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NASA SC(2)-0714 Airfoil Data Corrected for Sidewall Boundary-Layer Effects in the Langley 0.3-Meter Transonic Cryogenic Tunnel (NASA technical paper 2890, 1989), by Renaldo V. Jenkins (page images at HathiTrust)
Sur l'aérodynamique des ailes sustentatrices et des hélices (Gauthier-Villars et cie, 1928), by Maurice Roy (page images at HathiTrust; US access only)
Applied wing theory (McGraw-Hill book company, inc., 1932), by Elliott Gray Reid (page images at HathiTrust; US access only)
Basic wing and airfoil theory. (McGraw-Hill, 1951), by Alan Pope (page images at HathiTrust)
La mécanique des profils d'aviation; communication preséntée à la Société polytechnique de Varsovie. (É. Chiron, 1924), by Czeslaw Witoszyński and S. Ziembinski (page images at HathiTrust; US access only)
Étude sur les surfaces portantes en aéroplanie (H. Dunod et É. Pinat, 1909), by Louis Tariel and Édouard Tariel (page images at HathiTrust; US access only)
Airfoil theory at supersonic speed (National Advisory Committee for Aeronautics, 1939), by H. Schlichting and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Airplane design; performance. (McGraw-Hill, 1936), by Edward Pearson Warner (page images at HathiTrust; US access only)
The elements of aerofoil and airscrew theory (The University Press, 1926), by H. Glauert (page images at HathiTrust)
Investigation of feasibility of utilizing available heat resistant materials for hypersonic leading edge applications. (Wright Air Development Center, Air Research and Development Command, U. S. Air Force, 1900), by Bell Aircraft Corporation (page images at HathiTrust)
Theory of cambered Joukowsky airfoils in shear flow. (Cornell Aeronautical Laboratory, 1958), by Alexander Sowyrda (page images at HathiTrust)
Wind tunnel tests of thin airfoils oscillating near stall. (U.S. Army Aviation Materiel Laboratories, 1969), by Franklyn J. Davenport, Jaan Liiva, Lewis Gray, and U.S. Army Aviation Materiel Laboratories (page images at HathiTrust)
Two-dimensional tests of airfoils oscillating near stall. (U.S. Army Aviation Materiel Laboratories, 1968), by Lewis Gray, Jaan Liiva, and U.S. Army Aviation Materiel Laboratories (page images at HathiTrust)
Theoretical and experimental studies of airfoil characteristics in nonuniform sheared flow. (U. S. Army Aviation Materiel Laboratories], 1965), by William Gordon Brady (page images at HathiTrust)
Computed moisture interception on helicopter rotor blades (Cornell Aeronautical Laboratory, Inc., 1958), by Charles E. Treanor and Marcia J. Williams (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 two-dimensional effects of slipstream shear on airfoil characteristics (U. S. Army Transportation Research and Development Command, Transportation Corps, 1960), by Robert J. Vidal, James T. Curtis, and John H. Hilton (page images at HathiTrust)
Tables of two-dimensional oscillating airfoil coefficients for rotary wings. (Cornell Aeronautical Laboratory, Inc., 1955), by Robert G. Loewy (page images at HathiTrust)
The effects of axisymmetric shear on airfoil characteristics (U. S. Army Transportation Research Command, Transportation Corps., 1961), by Robert J. Vidal and James T. Curtis (page images at HathiTrust)
The effect of entrainment upon a jet-flapped airfoil. (Cornell University, Graduate School of Aeronautical Engineering, 1957), by Howard S. London (page images at HathiTrust)
US Army helicopter design datcom (Army Aviation Systems Command, 1976), by L. U. Dadone, U.S. Army Air Mobility Research and Development Laboratory. Systems Research Integration Office, and Boeing Vertol Company (page images at HathiTrust; US access only)
The calculation of the pressure distribution on a cascade of thick airfoils by means of Fredholm integral equations of the second kind (National Aeronautics and Space Administration; for sale by: National Technical Information Service, Springfield, Va., 1971), by Erich Martensen (page images at HathiTrust)
Effect of advanced rotorcraft airfoil sections on the hover performance of a small-scale rotor model (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1988), by Susan L. Althoff and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division (page images at HathiTrust)
NASA supercritical airfoils : a matrix of family-related airfoils (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Charles D. Harris and Langley Research Center (page images at HathiTrust)
Airfoil interaction with an impinging vortex (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by Kenneth W. McAlister, C. Tung, United States. Army Aviation Systems Command, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Water-tunnel experiments on an oscillating airfoil at RE = 21,000 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Kenneth W. McAlister, Lawrence W. Carr, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Airfoil design by numerical optimization using a minicomputer (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by R. M. Hicks, C. A. Szelazek, Computer Information Systems (Firm), Ames Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (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)
