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Supersonic speed

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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)
• Supersonic aerodynamic characteristics of a 1/6-scale model of the final two stages of the Argo D-4 four-stage rocket vehicle / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1965), by Clyde Hayes, William A. Corlett, and Langley Research Center (page images at HathiTrust)
• Effect of a variable-geometry diffuser on the operating characteristics of a helium tunnel designed for a mach number in excess of 20 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Patrick J. Johnston, Robert D. Witcofski, and Langley Research Center (page images at HathiTrust)
• Measurement of flow angularity at supersonic and hypersonic speeds with the use of a conical probe / (Washington, [D.C.] : National Aeronautics and Space Administration, [1961]), by Frank E. Swalley, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Flight test of a 30-foot nominal diameter disk-gap-band parachute deployed at a Mach number of 1.56 and a dynamic pressure of 11.4 pounds per square foot / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1967), by Clinton V. Eckstrom, John S. Preisser, and Langley Research Center (page images at HathiTrust)
• Effects of wing planform on the aerodynamic characteristics of a wing-body-tail model at Mach numbers 3.96 and 4.63 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1966), by Maurice O. Feryn and Langley Research Center (page images at HathiTrust)
• Lateral directional stability characteristics at mach 2.3 to 3.5 of a supersonic transport model with various outboard vertical-tail locations / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1965), by William A. Corlett and Langley Research Center (page images at HathiTrust)
• Experimental investigation of the effects of compressive stress on the flutter of a curved panel and a flat panel at supersonic Mach numbers / (Washington, [D.C.] : National Aeronautics and Space Administration, 1962), by R. W. Hess, Frederick W. Gibson, 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)
• Trim drag at supersonic speeds of various delta-planform configurations / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by M. E. Graham, B. M. Ryan, and Douglas Aircraft Company (page images at HathiTrust)
• Measured and theoretical flow fields behind a rectangular and a triangular wing up to high angles of attack at a Mach number of 2.46 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Frank J. Centolanzi and Ames Research Center (page images at HathiTrust)
• Investigation by Schlieren technique of methods of fixing fully turbulent flow on models at supersonic speeds / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Mary W. Jackson, K. R. Czarnecki, and Langley Research Center (page images at HathiTrust)
• Effect of distributed three-dimensional roughness and surface cooling on boundary-layer transition and lateral spread of turbulence at supersonic speeds / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Albert L. Braslow, Elmer A. Horton, Eugene C. Know, and Langley Research Center (page images at HathiTrust)
• Two techniques for detecting boundary-layer transition in flight at supersonic speeds and at altitudes above 20,000 feet / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by John G. McTigue, Gilbert Petty, John D. Overton, and Flight Research Center (U.S.) (page images at HathiTrust)
• Investigation of methods for computing flutter characteristics of supersonic delta wings and comparison with experimental data / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Charles H. Wilts and California Institute of Technology (page images at HathiTrust)

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