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Lift (Aerodynamics) -- Mathematical models

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• Lift (Aerodynamics)
• Aerodynamic load -- Mathematical models
• Aerodynamics -- Mathematical models
• Mathematical models

• Lift (Aerodynamics) -- Computer simulation
• Stalling (Aerodynamics) -- Mathematical models

• Leading-edge slat optimization for maximum airfoil lift (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by Lawrence E. Olson, Clayton J. Guest, Phillip R. McGowan, Ames Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Development of a nonlinear switching function and its application to static lift characteristics of straight wings (National Aeronautics and Space Administration, Scientific and Technical Information Service ;, 1978), by Donald E. Hewes, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• An unsteady lifting surface method for single rotation propellers (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Marc H. Williams, Lewis Research Center, and Purdue University. School of Aeronautics and Astronautics (page images at HathiTrust)
• Aerodynamic influence coefficient method using singularity splines (National Aeronautics and Space Administration ;, 1974), by J. E. Mercer, E. P. Lesferd, J. A. Weber, Ames Research Center, and Boeing Commercial Airplane Company (page images at HathiTrust)
• Steady subsonic flow around finite-thickness wings (National Aeronautics and Space Administration ;, 1975), by Ching-Chiang Kuo, L. Morino, Langley Research Center, and Boston University. Dept. of Aerospace Engineering (page images at HathiTrust)
• Calculation of the longitudinal aerodynamic characteristics of upper-surface blown wing-flap configurations (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Michael R. Mendenhall, Selden B. Spangler, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Analysis of transonic flow about lifting wing-body configurations (National Aeronautics and Space Administration ;, 1975), by Richard W. Barnwell and Langley Research Center (page images at HathiTrust)
• On the computation of the circulation of a gliding wing of large span (National Aeronautics and Space Administration, 1980), by N. M. Monakhov (page images at HathiTrust)
• On the relation between the generation of a lift force on a wing and the character of the flow in the boundary layer (National Aeronautics and Space Administration, 1960), by I. V. Ostoslavskiĭ and T. A. Grumondz (page images at HathiTrust)
• Calculation of the twist distribution of wings designed for cruise at transonic speeds (National Aeronautics and Space Administration ;, 1974), by Michael J. Mann and Langley Research Center (page images at HathiTrust)
• An analytical evaluation of airfoil sections for helicopter rotor applications (National Aeronautics and Space Administration ;, 1975), by Gene J. Bingham and Langley Research Center (page images at HathiTrust)
• On the logarithmic-singularity correction in the kernel function method of subsonic lifting-surface theory (National Aeronautics and Space Administration ;, 1977), by C. Edward Lan, John E. Lamar, Langley Research Center, and United States National Aeronautics and Space Administration (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)
• Development of aerodynamic prediction methods for irregular planform wings (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by David B. Benepe, General Dynamics Corporation, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)

• Steady and unsteady aerodynamic forces from the SOUSSA surface-panel method for a fighter wing with tip missile and comparison with experiment and PANAIR (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1987), by Herbert J. Cunningham and Langley Research Center (page images at HathiTrust)
• Prediction of effects of wing contour modifications on low-speed maximum lift and transonic performance for the EA-6B aircraft (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Dennis O. Allison, E. G. Waggoner, and Langley Research Center (page images at HathiTrust)
• Prediction of span loading of straight-wing/propeller combinations up to stall (National Aeronautics and Space Administration ;, 1975), by M. A. McVeigh, E. Kisielowski, L. Gray, Lanlgley Research Center, and Inc United Technology (page images at HathiTrust)
• Theory of an airfoil equipped with a jet flap under low-speed flight conditions (National Aeronautics and Space Administration ;, 1975), by F. L. Addessio, J. G. Skifstad, Langley Research Center, and Purdue University. School of Mechanical Engineering (page images at HathiTrust)
• An analytical study of the effects of jets located more than one jet diameter above a wing at subsonic speeds (National Aeronautics and Space Administration ;, 1974), by Lawrence E. Putnam and Langley Research Center (page images at HathiTrust)

• A computer program to calculate the longitudinal aerodynamic characteristics of wing-flap configurations with extremely blown flaps (National Aeronautics and Space Administration ;, 1976), by M. R. Mendenhall, Selden B. Spangler, Frederick K. Goodwin, Langley Research Center, and Nielsen Engineering & Research (page images at HathiTrust)

• Calculation of the longitudinal aerodynamic characteristics of STOL aircraft with externally-blown jet-augmented flaps (National Aeronautics and Space Administration ;, 1974), by Marnix F. E. Dillenius, Selden B. Spangler, M. R. Mendenhall, Ames Research Center, and Nielsen Engineering & Research (page images at HathiTrust)
• Theory of an airfoil equipped with a jet flap under low-speed flight conditions (National Aeronautics and Space Administration ;, 1975), by F. L. Addessio, J. G. Skifstad, Langley Research Center, and Purdue University. School of Mechanical Engineering (page images at HathiTrust)
• A computer program to calculate the longitudinal aerodynamic characteristics of wing-flap configurations with extremely blown flaps (National Aeronautics and Space Administration ;, 1976), by M. R. Mendenhall, Selden B. Spangler, Frederick K. Goodwin, Langley Research Center, and Nielsen Engineering & Research (page images at HathiTrust)
• A two dimensional, iterative solution for the jet flap (National Aeronautics and Space Administration ;, 1973), by Alan Charles Herold, Langley Research Center, and University of Washington (page images at HathiTrust)

• Finite element analysis of aeroacoustic jet-flap flows (Nat'l Aeronautics & Space Admin., Scientific & Technical Information Office ;, 1977), by A. J. Baker, P. D. Manhardt, Computational Mechanics Consultants, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)

• Validation of a computer code for analysis of subsonic aerodynamic performance of wings with flaps in combination with a canard or horizontal tail and an application to optimization (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Harry W. Carlson, Michael J. Mann, Christine M. Darden, and Langley Research Center (page images at HathiTrust)

• Dynamic heave-pitch analysis of air cushion landing systems (National Aeronautics and Space Administration ;, 1975), by K. M. Captain, D. N. Wormley, Ashok B. Boghani, Langley Research Center, and Foster-Miller Associates (page images at HathiTrust)