Low-speed aerodynamic characteristics of airfoil sections with rounded trailing edges in forward and reverse flow (National Aeronautics and Space Administration ;, 1974), by William D. Beasley, Robert J. McGhee, and Langley Research Center (page images at HathiTrust)
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)
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)
The application to airfoils of a technique for reducing orifice-induced pressure error at high Reynolds numbers (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1986), by Elizabeth B. Plentovich and Langley Research Center (page images at HathiTrust)
Static and dynamic pressure measurements on a NACA 0012 airfoil in the Ames High Reynolds Number Facility (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by John B. McDevitt, Arthur F. Okuno, and Ames Research Center (page images at HathiTrust)
Effects of independent variation of Mach and Reynolds numbers on the low-speed aerodynamic characteristics of the NACA 0012 airfoil section (National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988), by Charles L. Ladson and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division (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)
Dynamic stall experiments on the NACA 0012 airfoil (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Kenneth W. McAlister, William J. McCroskey, Lawrence W. Carr, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Low-speed aerodynamic characteristics of a 16-percent thick variable-geometry airfoil designed for general aviation applications (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Richard W. Barnwell, Robert J. McGhee, Kevin W. Noonan, Army Research and Technology Laboratories (U.S.). Structures Laboratory, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Flight evaluation of the transonic stability and control charcteristics of an airplane incorporating a supercritical wing (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Neil W. Matheny, Donald H. Gatlin, 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)
An experimental evaluation of the application of the Kirchhoff formulation for sound radiation fron an oscillating airfoil (National Aeronoautics and Space Administration, Scientific and Technical Information Office ;, 1977), by Thomas F. Brooks and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Application of shock tubes to transonic airfoil testing at high Reynolds numbers (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, William John Cook, and Iowa State University (page images at HathiTrust)
Effects of airfoil shape, thickness, camber, and angle of attack on calculated transonic unsteady airloads (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by John T. Batina and Langley Research Center (page images at HathiTrust)
An investigation of several NACA 1-series inlets at Mach numbers from 0.4 to 1.29 for mass-flow ratios near 1.0 (U.S. National Aeronautics and Space Administration ;, 1976), by Richard J. Re and Langley Research Center (page images at HathiTrust)
Wind-tunnel results for a modified 17-percent-thick low-speed airfoil section (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Robert J. McGhee, William D. Beasley, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
Approximation concepts for numerical airfoil optimization (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by Garret N. Vanderplaats, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Ames Research Center (page images at HathiTrust)
Mean-flow and turbulence measurements in the vicinity of the trailing edge of an NACA 63₁-012 airfoil (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by James C. Yu, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
Design and experimental results of a highly loaded, low solidity tandem rotor (National Aeronautics and Space Administration ;, 1971), by James L. Bettner, Langley Research Center, and General Motors Corporation (page images at HathiTrust)
Airfoil at supersonic mach number (National Aeronautics and Space Administration, 1965), by Lucien A. Schmit, William A. Thornton, Case Institute of Technology, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Exploratory investigation of sound pressure level in the wake of an oscillating airfoil in the vicinity of stall (National Aeronautics and Space Administration ;, 1972), by Robin B. Gray, G. A. Pierce, Langley Research Center, and Georgia Institute of Technology (page images at HathiTrust)
Theoretical and experimental study of a new method for prediction of profile drag of airfoil sections (National Aeronautics and Space Administration ;, 1975), by Suresh H. Goradia, D. G. Lilley, Langley Research Center, and Lockheed-Georgia Company (page images at HathiTrust)
The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil : drag euqations (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1989), by Cuyler W. Brooks, William D. Harvey, and Charles D. Harris (page images at HathiTrust)
