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Drag (Aerodynamics)

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• Aerodynamic load
• Aerodynamics
• Air resistance

• Base flow (Aerodynamics)
• Lift (Aerodynamics)

• Boundary layer control
• Skin friction (Aerodynamics)

• Aerodynamic forces
• Drag (physics)

• Flight-Determined Aerodynamic Properties of a Jet-Augmented, Auxiliary-Flap, Direct-Lift-Control System Including Correlation With Wind-Tunnel Results (NASA Technical Note D-5128, corrected copy; Washington: National Aeronautics and Space Administration, 1969), by L. Stewart Rolls, Anthony M. Cook, and Robert C. Innis
  • PDF at NASA
  • page images at HathiTrust
• Fluid-Dynamic Drag: Practical Information on Aerodynamic Drag and Hydrodynamic Resistance (revised and expanded from author's 1951 "Aerodynamic Drag"; Midland Park, NJ: The author, 1958), by Sighard F. Hoerner (page images at HathiTrust)
• Effects of sting-support interference on the drag of an ogive-cylinder body with and without a boattail at 0.6 to 1.4 mach number / (Washington : National Advisory Committee for Aeronautics, [1957]), by George Lee, James L. Summers, United States. National Advisory Committee for Aeronautics, and Ames Research Center (page images at HathiTrust)
• Comparison of full-scale lift and drag characteristics of the x-15 airplane with wind-tunnel results and theory / (Washington, D.C. : National Aeronautics and Space Administration, 1962), by Edward J. Hopkins, Edwin J. Saltzman, David E. Fetterman, Flight Research Center (U.S.), Langley Research Center, and Ames Research Center (page images at HathiTrust)
• Flight test results pertaining to the Space Shuttlecraft : a symposium held at Flight Research Center, Edwards, Calif., June 30, 1970. (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1970), by Flight Research Center (U.S.) (page images at HathiTrust)
• Variation of the drag coefficient with wind and wave state / (Monterey, Calif. : Naval Postgraduate School, 1985), by Beverly J Byars (page images at HathiTrust)
• Light aircraft lift, drag, and moment prediction : a review and analysis / (Washington, D.C. : National Aeronautics and Space Administration, 1975), by Frederick O. Smetana, Langley Research Center, and North Carolina State University (page images at HathiTrust)
• Longitudinal aerodynamic characteristics of an externally blown flap powered-lift model with several propulsive system simulators / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Danny R. Hoad and Langley Research Center (page images at HathiTrust)
• Aerodynamic characteristics of towed spheres, conical rings, and cones used as decelerators at Mach numbers from 1.57 to 4.65 / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1963), by Nickolai Charczenko, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Displacement effect of the laminar boundary layer and the pressure drag / (Washington, D.C. : NACA, 1951), by Henry Görtler and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Drag reduction by suction of the boundary layer separated behind shock wave formation at high mach numbers / (Washington, D.C. : NACA, 1947), by B. Regenscheit and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Theoretical investigation of drag reduction in maintaining the laminar boundary layer by suction / (Washington, D.C. : NACA, 1947), by A. Ulrich and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Experimental investigation of the effects of viscosity on the drag of bodies of revolution at a Mach number of 1.5 / (Washington, D.C. : NACA, 1947), by Dean R. Chapman, Edward W. Perkins, United States. National Advisory Committee for Aeronautics, and Ames Research Center (page images at HathiTrust)
• Aircraft configurations developing high lift-drag ratios at high supersonic speeds / (Washington, D.C. : NACA, 1956), by A. J. Eggers, Clarence A. Syvertson, United States. National Advisory Committee for Aeronautics, and Ames Research Center (page images at HathiTrust)
• A theoretical investigation of the drag of generalized aircraft configurations in supersonic flow / (Washington, D.C. : NACA, 1957), by E. W. Graham and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigations on reductions of friction on wings, in particular by means of boundary layer suction / (Washington, D.C. : NACA, 1947), by Werner Pfenninger and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• The aerodynamic analysis of single and multiple vehicles [entering and traveling in open tunnels] / (Washington : Dept. of Transportation, Federal Railroad Administration, Office of Research, Development, and Demonstration ; Springfield, Va. : For sale by the National Technical Information Service, 1975), by Charles R. Strom, Development and Demonstration United States. Federal Railroad Administration. Office of Research, and Mitre Corporation (page images at HathiTrust)