• Prediction of span loading of straight-wing/propeller combinations up to stall (National Aeronautics and Space Administration ;, 1975), by M. A. McVeigh, E. Kisielowski, L. Gray, Lanlgley Research Center, and Inc United Technology (page images at HathiTrust)
• Analysis of helicopter rotor blade torsional oscillations due to stall (National Aeronautics and Space Administration ;, 1975), by Peter Crimi, U.S. Army Air Mobility Research and Development Laboratory, Langley Research Center, and Avco Corporation. Systems Division (page images at HathiTrust)
• Investigation of nonlinear inviscid and viscous flow effects in the analysis of dynamic stall (National Aeronautics and Space Administration ;, 1974), by Peter Crimi, Langley Research Center, and Avco Corporation. Systems Division (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)
• Analysis of stall flutter of a helicopter rotor blade (National Aeronautics and Space Administration ;, 1973), by Peter Crimi, Langley Research Center, and Avco Corporation. Systems Division (page images at HathiTrust)

• Application of the ONERA model of dynamic stall (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by Kenneth W. McAlister, D. Petot, O. Lambert, and Aeromechanics Laboratory (page images at HathiTrust)
• Analysis of dynamic stall using unsteady boundary-layer theory (National Aeronautics and Space Administration ;, 1974), by R. M. Scruggs, R. E. Singleton, John F. Nash, Langley Research Center, and Inc Scientific & Business Consultants (page images at HathiTrust)

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

• Flight-Determined Aerodynamic Properties of a Jet-Augmented, Auxiliary-Flap, Direct-Lift-Control System Including Correlation With Wind-Tunnel Results (NASA Technical Note D-5128, corrected copy; Washington: National Aeronautics and Space Administration, 1969), by L. Stewart Rolls, Anthony M. Cook, and Robert C. Innis
  • PDF at NASA
  • page images at HathiTrust
• Aerodynamic considerations on the injection of tornado-generated missiles from ground level into tornado flow fields (The Division ;, 1979), by R. T. Hall, Naval Surface Weapons Center, and United States. Office of Nuclear Reactor Regulation. Division of Site Safety and Environmental Analysis (page images at HathiTrust)
• Drag due to lift of a not-so-slender configuration; application of theory. (Cornell Aeronautical Laboratory, Inc., 1958), by Robert J. Vidal (page images at HathiTrust)
• Reduction of drag due to lift at supersonic speeds (Wright Air Development Center, Air Research and Development Command, U. S. Air Force, 1955), by Douglas Aircraft Company and E. W. Graham (page images at HathiTrust)
• The influence of two-dimensional stream shear on airfoil maximum lift (Cornell Aeronautical Laboratory, 1961), by Robert J. Vidal, John H. Hilton, and James T. Curtis (page images at HathiTrust)
• The aerodynamic appraisal of STOL/VTOL configurations (Cornell Aeronautical Laboratory, 1960), by Robert J. Vidal, Richard A. Hartunian, and A. Sowyrda (page images at HathiTrust)
• Large-scale static investigation of circulation-control-wing concepts applied to upper-surface-blowing aircraft (National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987), by M. D. Shovlin and Ames Research Center (page images at HathiTrust)
• Planform effects on the supersonic aerodynamics of multibody configurations (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1987), by S. Naomi McMillin, Richard M. Wood, and Langley Research Center (page images at HathiTrust)
• A Review of technologies applicable to low-speed flight of high-performance aircraft investigated in the Langley 14- by 22-foot subsonic tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1988), by John W. Paulson and Langley Research Center (page images at HathiTrust)
• Low-speed, high-lift aerodynamic characteristics of slender, hypersonic accelerator-type configurations (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1989), by Gregory M. Gatlin and Langley Research Center (page images at HathiTrust)
• Experimental and theoretical aerodynamic characteristics of a high-lift semispan wing model (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Zachary T. Applin, Garl L. Gentry, and Langley Research Center (page images at HathiTrust)
• Effects of upper surface modification on the aerodynamic characteristics of the NACA 632-215 airfoil section (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by R. M. Hicks, Edward T. Shairer, Ames Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Aerodynamic characteristics of a supersonic cruise airplane configuration at Mach numbers of 2.30, 2.96, and 3.30 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by Barrett L. Shrout, Roger H. Fournier, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Informaton Office (page images at HathiTrust)
• Aerodynamic characteristics of a fixed arrow-wing supersonic cruise aircraft at Mach numbers of 2.30, 2.70, and 2.95 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Odell A. Morris, Crolyn B. Watson, Dennis E. Fuller, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (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)
• Low speed aerodynamic characteristics of NACA 6716 and NACA 4416 airfoils with 35 percent-chord single-slotted flaps (National Aeronautics and Space Administration ;, 1974), by Gene J. Bingham, Kevin W. Noonan, and Langley Research Center (page images at HathiTrust)
• Compressible, unsteady lifting-surface theory for a helicopter rotor in forward flight (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Harry L. Runyan, H. Tai, and Langley Research Center (page images at HathiTrust)
• Effect of under-wing aft-mounted nacelles on the longitudinal aerodynamic characteristics of a high-wing transport airplane (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by William Kelly Abeyounis, James C. Patterson, and Langley Research Center (page images at HathiTrust)
• A water tunnel study of gurney flaps (National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988), by Dan H. Neuhart, Odis C. Pendergraft, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division (page images at HathiTrust)
• An approximate analytical method for vortex-lift and center of pressure on the slender wing (U.S. National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Xieyuan Yin, Grace C. Liu, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (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)
• Comparison of concurrent strain gage- and presure transducer-measured flight loads on a lifting reentry vehicle and correlation with wind tunnel predictions (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Ming Han Tang, Robert G. Sheldon, Walter J. Sefic, Hugh L. Dryden Flight Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Effects of spanwise blowing on the surface pressure distributions and vortex-lift characteristics of a trapezoidal wing-strake configuration (National Aeronautics and Space Administration, Scientific and Technical Information Office, 1979), by James F. Campbell and Gary E. Erickson (page images at HathiTrust)