The effects of leading-edge serrations on reducing flow unsteadiness about airfoils : an experimental and analytical investigation (National Aeronautics and Space Administration ;, 1973), by R. G. Schwind, H. J. Allen, Ames Research Center, and Nielsen Engineering & Research (page images at HathiTrust)
Experimental studies of flow separation and stalling on a two-dimensional airfoil at low speeds (National Aeronautics and Space Administration, 1975), by H. C. Seetharam, W. H. Wentz, Wichita State University, and Langley Research Center (page images at HathiTrust)
Boundary-fitted curvilinear coordinate systems for solution of partial differential equations on fields containing any number of arbitrary two-dimensional bodies (National Aeronautics and Space Administration ;, 1978), by Joe F. Thompson, Charles Wayne Mastin, Frank C. Thames, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Acoustic radiation and surface pressure characteristics of an airfoil due to incident turbulence (National Aeronautics and Space Administration ;, 1976), by Robert W. Paterson, Roy K. Amiet, United Technologies Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Two-dimensional wind tunnel test of an oscillating rotor airfoil, volume I (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1977), by L. U. Dadone and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
A low speed two-dimensional study of flow separation on the GA(W)-1 airfoil with 30-percent chord Fowler flap (National Aeronautics and Space Administration, 1977), by H. C. Seetharam, W. H. Wentz, Wichita State University, and Langley Research Center (page images at HathiTrust)
Evaluation of effectiveness of various devices for attenuation of trailing vortices based on model tests in a large towing basin (National Aeronautics and Space Administration ;, 1973), by Karl L. Kirkman, Alex Goodman, Clinton E. Brown, Langley Research Center, and inc Hydronautics (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)
Jet array impingement with crossflow - correlation of streamwise resolved flow and heat transfer distributions (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by L. W. Florschuetz, C. R. Truman, Darryl E. Metzger, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
A rapid implicit-explicit solution to the two-dimensional time-dependent incompressible Navier-Stokes equations (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Joseph E. Davis, Ames Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Operational manual for two-dimensional transonic code TSFOIL (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Stephen S. Stahara, Ames Research Center, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Nielsen Engineering & Research (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)
The effects of winglets on low aspect ratio wings at supersonic Mach numbers (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ;, 1991), by James A. Keenan, John Kuhlman, Langley Research Center, and West Virginia University. Dept. of Mechanical and Aerospace Engineering (page images at HathiTrust)
An analysis of the crossover between local and massive separation on airfoils (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1987), by M. Burnett, J. E. Carter, and Langley Research Center (page images at HathiTrust)
Heat transfer measurements from a NACA 0012 airfoil in flight and in the NASA Lewis Icing Research Tunnel (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Philip E. Poinsatte, Lewis Research Center, and University of Toledo. Dept. of Chemical Engineering (page images at HathiTrust)
Numerical simulation and comparison of symmetrical/supercritical airfoils for the near tip region of a helicopter in forward flight (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1989), by F. F. Badavi and Langley Research Center (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)
Airfoil characteristics in a nonequilibrium ambient stream based on linearized theory (National Aeronautics and Space Administration :, 1964), by James J. Der, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Prediction of aerodynamic penalties caused by ice formations on various airfoils (National Aeronautics and Space Administration, 1964), by Vernon H. Gray and Lewis Research Center (page images at HathiTrust; US access only)
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; US access only)
Effect of ground proximity on the aerodynamic characteristics of aspect-ratio-1 airfoils with and without end plates (National Aeronautics and Space Administration, 1961), by Arthur W. Carter, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Flutter at very high speeds (National Aeronautics and Space Administration, 1961), by Harry L. Runyan, Homer G. Morgan, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Aerodynamic characteristics, temperature, and noise measurements of a large-scale external-flow jet-augmented-flap model with turbojet engines operating (National Aeronautics and Space Administration, 1961), by Marvin P. Fink, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
