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Wind tunnel tests

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• Pressure distributions on a rectangular aspect-ratio-6, slotted supercritical airfoil wing with externally blown flaps / (Washington : U.S. National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by William G. Johnson, Langley Research Center, and United States National Aeronautics and Space Administration (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 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Emma Jean Landrum, K. R. Czarnecki, and Langley Research Center (page images at HathiTrust)
• Ground effect for lifting rotors in forward flight / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Harry H. Heyson and Langley Research Center (page images at HathiTrust)
• Effects of a lower surface jet on the lift-drag ratio of a 45° sweptback wing at a Mach number of 2.01 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Emma Jean Landrum and Langley Research Center (page images at HathiTrust)
• Wind-tunnel investigation of the carry loads and mutual interference effects of 1/40-scale models of the X-15 and B-52 apirplanes in combination. / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Robert T. Taylor, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Aerodynamic characteristics of 0.187-scale model of a target missile at Mach 1.80 to 2.16 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1966), by 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)
• Investigation of aerodynamic effects of external combustion below flat-plate model in 10- by 10-foot wind tunnel at Mach 2.4 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Robert G. Dorsch, Murray Dryer, Harrison Allen, and Lewis Research Center (page images at HathiTrust)
• Effects of jet billowing on stability of missile-type bodies at Mach 3.85 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Reino J. Salmi and Lewis Research Center (page images at HathiTrust)
• Supersonic free-flight measurements of heat transfer and transition on a 10° cone having a low temperature ratio / (Washington, [D.C.] : National Aeronautical and Space Administration, 1961), by Charles F. Merlet, Charles B. Rumsey, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Lift and drag characteristics at subsonic speeds and at a Mach number of 1.9 of a lifting circular cylinder with a fineness ratio of 10 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Vernard E. Lockwood, Linwood W. McKinney, and Langley Research Center (page images at HathiTrust)
• Aerodynamic characteristics of several current helicopter tail boom cross sections including the effect of spoilers / ([Washington, DC] : National Aeronautics and Space Administration, 1986), by John C. org. AVSCOM. Wilson, Henry L. org. AVSCOM. Kelley, United States. Army Aviation Research and Technology Activity. Aerostructures Directorate, Langley Research Center, United States. Army Aviation Systems Command, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Wind-tunnel buffeting measurements on two wing end-plate airplane model configurations / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1967), by William B. Igoe and Langley Research Center (page images at HathiTrust)
• Supersonic aerodynamic characteristics of a Saturn IB launch vehicle model with third-stage modifications / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1966), by Roger H. Fournier 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)
• Wind-tunnel and piloted flight simulator investigation of a deflected-slipstream VTOL airplane, the Ryan VZ-3RY / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Harry A. James and Ames Research Center (page images at HathiTrust)
• Experimental investigation of orthotropic panel flutter at arbitrary yaw angles, and comparison with theory / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1973), by Peter Shyprykevich, Langley Research Center, and Grumman Aerospace Corporation (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)
• Aerodynamic loading characteristics at Mach numbers from 0.80 to 1.20 of a 1/10-scale three-stage scout model / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Thomas C. Kelly, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Wind-tunnel tests of seven static-pressure probes at transonic speeds / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Francis J. Capone, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Transonic wind-tunnel tests of an error-compensated static-pressure probe / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Francis J. Capone, 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)
• Terminal-shock and restart control of a Mach 2.5, axisymmetric, mixed compression inlet with 40 percent internal contraction / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by Robert J. Baumbick, Robert C. Seidel, Robert E. Wallhagen, and Lewis Research Center (page images at HathiTrust)
• Study of several factors affecting crew escape trajectories from the space shuttle orbiter at low-subsonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985), by William I. Scallion and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Comparison of full-scale and model buffet response of Apollo boilerplate service module / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1966), by Robert V. Doggett and Langley Research Center (page images at HathiTrust)
• Low-speed aerodynamic characteristics of airfoil sections with rounded trailing edges in forward and reverse flow / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by William D. Beasley, Robert J. McGhee, 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 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by Gene J. Bingham, Kevin W. Noonan, and Langley Research Center (page images at HathiTrust)
