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Aerofoils -- Testing

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• Aerofoils
• Testing

• Aerofoils -- Testing -- Statistics
• Aerofoils -- Wind tunnel testing
• Blades -- Testing
• Camber (Aerofoils) -- Testing
• Flaps (Airplanes) -- Testing
• Leading edges (Aerodynamics) -- Testing
• Rotors (Helicopters) -- Testing
• Stalling (Aerodynamics) -- Testing
• Aerofoils -- Fluid dynamics -- Testing
• Aerofoils -- Models -- Testing

• The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil : design overview (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1988), by Charles D. Harris, Cuyler W. Brooks, William D. Harvey, and Langley Research Center (page images at HathiTrust)
• Wind-tunnel investigation of a full-scale general aviation airplane equipped with an advanced natural laminar flow wing (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1987), by Daniel G. Murri, Frank L. Jordan, and Langley Research Center (page images at HathiTrust)
• Comparison of a two-dimensional adaptive-wall technique with analytical wall interference correction techniques (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Raymond E. Mineck and Langley Research Center (page images at HathiTrust)
• Full-scale semispan tests of a business-jet wing with a natural laminar flow airfoil (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ;, 1991), by David E. Hahne, Frank L. Jordan, and Langley Research Center (page images at HathiTrust)
• The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil : suction coefficient analysis (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ;, 1991), by Cuyler W. Brooks, William D. Harvey, Charles D. Harris, and Langley Research Center (page images at HathiTrust)
• Evaluation of flow quality in two large NASA wind tunnels at transonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Bill Harvey, F. Kevin Owen, P. Calvin Stainback, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Aerodynamic characteristics of three helicopter rotor airfoil sections at Reynolds numbers from model scale to full scale at Mach numbers from 0.35 to 0.90 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Kevin W. Noonan, Gene J. Bingham, Army Research and Technology Laboratories (U.S.). Structures Laboratory, United States. Army Aviation Research and Development Command, 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)
• Studies of condensation effects on airfoil testing in the Langley 0.3-meter transonic cryogenic tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1986), by Robert M. Hall and Langley Research Center (page images at HathiTrust)
• Experimental results for the Eppler 387 airfoil at low Reynolds numbers in the Langley low-turbulence pressure tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988), by Robert J. McGhee, Betty F. Millard, Betty S. Walker, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division (page images at HathiTrust)
• Aerodynamic performance and pressure distributions for a NASA SC(2)-0714 airfoil tested in the Langley 0.3-meter transonic cryogenic tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988), by Renaldo V. Jenkins, Edward J. Ray, Acquilla S. Hill, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division (page images at HathiTrust)
• Experimental and theoretical low-speed aerodynamic characteristics of the NACA 65₁-213, a = 0.50 airfoil (National Aeronautics and Space Administration ;, 1975), by William D. Beasley, William D. McGhee, and Langley Research Center (page images at HathiTrust)
• The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil : evaluation of initial perforated configuration (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Charles D. Harris and Langley Research Center (page images at HathiTrust)
• Reynolds number tests of an NPL 9510 airfoil in the Langley 0.3-meter transonic cryogenic tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Renaldo V. Jenkins and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Detailed transonic flow field measurements about a supercritical airfoil section (National Aeronautics and Space Administration ;, 1975), by Francis X. Hurley and Ames Research Center (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)
• Experimental investigation of three helicopter rotor airfoils designed analytically (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by Gene J. Bingham, Kevin W. Noonan, Army Research and Technology Laboratories (U.S.). Structures Laboratory, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Design and experimental results for a flapped natural-laminar-flow airfoil for general aviation applications (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Dan M. Somers and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Pressure distributions from high Reynolds number tests of a NASA SC(3)-0712(B) airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by William G. Johnson, Otto Eichmann, Acquilla S. Hill, and Langley Research Center (page images at HathiTrust)
• High Reynolds number tests of a NASA SC(3)-0712(B) airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by William G. Johnson, Otto Eichmann, Acquilla S. Hill, and Langley Research Center (page images at HathiTrust)
• Design and experimental results for a Natural-Laminar-Flow airfoil for general aviation application (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Dan M. Somers, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Section data for thin, highly cambered airfoils in incompressible flow (National Aeronautics and Space Administration ;, 1971), by Jerome H. Milgram, Langley Research Center, Massachusetts Institute of Technology, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Analysis of a theoretically optimized transonic airfoil (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by M. E. Lores, George D. Shrewsbury, Kenneth P. Burdges, Ames Research Center, and Lockheed-Georgia Company (page images at HathiTrust)