• Aerodynamic characteristics of a hypersonic research airplane concept having a 70 ̊swept double-delta wing at Mach number 0.2 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Jim A. Penland, James L. Dillon, Theodore R. Creel, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Effects of forward contour modification on the aerodynamic characteristics of the NACA 64₁-212 airfoil section (National Aeronautics and Space Administration ;, 1975), by R. M. Hicks, Angelo Bandettini, Joel P. Mendoza, and Ames Research Center (page images at HathiTrust)
• Approximate indicial lift function for tapered, swept wings in incompressible flow (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by M. J. Queijo, Dinesh A. Keskar, William R. Wells, Cinncinnati. University, Wright State University, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Recirculation characteristics of a small-scale VTOL lift engine pod (National Aeronautics and Space Administration, 1971), by Gordon H. Hall, United States National Aeronautics and Space Administration, Lewis Research Center, and Northrop Corporation (page images at HathiTrust)
• Model tests of concepts to reduce hot gas ingestion in VTOL lift engines (National Aeronautics and Space Administration, 1971), by Gordon R. Hall, United States National Aeronautics and Space Administration, Lewis Research Center, and Northrop Corporation (page images at HathiTrust)
• Further experimental investigations of delta and double-delta wing flow fields at low speeds (National Aeronautics and Space Administration, 1967), by William H. Wentz and Michael C. McMahon (page images at HathiTrust; US access only)
• A theoretical investigation of the aerodynamics of slender wing-body combinations exhibiting leading-edge separation (National Aeronautics and Space Administration, 1967), by Alvin H. Sacks, Charles W. Hanson, and Raymond E. Lundberg (page images at HathiTrust; US access only)
• Effects and importance of penetration and growth of lift on space vehicle response (National Aeronautics and Space Administration, 1965), by Robert R. Blackburn and A. D. St. John (page images at HathiTrust; US access only)
• Evaluation of advanced lift concepts and potential fuel conservation for short-haul aircraft (National Aeronautics and Space Administration ;, 1975), by H. S. Sweet, M. K. Bowden, J. H. Renshaw, Ames Research Center, and Lockheed Aircraft Corporation (page images at HathiTrust)
• Light aircraft lift, drag, and moment prediction : a review and analysis (National Aeronautics and Space Administration, 1975), by Frederick O. Smetana, Langley Research Center, and North Carolina State University (page images at HathiTrust)
• Lifting bodies. (NASA, Office of Public Affairs, Educational Programs Division, 1967), by United States. National Aeronautics and Space Administration. Education Division (page images at HathiTrust)
• Highly loaded multi-stage fan drive turbine-leaned stator configuration design (National Aeronautics and Space Administration ;, 1972), by D. C. Evans, G. W. Wolfmeyer, Lewis Research Center, and General Electric Company (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)
• Investigation of blown boundary layers with an improved wall jet system (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by K. R. Saripalli, R. L. Simpson, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Calculation of vortex lift effect for cambered wings by the suction analogy (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by C. Edward Lan, Jen-Fu Chang, University of Kansas. Center for Research, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
• Experimental and theoretical study of three interacting, closely-spaced, sharp-edged 60⁰ delta wings at low speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by H. F. Faery, J. A. Ham, J. K. Strozier, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Langley Research Center, and United States Military Academy. Dept. of Mechanics (page images at HathiTrust)
• Modification of the Douglas Neumann program to improve the efficiency of predicting component interference and high lift characteristics (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by D. R. Bristow, Gordon G. Grose, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (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)
• 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)
• NASA TR R-300 (National Aeronautics and Space Administration ;, 1969), by George W. Jones, Robert W. Walker, Joseph J. Cincotta, George C. Marshall Space Flight Center, Martin Company, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TR R-152 (National Aeronautics and Space Administration ;, 1963), by Clarence D. Cone, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• 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)
• Analytical and experimental investigation of circulation control by means of a turbulent Coanda jet (National Aeronautics and Space Administration ;, 1972), by E. S. Levinsky, T. T. Yeh, Ames Research Center, and Air Vehicle Corporation (page images at HathiTrust)
• NASA TR R-139 (National Aeronautics and Space Administration ;, 1962), by Clarence D. Cone and United States National Aeronautics and Space Administration (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)
• Definition of lateral-range and lift-drag-ratio requirements for return to both optimum and nonoptiumum recovery sites (National Aeronautics and Space Administration, 1966), by Paul F. Holloway and E. Brian Pritchard (page images at HathiTrust; US access only)
• Wind-tunnel lift interference on sweptback wings in rectangular test sections with slotted top and bottom walls (National Aeronautics and Space Administration, 1966), by Ray H. Wright and Raymond L. Barger (page images at HathiTrust; US access only)
• A Supersonic area rule and an application to the design of a wing-body combination with high lift-drag ratios (U.S. G.P.O., 1960), by Richard T. Whitcomb, John R. Sevier, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• NASA TR R-344 (National Aeronautics and Space Administration ;, 1970), by Ray H. Wright, James D. Keller, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Effect of wing planform and canard location and geometry on the longitudinal aerodynamic characteristics of a close-coupled canard wing model at subsonic speeds (National Aeronautics and Space Administration ;, 1975), by Blair B. Gloss and Langley Research Center (page images at HathiTrust)
• Subsonic aerodynamic characteristics of interacting lifting surfaces with separated flow around sharp edges predicted by a vortex-lattice method (National Aeronautics and Space Administration ;, 1975), by John E. Lamar, Blair B. Gloss, 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)
• Wind-tunnel investigation of aerodynamic loads on a large-scale externally blown flap model and comparison with theory (National Aeronautics and Space Administration ;, 1975), by Boyd Perry, George C. Greene, and Langley Research Center (page images at HathiTrust)