The effects of blowing over various trailing-edge flaps on an NACA 0006 airfoil section, comparisons with various types of flaps on other airfoil sections, and an analysis of flow and power relationships for blowing systems (National Aeronautics and Space Administration ;, 1976), by Jules B. Dods, Earl C. Watson, Ames Research Center, and United States. National Aeronautics and Space Center (page images at HathiTrust)
Procedure for scaling of experimental turbine vane airfoil temperatures from low to high gas temperatures (National Aeronautics and Space Administration, 1971), by Herbert J. Gladden, John N. B. Livingood, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
Pressure distributions and aerodynamic characteristics of several spoiler controls on a 40 degree sweptback wing at a Mach number of 1.61 (National Aeronautics and Space Administration, 1960), by Emma Jean Landrum, K. R. Czarnecki, and Langley Research Center (page images at HathiTrust)
Wind-tunnel tests of a full-scale model of a light twin-engine airplane with fixed auxiliary airfoil or leading-edge slot (National Aeronautics and Space Administration ;, 1974), by Marvin P. Fink, Lucy C. White, James P. Shivers, and Langley Research Center (page images at HathiTrust)
Comparisons of two-dimensional shock-expansion theory with experimental aerodynamic data for delta-planform wings at high supersonic speeds (National Aeronautics and Space Administration ;, 1974), by Lloyd S. Jernell and Langley Research Center (page images at HathiTrust)
NASA TN D-3936 (National Aeronautics and Space Administration :, 1967), by James Scheiman, Henry L. Kelley, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Experimental investigation at transonic speeds of pressure distributions over wedge and circular-arc airfoil sections and evaluation of perforated-wall interference (National Aeronautics and Space Administration, 1959), by Earl D. Knechtel and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-1788 (National Aeronautics and Space Administration ;, 1963), by Joseph M. Groen, Richard Rosecrans, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
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)
A method for predicting shock shapes and pressure distributions on two-dimensional airfoils at large angles of attack (National Aeronautics and Space Administration ;, 1973), by George E. Kaattari and Ames Research Center (page images at HathiTrust)
Measurements of surface-pressure and wake-flow fluctations in the flow field of a Whitcomb supercritical airfoil (National Aeronautics and Space Administration ;, 1977), by Frederick W. Roos, Dennis W. Riddle, Ames Research Center, 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 Charles M. Zimmey, Viola M. Lappi, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by John A. Zalovcik, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
Completed tabulation in the United States of tests of 24 airfoils at high Mach numbers (derived from interrupted work at Guidonia, Italy in the 1.31- by 1.74-foot high-speed tunnel) (Washington, 1946), by United States National Advisory Committee for Aeronautics and Antonio Ferri (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by Theodore Theodorsen, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
Generalization of Joukowski formula to an airfoil of a cascade in compressible gas stream with subsonic velocities (NACA, 1951), by L. G. Loĭt�si�anskiĭ and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by William Mutterperl, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1945), by E. O. Pearson, F. E. West, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1946), by W. F. Lindsey, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (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)
Lo stato attuale delle ricerche sul moto instazionario di una superficie portante (National Advisory Committee for Aeronautics, 1951), by P. Cicala and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
On the design of airfoils in which the transition of the boundary layer is delayed (NACA, 1952), by Itiro Tani 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)
Resistance of cascade of airfoils in gas stream at subsonic velocity (NACA, 1951), by L. G. Loĭt�si�anskiĭ and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by H. Page Hoggard, Marjorie E. Bulloch, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1945), by John M. Riebe, Oleta Church, 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)
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)
Investigation of a simple device for preventing separation due to shock and boundary-layer interaction (National Advisory Committee for Aeronautics, 1950), by Coleman duP. Donaldson, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Effect of thickness, camber, and thickness distribution on airfoil characteristics at Mach numbers up to 1.0 (National Advisory Committee for Aeronautics, 1952), by Bernard N. Daley, Richard S. Dick, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (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)
