tail arrangements including a twin tail (National Advisory Committee for Aeronautics, 1948), by Anshal I. Neihouse and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Oscillating pressures near a static pusher propeller at tip Mach numbers up to 1.20 with special reference to the effects of the presence of the wing (National Advisory Committee for Aeronautics, 1954), by Harvey H. Hubbard, Leslie W. Lassiter, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• NACA Wartime Reports. Series A. (National Advisory Committee for Aeronautics, 1941), by Lewis A. Rodert, Lawrence A. Clousing, William H. McAvoy, Ames Research Center, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• NACA Wartime Reports. Series L. (National Advisory Committee for Aeronautics, 1945), by James P. Peterson, 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, 1945), by Myron J. Block, S. Katzoff, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Wing-fuselage interference tail buffeting, and air flow about the tail of a low-wing monoplane (Government Printing Office, 1934), by James A. White, Manely J. Hood, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Flutter of low aspect-ratio wings. ([Cambridge, Mass.], 1957), by Massachusetts Institute of Technology (page images at HathiTrust)
• The drag of a delta wing in supersonic flow (Headquarters, Air Matériel Command, Wright-Patterson Air Force Base, 1949), by Eugene A. Carpovich, F. I. Frankl, and Brown University. Graduate Division of Applied Mathematics (page images at HathiTrust)
• The Conversion of aircraft ice crystal measurements into terms of liquid water using simulated data (Hanscom AFB, Massachusetts : Air Force Geophysics Laboratories, Air Force Systems Command, United States Air Force, 1981., 1981), by R. O. Berthel and U.S. Air Force Geophysics Laboratory (page images at HathiTrust)
• Determination of vortex paths by series expansion technique with application to cruciform wings (U.S. Government Printing Office, 1957), by Alberta Y. Alksne and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Effect of aspect ratio on the low-speed lateral control characteristics of untapered low-aspect-ratio wings equipped with flap and with retractable ailerons (U.S. Government Printing Office, 1952), by William M. O'Hare, John R. Hagerman, Rodger L. Naeseth, Jack Fischel, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• General potential theory of arbitrary wing sections (Government Printing Office, 1933), by T. Theodorsen, I. E. Garrick, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Ice accretions and icing effects for modern airfoils (National Aeronautics Administration, Glenn Research Center, 2000), by Harold E. Addy, NASA Glenn Research Center, United States Federal Aviation Administration, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Stochastic modeling of antisymmetric buffet loads on horizontal stabilizers in massively separated flows (Federal Aviation Administration, Office of Aviation Research ;, 1996), by Saeed Farokhi, James E. Locke, Clay S. Mauk, Aerotrech Engineering & Research Corporation, and United States. Federal Aviation Administration. Office of Aviation Research (page images at HathiTrust)
• Structural integrity evaluation of the Lear Fan 2100 aircraft (Federal Aviation Administration, Office of Aviation Research ;, 1996), by H. P. Kan, T. A. Dyer, Langley Research Center, Northrop Corporation. Military Aircraft Division, and United States. Office of Aviation Research (page images at HathiTrust)
• Effects of stiffener/rib separation on damage growth and residual strength (Federal Aviation Administration, Office of Aviation Research ;, 1996), by H. P. Kan, M. Mahler, Langley Research Center, Northrop Corporation. Military Aircraft Division, and United States. Office of Aviation Research (page images at HathiTrust)
• Design charts for predicting downwash angles and wake characteristics behind plain and flapped wings (1940), by Abe Silverstein, S. Katzoff, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Structural weight analysis; general method: wing structures. (Rand Corp., 1949), by F. R. Shanley and Rand Corporation (page images at HathiTrust)
• Prestressed ceramic structures (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1954., 1954), by F. R. Shanley, J. S. Mizushima, R. D. Chipman, R. B. Simonson, R. D. Johnston, F. A. Needham, J. F. Brahtz, W. J. Knapp, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Los Angeles University of California (page images at HathiTrust)