• NASA TN D-2334 (National Aeronautics and Space Administration :, 1964), by Roy V. Harris, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-2486 (National Aeronautics and Space Administration ; [For sale by the Office of Technical Services, Department of Commerce, Washington, D.C. 20230], 1964), by Dewey E. Wornom, Joseph Gera, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Effects of spanwise blowing on the pressure field and vortex-lift characteristics of a 44 ̊swept trapezoidal wing (National Aeronautics and Space Administration ;, 1975), by James F. Campbell and Langley Research Center (page images at HathiTrust)
• NASA TN D-5299 (National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Harold G. Gaidsick, Robert C. McCracken, William H. Dana, Flight Research Center (U.S.), and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5129 (National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Kiyoshi Aoyagi, Paul T. Soderman, Stanley O. Dickinson, Army Aeronautical Research Laboratory, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5218 (National Aeronautics and Space Administration ;, 1969), by Andrzej Dobrowolski, John L. Allen, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-4361 (National Aeronautics and Space Administration ;, 1968), by David R. Stone, George C. Ashby, Langley Research Center, 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)
• NASA TN D-6198 (National Aeronautics and Space Administration ;, 1971), by William A. Newsom, Sue B. Grafton, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Low-speed wind-tunnel investigation of a four-engine upper surface blown model having a swept wing and rectangular and D-shaped exhaust nozzles (National Aeronautics and Space Administration ;, 1975), by William C. Sleeman, William C. Hohlweg, and Langley Research Center (page images at HathiTrust)
• The effects on propulsion-induced aerodynamic forces of vectoring a partial-span rectangular jet at Mach numbers from 0.40 to 1.20 (National Aeronautics and Space Administration ;, 1975), by Francis J. Capone and Langley Research Center (page images at HathiTrust)
• Wind-tunnel investigation of a jet transport airplane configuration with high thrust-weight ratio and an external-flow jet flap (National Aeronautics and Space Administration; [for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], 1970), by Lysle P. Parlett, Charles Christian Smith, and Delma C. Freeman (page images at HathiTrust; US access only)
• NASA TN D-5862 (National Aeronautics and Space Administration :, 1970), by William D. Grantham, Robert W. Sommer, Perry L. Deal, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Application of a supersonic kernel-function procedure to flutter analysis of thin lifting surfaces (National Aeronautics and Space Administration :, 1970), by Herbert J. Cunningham, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5942 (National Aeronautics and Space Administration ;, 1970), by William A. Newsom, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5031 (National Aeronautics and Space Administration ;, 1968), by Thomas G. Gainer, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-5893 (National Aeronautics and Space Administration ;, 1970), by Rodger L. Naeseth, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5071 (National Aeronautics and Space Administration ;, 1969), by Robert H. Moore, Theodore F. Hughes, David L. Eichblatt, Manned Spacecraft Center (U.S.), and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Full-scale wind-tunnel investigation of the aerodynamic characteristics of the X-24A lifting body aircraft (National Aeronautics and Space Administration, 1970), by Kenneth W. Mort, Michael D. Falarski, U.S. Army Aeronautical Research Laboratory, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Low-speed wind-tunnel investigation of a swept-wing model having distributed upper-surface blowing near the wing leading edge or at the flap knee (National Aeronautics and Space Administration ;, 1977), by William C. Sleeman, Langley Research Center, United States National Aeronautics and Space Administration, and David R Forsyth (page images at HathiTrust)
• NASA TN D-5899 (National Aeronautics and Space Administration :, 1970), by Charles B. Johnson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-5900 (National Aeronautics and Space Administration :, 1970), by Blair B. Gloss, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• An investigation of a close-coupled canard as a direct side-force generator on a fighter model at Mach numbers from 0.40 to 0.90 (National Aeronautics and Space Administration ;, 1977), by Richard J. Re, Francis J. Capone, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effects of leading-edge sweep angle and design lift coefficient on performance of a modified arrow wing at a design Mach number of 2.6 (National Aeronautics and Space Administration ;, 1974), by Robert J. Mack 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)
• Wind-tunnel investigation of the low-speed high-lift aerodynamics of a one-fifth scale variable-sweep supersonic transport (National Aeronautics and Space Administration, 1968), by Anthony M. Cook, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5499 (National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by James F. Campbell, Dorothy T. Howell, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5335 (National Aeronautics and Space Administration ;, 1969), by James A. Blackwell, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-4891 (National Aeronautics and Space Administration :, 1969), by Charles H. Fox, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-4739 (National Aeronautics and Space Administration ;, 1968), by Edward C. Polhamus, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5662 (National Aeronautics and Space Administration ; [For sale for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by Arthur W. Carter, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Wind-tunnel investigation of an STOL aircraft configuration equipped with an external-flow jet flap (National Aeronautics and Space Administration :, 1969), by Lysle P. Parlett, James P. Shivers, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• NASA TN D-5682 (National Aeronautics and Space Administration ;, 1970), by Henry A. Putre, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Wind-tunnel study of slot spoilers for direct lift control (National Aeronautics and Space Administration, 1972), by Dominick Andrisani, Joseph W. Stickle, Garl L. Gentry, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• NASA TN D-6710 (National Aeronautics and Space Administration :, 1972), by Frederick W. Gibson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effects of body shape on the aerodynamic characteristics of an all-body hypersonic aircraft configuration at Mach numbers from 0.65 to 10.6 (National Aeronautics and Space Administration ;, 1972), by Walter P. Nelms and Ames Research Center (page images at HathiTrust)
• Results of full-scale wind tunnel tests on the H.126 jet flap aircraft (National Aeronautics and Space Administration, 1969), by Anthony M. Cook, Dale G. Jones, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• Experimental stability and control results at Mach 19 of an entry vehicle designed for an intermediate lift-drag ratio (National Aeronautics and Space Administration ;, 1968), by Patrick J. Johnston, Robert D. Witcofski, and Langley Research Center (page images at HathiTrust)