Two-dimensional low-speed cascade investigation of NACA compressor blade sections having a systematic variation in mean-line loading (National Advisory Committee for Aeronautics, 1953), by John R. Erwin, James C. Emery, Melvyn Savage, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
The effect of a change in airfoil section on the hinge-moment characteristics of a half-delta tip control with a 60° sweep angle at a Mach number of 6.9 (National Advisory Committee for Aeronautics, 1954), by David E. Fetterman, Herbert W. Ridyard, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
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)
Flutter at very high speeds (National Advisory Committee for Aeronautics, 1957), by Harry L. Runyan, Homer G. Morgan, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
An analysis of estimated and experimental transonic downwash characteristics as affected by plan form and thickness for wing and wing-fuselage configurations (National Advisory Committee for Aeronautics, 1952), by Joseph Weil, Margaret S. Diederich, George S. Campbell, Langley Aeronautical Laboratory, and United States. National Adviosry 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)
Charts of pressure rise obtainable with airfoil-type axial-flow cooling fans (National Advisory Committee for Aeronautics ;, 1947), by A. Kahane and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Isolated and cascade airfoils with prescribed velocity distribution (National Advisory Committee for Aeronautics, 1947), by John M. Riebs, Meyer Jerison, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Volterra's solution of the wave equation as applied to three-dimensional supersonic airfoil problems (National Advisory Committee for Aeronautics, 1947), by Max A. Heaslet, Arthur L. Jones, Harvard Lomax, 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)
Velocity distributions on symmetrical airfoils in closed tunnels by conformal mapping (National Advisory Committee for Aeronautics, 1948), by W. Perl, H. E. Moses, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
The yawing moment, due to sideslip of triangular, trapezoidal, and related plan forms in supersonic flow (National Advisory Committee for Aeronautics, 1949), by Arthur L. Jones, Alberta Alksne, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Subsonic two-dimensional-flow conditions near an airfoil determined by static pressures measured at the tunnel wall (National Advisory Committee for Aeronautics, 1949), by Bernard N. Daley, Lillian E. Hanna, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Calculation of the aerodynamic loading of flexible wings of arbitrary plan form and stiffness (National Advisory Committee for Aeronautics, 1949), by Franklin W. Diederich 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)
Note on the accuracy of a method for rapidly calculating the increments in velocity about an airfoil due to angle of attack (National Advisory Committee for Aeronautics, 1949), by Laurence K. Loftin and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Effect of aspect ratio on undamped torsional oscillations of a thin rectangular wing in supersonic flow (National Advisory Committee for Aeronautics, 1949), by Charles E. Watkins and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Velocity distributions on arbitrary airfoils in closed tunnels by conformal mapping (National Advisory Committee for Aeronautics, 1949), by H. E. Moses 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)
Investigation of spoiler ailerons for use as speed brakes or glide-path controls on two NACA 65-series wings equipped with full-span slotted flaps (National Advisory Committee for Aeronautics, 1949), by Jack Fischel, James M. Watson, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Low-speed experimental investigation of a thin, faired, double-wedge airfoil section with nose and trailing-edge flaps (National Advisory Committee for Aeronautics, 1949), by Leonard M. Rose, John M. Altman, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Attainable circulation of airfoils in cascade (National Advisory Committee for Aeronautics, 1949), by Arthur W. Goldstein, Artur Mager, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Theoretical relations between the stability derivatives of a wing in direct and in reverse supersonic flow (National Advisory Committee for Aeronautics, 1949), by Sidney M. Harmon and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
The reversibility theorem for thin airfoils in subsonic and supersonic flow (National Advisory Committee for Aeronautics, 1949), by Clinton E. Brown and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Measurements in the boundary layer of a yawed wing (National Advisory Committee for Aeronautics, 1949), by A. M. Kuethe, W. H. Curry, P. B. McKee, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Damping-in-roll calculations for slender swept-back wings and slender wing-body combinations (National Advisory Committee for Aeronautics, 1949), by Harvard Lomax, Max A. Heaslet, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Equations and charts for the rapid estimation of hinge-moment and effectiveness parameters for trailing-edge controls having leading and trailing edges swept ahead of the Mach lines (National Advisory Committee for Aeronautics, 1950), by Kennith L. Goin 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)