• Analytical and numerical investigation of structural response of compliant wall materials / (Washington : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978-), by Rama Krishna Balasubramanian and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Aerodynamic characteristics of a series of bodies with variations in nose camber / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1983), by Barrett L. Shrout, Peter F. Covell, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Computational study of single-expansion-ramp nozzles with external burning / ([Washington, D.C.] : National Aeronautics and Space Administration ; [Springfield, Va. : National Technical Information Service, distributor, 1994]), by Shaye Yungster, Charles J. Trefny, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Low-subsonic-speed static longitudinal stability and control characteristics of a winged reentry-vehicle configuration having wingtip panels that fold up for high-drag reentry / (Washington [D.C.] : National Aeronautics and Space Administration, [1960]), by George M. Ware and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effects of outboard thickened and blunted leading edges on the wave drag of a 45° swept-wing and body combination / (Washington [D.C.] : National Aeronautics and Space Administration, [1959]), by George H. Holdaway, Elaine W. Hatfield, Frank A. Lazzeroni, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Approach and landing investigation at lift-drag ratios of 2 to 4 utilizing a straight-wing fighter airplane / (Washington [D.C.] : National Aeronautics and Space Administration, [1959]), by Gene J. Matranga, Neil Armstrong, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Experimental investigation of a large-scale, two-dimensional, mixed-compression inlet system : internal performance and drag at transonic conditions, M[infinity]=0.6 to 1.28 / by Norman D. Wong and Warren E. Anderson. (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Norman D. Wong, Warren E. Anderson, and Ames Research Center (page images at HathiTrust)
• Use of potential flow theory to evaluate subsonic inlet data from a simulator-powered nacelle at cruise conditions / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Lawrence J. Bober and Lewis Research Center (page images at HathiTrust)
• A theoretical method for the analysis and design of axisymmetric bodies / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by T. D. Beatty, Langley Research Center, and McDonnell Douglas Corporation (page images at HathiTrust)
• Effect of location of aft-mounted nacelles on longitudinal aerodynamic characteristics of a high-wing transport airplane / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1990), by William Kelly Abeyounis, James C. Patterson, and Langley Research Center (page images at HathiTrust)
• Deployment and performance characteristics of 1.5-meter supersonic attached inflatable decelerators / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Herman L. Bohon, Robert Miserentino, James Wayne Sawyer, and Langley Research Center (page images at HathiTrust)
• Spray drag of surface-piercing struts / (San Diego, Calif. : Naval Undersea Research and Development Center, 1971), by Richard B Chapman and Naval Undersea Research and Development Center (page images at HathiTrust)
• Drag measurements on a laminar-flow body of revolution in the 13-inch magnetic suspension and balance system / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1989), by David A. Dress (page images at HathiTrust)
• A closed-form trim solution yielding minimum trim drag for airplanes with multiple longitudinal-control effectors / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1989), by Kenneth H. Goodrich, Frederick J. Lallman, and Steven M. Sliwa (page images at HathiTrust)
• NASA supercritical airfoils : a matrix of family-related airfoils / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1990), by Charles D. Harris and Langley Research Center (page images at HathiTrust)
• Flight and wind-tunnel measurements showing base drag reduction provided by a trailing disk for high Reynolds number turbulent flow for subsonic and transonic Mach numbers / (Washington, DC : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1986), by Sheryll Goecke Powers, Charles H. Fox, Jarrett K. Huffman, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Investigation at Mach numbers of 0.20 to 3.50 of blended wing-body combinations of sonic design with diamond, delta and arrow plan forms / (Washington [D.C.] : National Aeronautics and Space Administration, [1960]), by George H. Holdaway, Jack A. Mellenthin, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Free-flight measurments [i.e. measurements] of static and dynamic stability of models of the Project Mercury re-entry capsule at Mach numbers 3 and 9.5 / (Washington [D.C.] : National Aeronautics and Space Administration, [1960]), by Simon C. Sommer, Dale L. Compton, Barbara J. Short, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Evaluation of blended wing-body combinations with curved plan forms at Mach numbers up to 3.50 / (Washington [D.C.] : National Aeronautics and Space Administration, [1960]), by George H. Holdaway, Jack A. Mellenthin, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Ordinates and theoretical pressure-distribution data for NACA 6- and 6A-series airfoil sections with thicknesses from 2 to 21 and from 2 to 15 percent chord, respectively / ([Washington, D.C., U.S. G.P.O., 1961), by Elizabeth W. Patterson, Albert L. Braslow, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Analysis of various descent trajectories for a hypersonic-cruise, cold-wall research airplane / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Pierce L. Lawing and Langley Research Center (page images at HathiTrust)