• NASA TN D-5468 (National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Kenneth W. Mort, Michael D. Falarski, Army Aeronautical Research Laboratory, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Results of full-scale wind tunnel tests on the H.126 jet flap aircraft (National Aeronautics and Space Administration ;, 1973), by Thomas N. Aiken, Anthony Cook, and Ames Research Center (page images at HathiTrust)
• Low-speed aerodynamic characteristics of an airfoil optimized for maximum lift coefficient (National Aeronautics and Space Administration ;, 1972), by Gene J. Bingham, Allen Wen-shin Chen, and Langley Research Center (page images at HathiTrust)
• Theoretical and experimental longitudinal aerodynamic characteristics of an aspect ratio 0.25 sharp-edge delta wing at subsonic, supersonic, and hypersonic speeds (National Aeronautics and Space Administration ;, 1974), by Charles H. Fox, John E. Lamar, and Langley Research Center (page images at HathiTrust)
• Wind-tunnel investigation of an upper surface blown jet-flap powered-lift configuration (National Aeronautics and Space Administration ;, 1973), by Arthur E. Phelps, Charles Christian Smith, and Langley Research Center (page images at HathiTrust)
• NASA TN D-1823 (National Aeronautics and Space Administration, 1963), by Odell A. Morris, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-6263 (National Aeronautics and Space Administration ;, 1971), by Jon S. Pyle, Flight Research Center (U.S.), and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• 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)
• A wind-tunnel investigation of the development of lift on wings in accelerated longitudinal motion (National Aeronautics and Space Administration :, 1960), by Thomas R. Turner and United States National Aeronautics and Space Administration (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)
• Induced interference effects on a four-jet VTOL configuration with various wing planforms in the transition speed range (National Aeronautics and Space Administration :, 1962), by James H. Otis and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-4122 (National Aeronautics and Space Administration ;, 1967), by Jim A. Penland, Peter T. Bernot, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Aerodynamic effects of some configuration variables on the aeroelastic characteristics of lifting surfaces at Mach numbers from 0.7 to 6.86 (National Aeronautics and Space Administration, 1961), by Perry W. Hanson, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Effects of camber and twist on the aerodynamic characteristics of parawings having nominal aspect ratios of 3 and 65 (NASA, 1963), by Edward C. Polhamus, Rodger L. Naeseth, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Wind-tunnel investigation of steady-state aerodynamics of a composite-lift VTOL aircraft model (National Aeronautics and Space Administration ;, 1969), by Matthew M. Winston, Robert J. Huston, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Effect of engine position and high-lift devices on aerodynamic characteristics of an external-flow jet-flap STOL model (National Aeronautics and Space Administration ;, 1971), by Charles C. Smith, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• On the use of thick-airfoil theory to design airfoil families in which thickness and lift are varied independently (National Aeronautics and Space Administration ;, 1974), by Raymond L. Barger and Langley Research Center (page images at HathiTrust)
• Aerodynamic characteristics of three slender sharp-edge 74 ̊swept wings at subsonic, transonic, and supersonic Mach numbers (National Aeronautics and Space Administration ;, 1974), by Edwin E. Davenport and Langley Research Center (page images at HathiTrust)
• NASA TN D-1779 (National Aeronautics and Space Administration :, 1963), by James H. Otis, Kenneth W. Goodson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-1775 (National Aeronautics and Space Administration, 1963), by Joseph J. Janos, John R. Unangst, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Effect of canard location and size on canard-wing interference and aerodynamic-center shift related to maneuvering aircraft at transonic speeds (National Aeronautics and Space Administration ;, 1974), by Blair B. Gloss and Langley Research Center (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)
• Wind-tunnel investigation of an external-flow jet-flap transport configuration having full-span triple-slotted flaps (National Aeronautics and Space Administration :, 1971), by Lysle P. Parlett, Langley Directorate, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-6384 (National Aeronautics and Space Administration ;, 1971), by William F. Hady, Lawrence P. Ludwig, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-6482 (National Aeronautics and Space Administration ;, 1971), by Kiyoshi Aoyagi, Leo P. Hall, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Manual-control simulation study of a nonlifting vehicle during orbit, retro-rocket firing, and reentry into the earth's atmosphere (National Aeronautics and Space Administration, 1960), by Roger M. Davidson, Jack T. Kaylor, Donald C. Cheatham, and Langley Research Center (page images at HathiTrust)
• Lowspeed wind-tunnel investigation of a semispan STOL jet transport wing-body with an upper-surface blown jet flap (National Aeronautics and Space Administration ;, 1973), by Arthur R. Phelps, Robert L. Henderson, William Letko, and Langley Research Center (page images at HathiTrust)
• Longitudinal aerodynamic characteristics of an externally blown flap powered-lift model with several propulsive system simulators (National Aeronautics and Space Administration ;, 1974), by Danny R. Hoad and Langley Research Center (page images at HathiTrust)
• Effects of wing leading-edge radius and Reynolds number on longitudinal aerodynamic characteristics of highly swept wing-body configurations at subsonic speeds (National Aeronautics and Space Administration ;, 1976), by William P. Henderson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Low-speed wind-tunnel investigation of a large-scale advanced arrow-wing supersonic transport configuration with engines mounted above wings for upper-surface blowing (National Aeronautics and Space Administration :, 1976), by James P. Shivers, Paul L. Coe, H. Clyde McLemore, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Wind-tunnel investigation of a twin-engine straight-wing upper-surface blown jet-flap configuration (National Aeronautics and Space Administration ;, 1975), by Arthur E. Phelps and Langley Research Center (page images at HathiTrust)
• NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1945), by John L. Crigler, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1945), by Clotaire Wood, John A. Zalovcik, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Analysis of factors affecting net lift increment attainable with trailing-edge split flaps on tailless airplanes (NACA, 1944), by Marvin Pitkin, Bernard Maggin, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Flight test results pertaining to the Space Shuttlecraft : a symposium held at Flight Research Center, Edwards, Calif., June 30, 1970. (National Aeronautics and Space Administration ;, 1970), by Flight Research Center (U.S.) (page images at HathiTrust)
• Normal component of induced velocity in the vicinity of a lifting rotor with a nonuniform disk loading (National Advisory Committee for Aeronautics, 1956), by Harry H. Heyson, S. Katzoff, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation of the effects of leading-edge chord-extensions and fences in combination with leading-edge flaps on the aerodynamic characteristics at Mach numbers of 0.40 to 0.93 of a 45©� sweptback wing of aspect ratio 4 (National Advisory Committee for Aeronautics, 1957), by Kenneth P. Spreemann, William J. Alford, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• The wave drag of arbitrary configurations in linearized flow as determined by areas and forces in oblique planes (National Advisory Committee for Aeronautics, 1955), by Harvard Lomax, United States National Advisory Committee for Aeronautics, and Ames Research Center (page images at HathiTrust)
• An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability below the Mach Number of Lift Divergence (National Advisory Committee for Aeronautics, 1948), by John A. Axelson, J. Conrad Crown, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Summary of results of a wind-tunnel investigation of 9 related horiztonal tails. (National Advisory Committee for Aeronautics, 1955), by Jules B. Jr Dods, Bruce E. Tinling, United States National Advisory Committee for Aeronautics, and Ames Research Center (page images at HathiTrust)
• Estimation of lift and drag of airfoils at near sonic speeds and in the presence of detached shock waves (National Advisory Committee for Aeronautics, 1949), by John P. Mayer, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Aerodynamic characteristics of a delta wing with leading edge swept back 45 degrees, aspect ratio 4, and NACA 65A006 airfoil section. Transonic-bump method (National Advisory Committee for Aeronautics, 1949), by William C. Sleeman, Robert E. Becht, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation of the NACA-4-(3)(08)-03 two-blade propeller at forward Mach numbers to 0.925 (National Advisory Committee for Aeronautics, 1949), by James B. Delano, Francis G. Morgan, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation of the NACA 4-(4)(06)-04 two-blade propeller at forward Mach numbers to 0.925 (National Advisory Committee for Aeronautics, 1949), by James B. Delano, Daniel E. Harrison, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory 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, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Transonic flight tests to compare the zero-lift drag on underslung and symmetrical nacelles varied chordwise at 40 percent semispan of a 45©� sweptback, tapered wing (National Advisory Committee for Aeronautics, 1950), by William B. Pepper, Sherwood Hoffman, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Large-scale flight measurements of zero-lift drag and low-lift drag of 10 wing-body configurations at Mach numbers from 0.8 to 1.6 (National Advisory Committee for Aeronautics, 1953), by John D. Morrow, Robert L. Nelson, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Transonic flight tests to determine the effect of thickness ratio and plan-form modification on the zero-lift drag of a 45©� sweptback wing (National Advisory Committee for Aeronautics, 1952), by William B. Pepper, Sherwood Hoffman, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Flight investigation of the zero-lift drag of two ram-jet missile configurations at Mach numbers from 1.0 to 1.89 (National Advisory Committee for Aeronautics, 1953), by Clarence A. Brown, Walter E. Bressette, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• A note on the drag due to lift of delta wings at Mach numbers up to 2.0 (National Advisory Committee for Aeronautics, 1953), by Robert S. Osborne, Thomas C. Kelly, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Comparison of lift-curve slopes for a model tested in two slotted tunnels of different sizes at high subsonic speeds (National Advisory Committee for Aeronautics, 1953), by Robert W. Boswinkle, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Effect of some section modifications and protuberances on the zero-lift drag of delta wings at transonic and supersonic speeds (National Advisory Committee for Aeronautics, 1954), by Carl A. Sandahl, William E. Stoney, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Factors affecting the maximum lift-drag ratio at high supersonic speeds (National Advisory Committee for Aeronautics, 1956), by Charles H. McLellan, Robert W. Dunning, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• A wind-tunnel investigation of the development of lift on wings in accelerated longitudinal motion (National Advisory Committee for Aeronautics, 1956), by Thomas R. Turner, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Aerodynamic characteristics of a leading-edge slat on a 35 degree swept-back wing for Mach numbers from 0.30 to 0.88 (National Advisory Committee for Aeronautics, 1951), by John A. Kelly, Nora-Lee F. Hayter, Ames Research Center, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane 45©� swept-back wing of aspect ratio 3, taper ratio 0.4 with 3-percent-thick, biconvex section (National Advisory Committee for Aeronautics, 1951), by John C. Heitmeyer, Ames Research Center, and United States. National Adviosry Committee for Aeronautics (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)
• Lift, drag, and static longitudinal stability data from an exploratory investigation at a Mach number of 6.86 of an airplane configuration having a wing of trapezoidal plan form (National Advisory Committee for Aeronautics, 1955), by Jim A. Penland, David E. Fetterman, Herbert W. Ridyard, 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 45 degrees, aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil section. Transonic-bump method (National Advisory Committee for Aeronautics, 1949), by Boyd C. Myers, Thomas J. King, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Aerodynamic investigation at Mach number 1.92 of a rectangular wing and tail and body configuration and Its components (National Advisory Committee for Aeronautics, 1950), by Macon C. Ellis, Carl E. Grigsby, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation in the Langley 19-foot pressure tunnel of two wings of NACA 65-210 and 64-210 airfoil sections with various type flaps (National Advisory Committee for Aeronautics, 1948), by James C. Sivells, Stanley H. Spooner, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Theoretical lift and damping in roll of thin sweptback wings of arbitrary taper and sweep at supersonic speeds : Subsonic leading edges and trailing edges (National Advisory Committee for Aeronautics, 1949), by Frank