• Analytical investigation of effect of spin entry technique on spin and recovery characteristics for a 60 degree delta-wing airplane / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Stanley H. Scher, George F. Lawrence, Ernie L. Anglin, and Langley Research Center (page images at HathiTrust)
• Flight measurement of wall-pressure fluctuations and boundary-layer turbulence / (Washington [D.C.] : National Aeronautics and Space Administration, 1960), by Harold R. Mull, Joseph S. Algranti, and Lewis Research Center (page images at HathiTrust)
• Compressibility effects on the hovering performance of a two-blade 10-foot-diameter helicopter rotor operating at tip Mach numbers up to 0.98 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Joesph W. Jewel and Langley 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)
• Lift generation on a circular cylinder by tangential blowing from surface slots / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Vernard E. Lockwood and Langley Research Center (page images at HathiTrust)
• Free flight observation of a separated turbulent flow including heat transfer up to Mach 8.5 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Dudley George McConnell and Lewis 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)
• Wind tunnel investigation of simulated helicopter engine exhaust interacting with windstream / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by Craig S. Shaw, John C. Wilson, and Langley Research Center (page images at HathiTrust)
• Effects of Reynolds number and model support on the supersonic aerodynamic chacteristics of a 140° included-angle cone / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by Charles D. Trescot, Dorothy T. Howell, Clarence A. Brown, and Langley Research Center (page images at HathiTrust)
• Full-scale wind-tunnel investigation of the effects of a target-type thrust reverser on the low-speed aerodynamic characteristics of a single-engine jet airplane / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by William H. Tolhurst, Richard K. Greif, Mark W. Kelly, and Ames Research Center (page images at HathiTrust)
• Effectiveness of an all-movable horizontal tail on an unswept-wing and body combination for Mach numbers from 0.60 to 1.40 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Louis S. Stivers and Ames Research Center (page images at HathiTrust)
• Large-scale wind-tunnel tests of an airplane model with an unswept, aspect-ratio-10 wing, four propellers, and blowing flaps / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by James A. Weiberg, V. Robert Page, and Ames Research Center (page images at HathiTrust)
• Wind-tunnel investigation of the aerodynamic characteristics of a model representative of a supersonic fighter-class airplane with an external-flow jet-augmented flap in low-speed flight / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by William A. Newsom and Langley Research Center (page images at HathiTrust)
• Low-speed wind-tunnel investigation of a wingless jet VTOL transport model / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Marion O. McKinney and Langley Research Center (page images at HathiTrust)
• Full-scale wind-tunnel tests of a low-aspect-ratio, straight-wing airplane with blowing boundary-layer control on leading- and trailing-edge flaps / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Mark W. Kelly, Ralph L. Maki, William H. Tolhurst, and Ames 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)
• A limited flight and wind-tunnel investigation of paddle spoilers as lateral controls / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Robert G. Mungall, William L. Alford, Harold I. Johnson, and Langley Research Center (page images at HathiTrust)
• Full-scale wind-tunnel investigation of the longitudinal characteristics of a tilting-rotor convertiplane / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by David G. Koenig, Mark W. Kelly, Richard K. Greif, and Ames Research Center (page images at HathiTrust)
• Investigation at transonic speeds to determine lateral control effectiveness of blowing laterally over surfaces of 30° and 45° swept wings / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Alexander D. Hammond, Linwood W. McKinney, and Langley Research Center (page images at HathiTrust)
• Effects of body and fin deflections on the aerodynamic characteristics in pitch of a 0.065-scale model of a four-stage rocket configuration at Mach numbers of 1.41 and 1.82 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Ross B. Robinson and Langley Research Center (page images at HathiTrust)
• Low-speed wind-tunnel investigation of blowing boundary-layer control on leading- and trailing-edge flaps of a full-scale, low-aspect-ratio, 42° swept-wing airplane configuration / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Ralph L. Maki, Demo J. Giulianetti, and Ames Research Center (page images at HathiTrust)
• Wind-tunnel investigation of effect of ratio of wing chord to propeller diameter with addition of slats on the aerodynamic characteristics of tilt-wing VTOL configurations in the transition speed range / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Robert T. Taylor, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• An examination of methods of buffeting analysis based on experiments with wings of varying stiffness / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by A. Gerald Rainey, Thomas A. Byrdsong, and Langley Research Center (page images at HathiTrust)

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