• Dynamics and column densities of small particles ejected from spacecraft / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by National Technical Information Service], 1974), by Robert J. Naumann and George C. Marshall Space Flight Center. Space Sciences Laboratory (page images at HathiTrust)
• Aerodynamic characteristics of three slender sharp-edge 74 ̊swept wings at subsonic, transonic, and supersonic Mach numbers / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Edwin E. Davenport and Langley Research Center (page images at HathiTrust)
• Effect of afterbody terminal fairings on the performance of a pylon-mounted turbojet-nacelle model / (Washington [D.C.] : National Aeronautics and Space Administration, [1960]), by Conrad M. Willis, Charles E. Mercer, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Low-speed free-flight stability and drag characteristics of radially vented parachutes / (Washington, D.C. : NASA : For sale by the Office of Technical Services, Dept. of Commerce, 1964), by Sanger M. Burk, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Drag of a supercritical body of revolution in free flight at transonic speeds and comparison with wind-tunnel data / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971), by J. W. Usry, John W. Wallace, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Dynamics of high-drag probe shapes at transonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, 1971), by Robert I. Sammonds, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• Correlation of full-scale drag predictions with flight measurements on the C-141A aircraft : phase II, wind tunnel test, analysis, and prediction techniques / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by D. G. MacWilkinson, J. H. Paterson, W. T. Blackerby, Langley Research Center, and Lockheed-Georgia Company (page images at HathiTrust)
• Flight-measured base pressure coefficients for thick boundary-layer flow over an aft-facing step for Mach numbers from 0.4 to 2.5 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Sheryll A. Goecke and Flight Research Center (U.S.) (page images at HathiTrust)
• Interference between exhaust system and afterbody of twin-engine fuselage configurations / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Jack F. Runckel and Langley Research Center (page images at HathiTrust)
• Effects of canopy shape on low-speed aerodynamic characteristics of a 55⁰ swept parawing with large-diameter leading edges / (Washington, D.C. : NASA : For sale by the Office of Technical Services, Dept. of Commerce, 1964), by Delwin R. Croom, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effects of body shape on the aerodynamic characteristics of an all-body hypersonic aircraft configuration at Mach numbers from 0.65 to 10.6 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by Walter P. Nelms and Ames Research Center (page images at HathiTrust)
• Experimental determination of pressure drop and flow characteristics of dilute gas-solid suspensions / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1971), by Robert Pfeffer, Salvatore J. Rossetti, Lewis Research Center, and City University of New York. City College (page images at HathiTrust)
• Drag coefficients for spheres in free molecular flow in O at satellite velocities / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by John W. Boring, Robert R. Humphris, Langley Research Center, and University of Virginia (page images at HathiTrust)
• Heat transfer coefficients of dilute flowing gas-solids suspensions / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Ronald S. Kane, Robert Pfeffer, Lewis Research Center, and City University of New York (page images at HathiTrust)
• Drag and stability characteristics of a variety of reefed and unreefed parachute configurations at Mach 1.80 with an empirical correlation for supersonic Mach numbers / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Lana M. Couch and Langley Research Center (page images at HathiTrust)
• Jet effects on the drag of conical afterbodies at spersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by William B. Compton and Langley Research Center (page images at HathiTrust)
• Longitudinal aerodynamic characteristics of light, twin-engine, propeller-driven airplanes / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by Chester H. Wolowicz, Roxanah B. Yancey, and Flight Research Center (U.S.) (page images at HathiTrust)
• Effect of fineness ratio on boattail drag of circular-arc afterbodies having closure ratios of 0.50 with jet exhaust at Mach numbers up to 1.30 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by David E. Reubush, Jack F. Runckel, and Langley Research Center (page images at HathiTrust)
• Effects of fineness and closure ratios on boattail drag of circular-arc afterbody models with jet exhaust at Mach numbers up to 1.3 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by David E. Reubush and Langley Research Center (page images at HathiTrust)
