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Aspect ratio

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• Pressure distributions and aerodynamic characteristics of several spoiler controls on a 40 degree sweptback wing at a Mach number of 1.61 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Emma Jean Landrum, K. R. Czarnecki, and Langley Research Center (page images at HathiTrust)
• Effects of canard planform and wing-leading-edge modification on low-speed longitudinal aerodynamic characteristics of a canard airplane configuration / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Bernard Spencer, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• The effects of an inverse-taper leading-edge flap on the aerodynamic loading characteristics of a 45° sweptback wing at Mach numbers to 0.90 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Fred A. Demele and Ames Research Center (page images at HathiTrust)
• Investigation of double slotted flaps on a swept-wing transport model / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Rodger L. Naeseth, Edwin E. Davenport, 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 / (Washington, [D.C.] : 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)
• Static longitudinal characteristics at high subsonic speeds of a complete airplane model with a highly tapered wing having the 0.80 chord line unswept and with several tail configurations / (Washington [D.C.] : National Aeronautics and Space Administration, 1961), by Kenneth W. Goodson, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Transonic aerodynamic loading characteristics of a wing-body-tail combination having 52.5° sweptback wing of aspect ratio 3 with conical wing camber and body indentation for a design Mach number [square root of] 2 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Marlowe D. Cassetti, William B. Igoe, Richard J. Re, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Effect of ground proximity on the aerodynamic characteristics of aspect-ratio-1 airfoils with and without end plates / (Washington, [D.C.] : 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)
• Experimental investigation of the effect of aspect ratio and Mach number on the flutter of cantilever wings / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by E. Widmayer, S. A. Clevenston, W. T. Lauten, and Langley Research Center (page images at HathiTrust)
• Wing-on and wing-off longitudinal characteristics of an airplane configuration having a thin unswept wing of aspect ratio 3, as obtained from rocket-propelled models at Mach numbers from 0.8 to 1.4 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Clarence L. Gillis, A. James Vitale, and Langley Research Center (page images at HathiTrust)
• The hydrodynamic characteristics of a submerged lifting surface having a shape suitable for hydro-ski application / (Washington [D.C.] : National Aeronautics and Space Administration, 1959), by Victor L. Vaughan and Langley Research Center (page images at HathiTrust)
• Wind-tunnel tests of a semispan wing with a fan rotating in the plane of the wing / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by David H. Hickey, David R. Ellis, and Ames Research Center (page images at HathiTrust)

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