Similarity laws for transonic flow about wings of finite span (National Advisory Committee for Aeronautics, 1951), by John R. Spreiter 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)
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)
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)
Correspondence flows for wings in linearized potential fields at subsonic and supersonic speeds (National Advisory Committee for Aeronautics, 1951), by Sidney M. Harmon and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Wind-tunnel investigation at low speed of lateral control characteristics of an untapered 45° sweptback semispan wing of aspect ratio 1.59 equipped with various 25-percent-chord plain ailerons (National Advisory Committee for Aeronautics, 1951), by Harold S. Johnson, John R. Hagerman, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Transient aerodynamic behavior of an airfoil due to different arbitrary modes of nonstationary motions in a supersonic flow (National Advisory Committee for Aeronautics, 1951), by Chieh-Chien Chang and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Two-dimensional transonic flow past airfoils (National Advisory Committee for Aeronautics, 1951), by Yung-Huai Kuo 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)
An experimental investigation of transonic flow past two-dimensional wedge and circular-arc sections using a Mach-Zehnder interferometer (National Advisory Committee for Aeronautics, 1951), by Arthur E. Bryson 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)
Determination of mean camber surfaces for wings having uniform chordwise loading and arbitrary spanwise loading in subsonic flow (National Advisory Committee for Aeronautics, 1953), by S. Katzoff, Hugh C. DuBose, M. Frances Faison, 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)
Theoretical prediction of pressure distributions on nonlifting airfoils at high subsonic speeds (National Advisory Committee for Aeronautics, 1954), by John R. Spreiter, Alberta Alksne, 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)
Formulas and tables of coefficients for numerical differentiation with function values given at unequally spaced points and application to solution of partial differential equations (National Advisory Committee for Aeronautics, 1950), by Zhonghua Wu, Lewis Research Center, and United States National Advisory Committee for Aeronautics (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)
An Integrating manometer for use in wind tunnel pressure distribution measurements (National Advisory Committee for Aeronautics ;, 1931), by Richard W. Noyes and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Wind-tunnel investigation of the boundary layer on an NACA 0009 airfoil having 0.25- and 0.50-airfoil chord plain sealed flaps (National Advisory Committee for Aeronautics, 1948), by Jack D. Brewer, Josephine F. Polhamus, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
On the Second-order tunnel-wall-constriction corrections in two-dimensional compressible flow (National Advisory Committee for Aeronautics, 1951), by E. B. Klunker, Keith C. Harder, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
NACA Wartime Reports. Series A. (National Advisory Committee for Aeronautics, 1944), by Robert M. Crane, Ralph W. Holtzclaw, Ames Research Center, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
NACA Wartime Reports. Series A. (National Advisory Committee for Aeronautics, 1944), by Robert M. Crane, Ralph W. Holtzclaw, Ames Research Center, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
NACA Wartime Reports. Series E. (National Advisory Committee for Aeronautics, 1945), by W. Perl, M. Tucker, Aircraft Engine Research 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 J. D. Bird, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
NACA Wartime Reports. Series L. (National Advisory Committee for Aeronautics, 1944), by 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, 1943), by H. Page Hoggard, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
NACA Wartime Reports. Series L. (National Advisory Committee for Aeronautics, 1942), by Francis M. Rogallo, Paul E. Purser, 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 Harold E. Cleary, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
NACA Wartime Reports. Series L. (National Advisory Committee for Aeronautics, 1944), by Harold E. Cleary, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
NACA Wartime Reports. Series L. (National Advisory Committee for Aeronautics, 1944), by John G. Lowry, I. Elizabeth Garner, James A. Maloney, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Chord-wise air load distribution : War Dept., Army Air Forces : Navy Dept., Bureau of Aeronautics : Dept. of Commerce, Civil Aeronautics ... ([U.S. Govt. Print. Off.?], 1942), by United States. Army-Navy-Civil Committee on Aircraft Design Criteria (page images at HathiTrust)