• Effect of blockage ratio on drag and pressure distributions for bodies of revolution at transonic speeds (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Lana M. Couch, Cuyler W. Brooks, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Performance of a Mach Number 3.0 design axisymmetric double-cone external-compression inlet in the mach number range 1.97 to 0.79 / (Washington, D.C. : National Aeronautics and Space Administration, 1960), by Owen H. Davis, Glenn A. Mitchell, and Lewis Research Center (page images at HathiTrust)
• An analytical evaluation of airfoil sections for helicopter rotor applications / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Gene J. Bingham and Langley Research Center (page images at HathiTrust)
• An analytical study of the effects of jets located more than one jet diameter above a wing at subsonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Lawrence E. Putnam and Langley Research Center (page images at HathiTrust)
• Numerical methods for the design and analysis of wings at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Harry W. Carlson, David S. Miller, and Langley Research Center (page images at HathiTrust)
• Boundary-layer transition and displacement-thickness effects on zero-lift drag of a series of power-law bodies at Mach 6 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by George C. Ashby, Julius E. Harris, and Langley Research Center (page images at HathiTrust)
• Investigation of new radar-data-reduction techniques used to determine drag characteristics of a free-flight vehicle / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Gerard E. Woodbury, John W. Wallace, and Langley Research Center (page images at HathiTrust)
• Sweep effect on the drag of rows of perpendicular circular cylinders in a laminar boundary layer at supersonic free-stream velocities / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Milton Lamb, Robert L. Stallings, and Langley Research Center (page images at HathiTrust)
• Aerodynamic drag and fuel spreading measurements in a simulated scramjet combustion module / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Louis A. Povinelli and Lewis Research Center (page images at HathiTrust)
• Effects of nozzle interfairing modifications on longitudinal aerodynamic characteristics of a twin-jet, variable-wing-sweep fighter model / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by David E. Reubush, Charles E. Mercer, and Langley Research Center (page images at HathiTrust)
• The effects of winglets on low aspect ratio wings at supersonic Mach numbers / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ; Springfield, Va. : For sale by the National Technical Information Service, 1991), by James A. Keenan, John Kuhlman, Langley Research Center, and West Virginia University. Dept. of Mechanical and Aerospace Engineering (page images at HathiTrust)
• Drag of two-dimensional small-amplitude symmetric and asymmetric wavy walls in turbulent boundary layers / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1984), by John C. Lin, R. Balasubramanian, Michael J. Walsh, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• An exploratory wind-tunnel investigation of the wake effect of a panel tip-mounted fan-jet engine on the lift-induced vortex / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1970), by James C. Patterson, Stuart G. Flechner, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Experimental study of the effectiveness of cylindrical plume simulators for predicting jet-on boattail drag at Mach numberes up to 1.30 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by David E. Reubush and Lanlgely Research Center (page images at HathiTrust)
• Determinations of aerodynamic-drag parameters of small irregular objects by means of drop tests / (Oak Ridge, Tenn. : U.S. Atomic Energy Commission, Division of Technical Information Extension, [1961]), by E. Royce Fletcher and U.S. Atomic Energy Commission. Civil Effects Test Operations (page images at HathiTrust)
• Zero-lift drag of a series of bomb shapes at mach numbers from .60 to 1.10 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1956), by William E. Stoney, John Royall, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust; US access only)
• Economics of railroad automobile rack car aerodynamic drag / (Washington, Engineering, Research, and Development Division, Office of High Speed Ground Transportation, Federal Railroad Administration, U.S. Dept. of Transportation, 1969), by Robert W. Luebke and Research United States. Office of High-Speed Ground Transportation. Engineering (page images at HathiTrust)
• An experimental investigation of dynamic ground effect / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division, 1987), by Pai Hung Lee, Vincent U. Muirhead, C. Edward Lan, and Langley Research Center (page images at HathiTrust)
• Determination of the profile drag of an airplane wing in flight at high Reynolds numbers /, by Joseph Bicknell and Langley Aeronautical Laboratory (page images at HathiTrust)