S. Malvestuto, H. S. Ribner, Kenneth Margolis, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Effects of compressibility on lift and load characteristics of a tapered wing of NACA 64-210 airfoil sections up to a Mach number of 0.60 (National Advisory Committee for Aeronautics, 1949), by F. E. West, T. Himka, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• The effects of sideslip, aspect ratio, and Mach number on the lift and pitching moment of triangular, trapezoidal, and related plan forms in supersonic flow (National Advisory Committee for Aeronautics, 1949), by Arthur L. Jones, Elizabeth E. Lindler, Robert M. Sorenson, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Estimation of the damping in roll of rings through the normal flight range of lift coefficient (National Advisory Committee for Aeronautics, 1949), by Alex Goodman, Glenn H. Adair, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Line-vortex theory for calculation of supersonic downwash (National Advisory Committee for Aeronautics, 1949), by Harold Mirels, Rudolph C. Haefeli, and United States National Advisory Committee for Aeronautics (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)
• Experimental and theoretical distribution of flow produced by inlet guide vanes of an axial-flow compressor (National Advisory Committee for Aeronautics, 1949), by Harold B. Finger, Howard A. Buckner, Harold J. Schum, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Linearized lifting-surface theory for swept-back wings with slender plan forms (National Advisory Committee for Aeronautics, 1949), by Harvard Lomax, Max A. Heaslet, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Effects of Mach number up to 0.34 and Reynolds number up to 8,000,000 on the maximum lift coefficient of a wing of NACA 66-series airfoil sections (National Advisory Committee for Aeronautics, 1950), by G. Chester Furlong, James E. Fitzpatrick, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Three-dimensional, unsteady-lift problems in high-speed flight : basic concepts (National Advisory Committee for Aeronautics, 1950), by Harvard Lomax, Franklyn B. Fuller, Max A. Heaslet, 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)
• 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)
• Supersonic lift and pitching moment of thin sweptback tapered wings produced by constant vertical acceleration. Subsonic leading edges and supersonic trailing edges (National Advisory Committee for Aeronautics, 1951), by Frank S. Malvestuto, Dorothy M. Hoover, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Three-dimensional unsteady lift problems in high-speed flight : the triangular wing (National Advisory Committee for Aeronautics, 1951), by Harvard Lomax, Franklyn B. Fuller, Max A. Heaslet, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• The normal component of the induced velocity in the vicinity of a lifting rotor and some examples of its application (National Advisory Committee for Aeronautics, 1953), by Walter Castles, Jacob Henri De Leeuw, 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)
• Calibration of strain-gage installations in aircraft structures for the measurement of flight loads (National Advisory Committee for Aeronautics, 1953), by T. H. Skopinski, Wilber B. Huston, William S. Aiken, 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)
• Approach and landing investigation at lift-drag ratios of 2 to 4 utilizing a straight-wing fighter airplane (National Aeronautics and Space Administration, 1959), by Gene J. Matranga, Neil Armstrong, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• An investigation at transonic speeds of the effects of thickness ratio and of thickened root sections on the aerodynamic characteristics of wings with 47©� sweepback, aspect ratio 3.5, and taper ratio 0.2 in the slotted test section of the Langley 8-foot high-speed tunnel (National Advisory Committee for Aeronautics, 1951), by Ralph P. Bielat, Domenic A. Coppolino, Daniel E. Harrison, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Effects of wing inboard plan-form modifications on lift, drag, and longitudinal stability at Mach numbers from 1.0 to 2.3 of a rocket-propelled free-flight model with a 52.5 degree sweptback wing of aspect ratio 3 (National Advisory Committee for Aeronautics, 1957), by Allen B. Henning and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation of the lift, center of pressure, and drag of a projectile at Mach number of 8.6 and a Reynolds number of 17 million (National Advisory Committee for Aeronautics, 1954), by Thomas N. Canning, Ames Research Center, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Aerodynamic characteristics in pitch of several triple-body missile configurations at Mach numbers 0.6 to 1.4 (National Advisory Committee for Aeronautics, 1956), by Earl D. Knechtel, Arvid N. Andrea, Ames Research Center, and United States National Advisory 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)
• 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)
• Die Thatsache der lenkbaren Luftschiffahrt und ihre Verwendung für Militärzwecke von A-Z. (F.W. v. Biedermann, 1890) (page images at HathiTrust)
• Tests in the Variable Density Wind Tunnel to investigate the effects of scale and turbulence on airfoil characteristics (National Advisory Committee for Aeronautics ;, 1931), by John Stack and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• The Aerodynamic characteristics of three tapered airfoils tested in the Variable Density Wind Tunnel (National Advisory Committee for Aeronautics ;, 1931), by Raymond F. Anderson and United States National Advisory 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)
• Effect of compressibility at high subsonic velocities on the lifting force acting on an elliptic cylinder (National Advisory Committee for Aeronautics ;, 1946), by Carl Kaplan and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• A Simple method of estimating the subsonic lift and damping in roll of sweptback wings (National Advisory Committee for Aeronautics, 1949), by Edward C. Polhamus and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• NACA Wartime Reports. Series L. (National Advisory Committee for Aeronautics, 1944), by F. J. Bailey, F. B. Gustafson, 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, 1942), by William J. Underwood, Frank T. Abbott, 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, 1941), by Ira H. Abbott, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (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)
• 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; US access only)
• A Method for determining the point of lift-off and modified trajectory of a ground-based heated turbulent planar jet in a co-flowing wind (Hanscom AFB, Massachusetts : Air Force Geophysics Laboratories, Air Force Systems Command, United States Air Force, 1977., 1977), by Milton M. Klein and U.S. Air Force Geophysics Laboratory (page images at HathiTrust)
• Preliminary investigation of the characteristics of a two-dimensional wing and propeller with the propeller plane of rotation in the wing-chord plane (National Advisory Committee for Aeronautics, 1957), by David H. Hickey, United States National Advisory Committee for Aeronautics, and Ames Research Center (page images at HathiTrust)