Scientific fairing of veneer fuselages. (Dayton, Ohio : Airplane Engineering Division, Experimental Department, 1918., 1918), by United States. Bureau of Aircraft Production (page images at HathiTrust)
Construction and testing of a doubly-flexible flutter model of a delta wing. (M.I.T. Aeroelastic and Structures Research Laboratory, 1955), by Michael M. Chen (page images at HathiTrust; US access only)
Comparative flutter calculations on low-aspect-ratio wings in incompressible and supersonic flows. (M.I.T. Department of Aeronautical Engineering, 1954), by Garabed Zartarian, Herbert M. Voss, and Pao Tan Hsu (page images at HathiTrust; US access only)
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)
Airfoil section data obtained in the N. A. C. A. variable-density tunnel as affected by support interference and other corrections (U. S. Govt. print. off.], 1939), by Eastman Nixon Jacobs and Ira Herbert Abbot (page images at HathiTrust; US access only)
On harmonic motion of wide delta airfoils at supersonic speeds (U.S. Naval Ordnance Test Station, Research Dept., Ballistics Division, Aerodynamics Branch, 1950), by John Miles (page images at HathiTrust)
The characteristics of 78 related airfoil sections from tests in the variable-density wind tunnel (U.S. G.P.O., 1933), by Eastman Nixon Jacobs, Robert McLean Pinkerton, and Kenneth Edwards Ward (page images at HathiTrust; US access only)
Tests of related forward-camber airfoils in the variable-density wind tunnel (U.S. G.P.O.], 1939), by Eastman Nixon Jacobs, Harry Greenberg, and Robert McLean Pinkerton (page images at HathiTrust; US access only)
16th Wilbur Wright memorial lecture (London : "The Royal aeronautical society", 1928., 1928), by Frederick Handley Page (page images at HathiTrust; US access only)
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; US access only)
Unsteady airloads on pointed airfoils and slender bodies at high mach numbers (Wright Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1959., 1959), by Garabed Zartarian, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Massachusetts Institute of Technology (page images at HathiTrust)
The generation of gusts in a wind tunnel and measurement of unsteady lift on an airfoil (Wright-Patterson Air Force Base, Ohio : Wright Air Development Division, Air Research and Development Command, United States Air Force, 1957., 1957), by L. C. Garby, J. D. Schetzer, A. M. Kuethe, United States. Air Force. Air Research and Development Command, University of Michigan, and Wright Air Development Center (page images at HathiTrust)
Aerodynamic heating and heat transfer for airfoils at Mach numbers of 2.74 through 5.7 (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1955., 1955), by A. E. Abramson, J. A. Zdrazil, W. L. Torgeson, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Inc Research (page images at HathiTrust)
A study of aerodynamic control in stalled flight long laminar separation bubble analysis (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 Frank A. Dvorak, D. H. Choi, Air Force Flight Dynamics Laboratory (U.S.), Air Force Wright Aeronautical Laboratories, and Inc Analytical Methods (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)
Handbook of supersonic aerodynamics : Volume 4 (Washington, D. C. : U.S. Bureau of Ordnance, U.S. Naval Ordnance Laboratory , 1952., 1952), by Johns Hopkins University. Applied Physics Laboratory and United States. Navy Department. Bureau of Ordnance (page images at HathiTrust)
An Analysis of wake-stator interaction in airfoil cascades (Bolling Air Force Base, D. C. : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 1995., 1995), by M. Barnett, D. L. Sondak, United Technologies Research Center, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Large eddy simulation of turbulent flow over an airfoil (Stanford, California : Stanford University, Department of Mechanical Engineering, Thermosciences Division, 1995., 1995), by Parviz Moin, Stanford University. Thermosciences Division, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Development of a miniature pressure transducer for application to airfoil studies in the shock tube (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1958., 1958), by J. Ray Ruetenik, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Massachusetts Institute of Technology. Aeroelastic and Structures Research Laboratory (page images at HathiTrust)
Optimal controller for turbulent flow over an airfoil (Arlington, Virginia. : Air Force Office of Scientific Research, 2006., 2006), by John Kim, Los Angeles. Mechanical University of California, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