• A simplified fourwall interference assessment procedure for airfoil data obtained in the Langley 0.3-meter transonic cryogenic tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987), by A. V. Murthy and Langley Research Center (page images at HathiTrust)
• Aerofoil testing in a self-streamlining flexible walled wind tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988), by Mark Charles Lewis and Langley Research Center (page images at HathiTrust)
• Experimental and theoretical low-speed aerodynamic characterisitics of a Wortmann airfoil as manufactured on a fiberglass sailplane (National Aeronautics and Space Administration :, 1977), by Dan M. Somers and United States National Aeronautics and Space Administration (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)
• A tabulation of wind-tunnel pressure data and section aerodynamic characteristics at Mach numbers of 1.61 and 2.01 for a reflex cambered wing and a cambered and twisted wing having the same swept planform (National Aeronautics and Space Administration :, 1962), by Emma Jean Landrum and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Evaluation of turbulence reduction devices for the Langley 8-foot Transonic Pressure Tunnel (National Aeronautics and Space Administration, 1981), by Marion O. McKinney, James Scheiman, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Aerodynamic characteristics of several 6-percent-thick airfoils at angles of attack from 0 to 20 degrees at high subsonic speeds (National Advisory Committee for Aeronautics, 1949), by Bernard N. Daley, Douglas R. Lord, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• 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)
• Flight investigation at Mach numbers from 0.6 to 1.7 to determine drag and base pressures on a blunt-trailing-edge airfoil and drag of diamond and circular-arc airfoils at zero lift (National Advisory Committee for Aeronautics, 1950), by John D. Morrow, Ellis Katz, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Results of two free-fall experiments on flutter of thin unswept wings in the transonic speed range (National Advisory Committee for Aeronautics, 1951), by WIlliam T. Lauten, Herbert C. Nelson, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Results of two experiments on flutter of high-aspect-ratio swept wings in the transonic speed range (National Advisory Committee for Aeronautics, 1952), by William T. Lauten, Burke R. O'Kelly, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Transonic wind-tunnel investigation of the effects of aspect ratio, spanwise variations in section thickness ratio, and a body indentation on the aerodynamic characteristics of a 45©� sweptback wing-body combination (National Advisory Committee for Aeronautics, 1953), by Melvin M. Carmel, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Investigation of transonic flutter characteristics of a thin 10 degree sweptback wing having an aspect ratio of 4 and a taper ratio of 0.6 (National Advisory Committee for Aeronautics, 1957), by George W. Jones, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation at Mach numbers from 0.80 to 1.43 of pressure and load distributions over a thin 45©� sweptback highly tapered wing in combination with basic and indented bodies (National Advisory Committee for Aeronautics, 1957), by Thomas L. Fischetti, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, 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)
• Lateral-control investigation of flap-type controls on a wing with quarter-chord line sweptback 35©�, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section. Transonic-bump method (National Advisory Committee for Aeronautics, 1950), by Robert F. Thompson, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Effects of wing 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)
• Oberflachenrauhigkeiten auf Tragflugeln. (National Advisory Committee for Aeronautics ;, 1926), by O. Schrenk and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• The Effect of small variations in profile of airfoils (National Advisory Committee for Aeronautics ;, 1931), by Kenneth E. Ward and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Collection and analysis of hinge-moment data on control-surface tabs (National Advisory Committee for Aeronautics ;, 1947), by Paul E. Purser, Charles B. Cook, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• 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)
• NACA Wartime Reports. Series L. (National Advisory Committee for Aeronautics, 1942), by Ira H. Abbott, Langley Aeronautical Laboratory, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• The drag and stability of a circular wedge airfoil in supersonic flight (Aberdeen, Maryland : Aberdeen Proving Ground, 1960., 1960), by Maynard J. Piddington, C. H. Murphy, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Miniature piezoelectric gages for measuring transient pressures on airfoils (Aberdeen, Maryland : Aberdeen Proving Ground, 1961., 1961), by W. E. Baker, W. O. Ewing, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Use of truncated flapped airfoils for impingement and icing tests of full-scale leading-edge sections (National Advisory Committee for Aeronautics, 1956), by U. Von Glahn and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Effect of compressibility on pressures and forces acting on an airfoil. (1940), by John Stack, Robert E. Littell, W. F. Lindsey, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Wind-tunnel investigation of an NACA 23021 airfoil with various arrangements of slotted flaps. (National Advisory Committee for Aeronautics, 1939), by Carl J. Wenzinger, Thomas A. Harris, and Langley Aeronautical Laboratory (page images at HathiTrust)

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