• Gust alleviation study : Part I. Estimation of the control derivatives for flaps, spoilers and other control devices intended for use as gust alleviators (Wright Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1958., 1958), by Arthur L. Jones, Douglas C. Nichols, Charles D. Christopherson, Owen P. Lamb, A. E. Cronk, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Fluidyne Engineering Corporation (page images at HathiTrust)
• Gust alleviation study : Part II. Prediction of the alleviation of gust loads on a rigid restrained wing utilizing wing installed alleviator devices (Wright Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1958., 1958), by Arthur L. Jones, Douglas C. Nichols, Charles D. Christopherson, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Fluidyne Engineering Corporation (page images at HathiTrust)
• Procedures for including temperature effects in structural analyses of elastic wings - part I an equivalent plate method of structural analysis for elevated temperature structures (Wright Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1958., 1958), by William R. Mills, United States. Air Force. Air Research and Development Command, and Wright Air Development Center (page images at HathiTrust)
• Aeroelastic stability and performance characteristics of aircraft with advanced composite sweptforward wing structures (Wright-Patterson Air Force Base : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1978., 1978), by Terry A. Weisshaar, Air Force Flight Dynamics Laboratory (U.S.), and Virginia Polytechnic Institute and State University. Aerospace and Ocean Engineering Department (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)
• Thermal effects on static aeroelastic stability and control : description and results of tests conducted to determine the thermally affected deflectional behavior of corrugated multiweb wing structures (Wright-Patterson Air Force Base, Ohio : Wright Air Development Division, Aeromechanics Branch, Air Research and Development Command, United States Air Force, 1959., 1959), by James F. Quinn, Richard H. Gallagher, Donald Turrentine, Bell Aircraft Corporation, United States. Wright Air Development Division, and United States. Air Force. Air Research and Development Command (page images at HathiTrust)
• Evaluations of methods to predict flutter of wings with external stores (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1970., 1970), by Sidney Siegel, Lowell V. Andrew, Air Force Flight Dynamics Laboratory (U.S.), and North American Rockwell Corporation (page images at HathiTrust)
• Aerodynamic analysis of a fighter aircraft with a higher order paneling method (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 A. R. Dusto, Air Force Flight Dynamics Laboratory (U.S.), Air Force Wright Aeronautical Laboratories, and Boeing Military Airplane Company (page images at HathiTrust)
• Aerodynamic characteristics of non-straight-taper wings (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1966., 1966), by David B. Benepe, J. Bert Webb, Bobby G. Kouri, Air Force Flight Dynamics Laboratory (U.S.), and General Dynamics Corporation. Fort Worth Division (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)
• Subsonic flutter characteristics of a variable sweep wing and horizontal tail combination (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1970., 1970), by Walter J. Mykytow, Michael H. Shirk, Lawrence J. Huttsell, Thomas E. Noll, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Sinusoidal variation ([Washington, D.C.] : [United States Air Force, Office of Scientific Research], [1960], 1960), by Maurice Holt, Bohyun Yim, United States. Air Force. Office of Scientific Research, and Brown University. Division of Applied Mathematics (page images at HathiTrust)
• Linear variation ([Washington, D.C.] : [United States Air Force, Office of Scientific Research], [1960], 1960), by Maurice Holt, Bohyun Yim, United States. Air Force. Office of Scientific Research, and Brown University. Division of Applied Mathematics (page images at HathiTrust)
• Elastic twist of straight wings (Wright-Patterson air force base, Dayton, Ohio : Air Documents Division, Intelligence Department, Headquarters, Air Materiel Command, 1948., 1948), by Walther Gustav Carl Boccius and United States. Army Air Forces. Air Matériel Command (page images at HathiTrust)
• Effect of structural flexibiligy on aircraft loading. Part III, Maneuvering load dynamic overstress (Wright-Patterson Air Force Base, Ohio : United States, Air Force, Air Materiel Command, 1951., 1951), by Gabriel Isakson, Norman P. Hobbs, Massachusetts Institute of Technology. Aeroelastic and Structures Research Laboratory, and United States. Air Force. Air Matériel Command (page images at HathiTrust)

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