An influence of the orifice on measured pressures in rarefied flow (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1964., 1964), by J. Leith Potter, David E. Boylan, Max Kinslow, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Low Reynolds number aerodynamics of flapped airfoils at supersonic speeds (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1958., 1958), by James L. Amick, Gerard F. Carvalho, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and University of Michigan (page images at HathiTrust)
Two-dimensional airfoils (Washington, D. C. : U.S. Bureau of Ordnance, U.S. Naval Ordnance Laboratory , 1957., 1957), by Johns Hopkins University. Applied Physics Laboratory and United States. Navy Department. Bureau of Ordnance (page images at HathiTrust)
Handbook of supersonic aerodynamics : Volume 1 (Washington, D. C. : U.S. Bureau of Ordnance, U.S. Naval Ordnance Laboratory , 1950., 1950), by Johns Hopkins University. Applied Physics Laboratory and United States. Navy Department. Bureau of Ordnance (page images at HathiTrust)
Numerical calculation of the subsonic and transonic turbulent boundary layer on an infinite yawed airfoil (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, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Unsteady viscous-inviscid interaction procedures for transonic airfoil flows (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1984., 1984), by Tracy Donegan, United States. Air Force. Arnold Air Force Base, Arnold Engineering Development Center, and Calspan Field Services (page images at HathiTrust)
Nonlinear normal and axial force indicial responses for a two dimensional airfoil (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 1991., 1991), by G. M. Graham, K. C. Fang, M. Islam, Ohio University, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Flow transition in gas turbine airfoil boundary layers: fundamentals and empiricisms (Wright-Patterson Air Force Base, Ohio : Aero Propulsion Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1985., 1985), by Gregory S. West, Lit S. Han, Air Force Wright Aeronautical Laboratories, and University of Dayton. Research Institute (page images at HathiTrust)
Direct numerical simulation of flow transition in compressible boundary layer around airfoils (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, United States Air Force, 1997., 1997), by Chaoqun Liu, Guohua Xiong, Wei Zhao, Zhining Liu, United States. Air Force. Office of Scientific Research, and Louisiana Tech University (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)
Transonic scaling effect on a quasi, two-dimensional C-141 airfoil model (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1973., 1973), by C. F. Lo, W. E. Carleton, Arnold Engineering Development Center, United States. Air Force. Systems Command, and Inc ARO (page images at HathiTrust)
Unsteady separated flows : empirical model and control (Boulder, Colorado : University of Colorado, Aerospace Sciences, 1993., 1993), by Marvin Luttges, Michael Robinson, University of Colorado Boulder, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Two-dimensional Navier-Stokes solution of the flow over a thick supercritical airfoil with strong shock-induced separation (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1988., 1988), by Don W. Kinsey, Air Force Wright Aeronautical Laboratories, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
Handbook of supersonic aerodynamics : Volume 2 / Johns Hopkins University, Applied Physics Laboratory. (White Oak, Maryland : U.S. Naval Ordnance Laboratory, 1950), by Johns Hopkins University. Applied Physics Laboratory and United States. Navy Department. Bureau of Ordnance (page images at HathiTrust)
Unsteady flow past a NACA 0012 airfoil pitching at constant rates (Tallahassee, Florida : Florida A&M University, Department of Mechanical Engineering, 1993., 1993), by Luiz M. Lourenco, C. Shih, Leon L. Van Dommelen, Anjaneyulu Krothapalli, Florida Agricultural and Mechanical University, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by Warren A. Tucker, Arthur R. Wallace, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by John H. Quinn, Warren A. Tucker, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1945), by John A. Zalovcik, Richard B. Skoog, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1946), by Laurence K. Loftin, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1945), by William J. Underwood, Jones F. Cahill, Albert L. Braslow, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by Albert L. Braslow, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by Felicien F. Fullmer, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by Albert E. Von Doenhoff, Louis S. Stivers, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by Frank T. Abbott, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
Effect of Mach number, Reynolds number, and thickness ratio on the aerodynamic characteristics of NACA 63A-series airfoil sections (Fort Eustis, Virginia : U.S. Army Aviation Materiel Laboratories, June 1965., 1965), by O. E. Sipe, N. B. Gorenberg, Lockheed-California Company, and U.S. Army Aviation Materiel Laboratories (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)

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