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Pressure distribution

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• Calculation of compressible turbulent boundary layers with pressure gradients and heat transfer / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1969), by Larry L. Lynes, Gary D. Kuhn, Jack Norman Nielsen, Nielsen Engineering & Research, and Ames Research Center (page images at HathiTrust)
• 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)
• Transonic pressure measurements and comparison of theory to experiment for an arrow-wing configuration / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1976), by Marjorie E. Manro, Langley Research Center, and Boeing Commercial Airplane Company (page images at HathiTrust)
• Theoretical study of ducted fan performance / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1970), by M. R. Mendenhall, Selden B. Spangler, Ames Research Center, and Nielsen Engineering & Research (page images at HathiTrust)
• Distributed system response characteristics in random pressure fields / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1970), by Richard L. Barnoski, John R. Maurer, Goddard Space Flight Center, and Measurement Analysis Corporation (page images at HathiTrust)
• Analysis of laminar flow between stationary and rotating disks with inflow / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by Upendra S. Rohatgi, Eli Reshotko, Lewis Research Center, and Case Western Reserve University (page images at HathiTrust)
• Investigation of the effect of a guide-vane-rotor combination on inlet total-pressure distortions in a compressible fluid / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by George C. Ashby and Langley Research Center (page images at HathiTrust)
• Experimental investigation of the pressure fluctuations on a flat plate and a cylinder in the slipstream of a hovering rotor / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by John W. McKee and Langley Research Center (page images at HathiTrust)
• The effect of angle of attack on the buckling of Mars entry aeroshells / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1973), by Gerald A. Cohen, Langley Research Center, and Structures Research Associates (page images at HathiTrust)
• A simulator study of the effectiveness of a pilot's indicator which combined angle of attack and rate of change of total pressure as applied to the take-off rotation and climbout of a supersonic transport / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Albert W. Hall, Jack E. Harris, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Research and development program on cold cathode magnetron ultrahigh vacuum gage / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1969), by Robert M. Oman, Langley Research Center, and Norton Research Corporation (page images at HathiTrust)
• Laminar heat-transfer and pressure measurements at a Mach number of 6 on a sharp and blunt 15° half-angle cones at angles of attack up to 90° / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Raul J. Conti, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Operational method of determining initial contour of and pressure field about a supersonic jet / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Gerald W. Englert and Lewis 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 advanced concepts to increase turbine blade loading. (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1968), by H. G. Lueders, General Motors Corporation. Allison Division, and Lewis Research Center (page images at HathiTrust)
• An approximate method for calculating surface pressures on curved profile blunt plates in hypersonic flow / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Marcus O. Creager and Ames Research Center (page images at HathiTrust)
• Low subsonic pressure distributions on three rigid wings simulating paragliders with varied canopy curvature and leading-edge sweep / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Paul G. Fournier, B. Ann Bell, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Calculation of supersonic flow past bodies supporting shock waves shaped like elliptic cones / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Benjamin R. Briggs and Ames Research Center (page images at HathiTrust)
• Measured and predicted section wave drag coefficients at a Mach number of 1.6 for a delta wing with two airfoil sections / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Frederick C. Grant and Langley Research Center (page images at HathiTrust)

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