• Large-scale wind-tunnel tests of a jet-transport-type model with leading- and trailing-edge high-lift devices (National Advisory Committee for Aeronautics, 1958), by David H. Hickey, Kiyoshi Aoyagi, and Ames Research Center (page images at HathiTrust)
• Working charts for the determination of the lift distribution between biplane wings (Government Printing Office, 1932), by Paul Kuhn and United States National Advisory Committee for Aeronautics (page images at HathiTrust; US access only)
• The unsteady lift of a wing of finite aspect ratio (U.S. Government Printing Office, 1940), by Robert T. Jones (page images at HathiTrust; US access only)
• 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)
• An approximate analysis of wing unsteady aerodynamics (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories. Air Force Systems Command, United States Air Force, 1979., 1979), by William R. Wells, Air Force Flight Dynamics Laboratory (U.S.), Wright State University, and United States. Air Force. Systems Command (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)
• Basic principles of the indicial lifting-surface flutter-analysis procedure (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1962., 1962), by Bernard Mazelsky, Harry B. Amey, United States. Air Force. Systems Command. Aeronautical Systems Division, and Aerojet-General Corporation (page images at HathiTrust)
• Development of an empirically based computer program to predict the aerodynamic characteristics of aircraft. Volume I, Basic Theoretical methods (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1973., 1973), by M. L. Goldhammer, C. C. Shen, M. L. Lopez, Air Force Flight Dynamics Laboratory (U.S.), and Douglas Aircraft Company (page images at HathiTrust)
• A study of hypersonic aerodynamic drag devices : final technical report (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1960., 1960), by W. B. Champney, Wright Air Development Center, and United States. Air Force. Air Research and Development Command (page images at HathiTrust)
• Optimization of lifting re-entry vehicles (Wright-Patterson Air Force Base, Ohio : X-20 (Dyna-Soar) Engineering Office, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1963., 1963), by Wilbur Leason Hankey, United States. Air Force. Systems Command. Aeronautical Systems Division, and Wright-Patterson Air Force Base (Ohio) (page images at HathiTrust)
• Research on rotating stall in axial flow compressors. Part I. On lift hysteresis at maximum lift including effect of camber (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1959., 1959), by R. A. Hartunian, Wright Air Development Center, and United States. Air Force. Air Research and Development Command (page images at HathiTrust)
• Calculation of interference for a porous wall wind tunnel by the method of block cyclic reduction (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1975., 1975), by C. F. Lo, H. N. Glassman, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Equations and charts for the evaluation of the hypersonic aerodynamic characteristics of lifting configurations by the Newtonian theory (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1964., 1964), by E. L. Clark, L. L. Trimmer, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Lift and pitching moment Induced on jet STOVL aircraft hovering in ground effect : data report (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Directorate , Wright Laboratory, Air Force Materiel Command, United States Air Force, 1993., 1993), by Richard E. Kuhn, Vearl R. Stewart, and Ohio) Wright Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
• Development of a device for controlling the leading edge vortices ona delta wing : Phase I SBIR, Final technical report (Bolling Air Force Base, D. C. : Air Force Office of Scientific Research, Aerospace Sciences Directorate, United States Air Force, 1986., 1986), by Mohamed Gad-el-Hak, Flow Research Company, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Hypersonic lifting body windward surface flow-field analysis for high angles of incidence (Arnold Air Force Base, Tennessee : Von Kármán Gas Dynamics Facility, Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1973., 1973), by John C. Adams, William R. Martindale, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Lift and pitching moment Induced on jet STOVL by the ground vortex : data report (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Directorate , Wright Laboratory, Air Force Materiel Command, United States Air Force, 1993., 1993), by Vearl R. Stewart, Richard E. Kuhn, and Ohio) Wright Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
• Unique stealth unmanned aerial vehicle (UAV) Houck aircraft design program. Volume 1, Program overview (Wright-Patterson Air Force Base, Ohio : Air Force Research Laboratory, Air Force Materiel Command, 2008., 2008), by Aaron Altman, University of Dayton, Ohio). Air Vehicles Directorate Air Force Research Laboratory (Wright-Patterson Air Force Base, and United States. Air Force Materiel Command (page images at HathiTrust)
• Subsonic characteristics of low aspect ratios. Volume II. Wind-tunnel test results (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1964., 1964), by J. K. Beamish, Eugene L. Crosthwait, G. J. Klein, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and General Dynamics Corporation. Fort Worth Division (page images at HathiTrust)
• Longitudinal force charactristics of two AFFDL MDF-4 high lift-to-drag configurations at Mach number 19 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1964., 1964), by A. R. Wallace, L. G. Siler, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Choking Mach number in high speed wind tunnel with consideration of the model lift (Wright-Patterson Air Force Base, Ohio : United States, Air Force, Air Materiel Command, 1948., 1948), by Bernhard A. Goethert and United States. Air Force. Air Matériel Command (page images at HathiTrust)
• Viscous effects on zero-lift drag of slender blunt cones (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1963., 1963), by Jack D. Whitfield, B. J. Griffith, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• An Experimental investigation of high lift/high rate aerodynamics of an unsteady airfoil (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 1989., 1989), by G. M. Graham, Ohio University, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Heat-transfer and shadowgraph tests of several elliptical lifting bodies at Mach 10 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1964., 1964), by M. E. Hillsamer, J. P. Rhudy, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Aerodynamics of supersonic lifting bodies (Air Force Armament Laboratory, Armamaent Division, Air Force Systems Command, United States Air Force, 1981), by M. C. Jischke, M. L. Rasmussen, United States. Air Force. Systems Command, Air Force Armament Laboratory, and Mechanical University of Oklahoma. School of Aerospace (page images at HathiTrust)

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