• Flight determination of drag of normal-shock nose inlets with various cowling profiles at mach numbers from 0.9 to 1.5 / (Washington, D.C. : U.S. Government Printing Office, 1956), by R. I. Sears, L. W. Putland, C. F. Merlet, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Drag due to lift of a not-so-slender configuration; application of theory. (Buffalo, Cornell Aeronautical Laboratory, Inc., 1958), by Robert J. Vidal (page images at HathiTrust)
• Reduction of drag due to lift at supersonic speeds (Wright-Patterson Air Force Base, Ohio, Wright Air Development Center, Air Research and Development Command, U. S. Air Force, 1954 [i. e. 1955]), by Douglas Aircraft Company and E. W. Graham (page images at HathiTrust)
• Hydrodynamic drag measurements on SWATH ship components / (San Diego, Calif. : Naval Undersea Center, 1974), by R. B. Chapman and Naval Undersea Center (page images at HathiTrust; US access only)
• Investigation of opening characteristics of an all-flexible parawing / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information], 1968), by Thomas G. Gainer, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Application of Brouwer's artificial-satellite theory to computation of the state transition matrix / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by George H. Born, James C. Kirkpatrick, Manned Spacecraft Center (U.S.), and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Effect of jet velocity and axial location of nozzle exit on the performance of a twin-jet afterbody model at Mach numbers up to 2.2 / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 20230], 1969), by Bobbly Lee Berrier, Frederick H. Wood, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Real-gas effects on the drag and trajectories of a nonlifting 140° conical aeroshell during Mars entry / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971), by Dennis O. Allison, Percy J. Bobbitt, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Comparison of wind-tunnel and flight-measured base pressures from the sharp-leading-edge upper vertical fin of the X-15 airplane for turbulent flow at Mach numbers from 1.5 to 5.0 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971), by Sheryll Goecke Powers, Flight Research Center (U.S.), and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Aerodynamic characteristics of a monoplanar missile concept with bodies of circular and elliptical cross sections / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Office, 1977), by Ernald B. Graves and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust; US access only)
• Aerodynamic forces on a stationary and oscillating circular cylinder at high Reynolds numbers / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1969), by George W. Jones, Robert W. Walker, Joseph J. Cincotta, George C. Marshall Space Flight Center, Martin Company, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Lift and drag characteristics of the HL-10 lifting body during subsonic gliding flight / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971), by Jon S. Pyle, Flight Research Center (U.S.), and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• On the second-order solution of artificial satellite theory without air drag / (Washington, D.C. : National Aeronautics and Space Administration, 1964), by Theodore L. Felsentreger, Goddard Space Flight Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• The problem of roughness drag at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 2215], 1966), by K. R. Czarnecki, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• The slow motion of a permanently magnetized sphere in an electrically conducting medium, ([Lafayette, Ind., Purdue University, School of Aeronautical Engineering, [1959]), by James R. Barthel and P. S. Lykoudis (page images at HathiTrust)
• On the use of impact theory for slender configurations exhibiting flow separation / (Palo Alto, Calif. : Vidya, a division of Itek Corp., 1963), by Alvin Howard Sacks and Jack A Burnell (page images at HathiTrust)
• Effects of installation of F101 DFE exhaust nozzles on the afterbody-nozzle characteristics of the F-14 airplane / (Washington, D.C. : U.S. National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va., : For sale by the National Technical Information Service], 1982), by David E. Reubush, John R. Carlson, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Drag reduction obtained by modifying a standard truck / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Arthur E. Sheridan, Steven J. Grier, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Flight-measured pressure characteristics of aft-facing steps in high Reyonlds number flow at Mach numbers of 2.20, 2.50, and 2.80 and comparison with other data / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Office, 1978), by Sheryll Goecke Powers and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Truncated cone in supersonic flight at zero angle of attack : surface pressure coefficients, drag coefficients, and shock front configurations / (Urbana, Ill. : Mechanical Engineering Dept., Engineering Experiment Station, University of Illinois, Jan. 1960), by W. L. Chow, C.C. Tsung, Helmut Hans Korst, and University of Illinois (Urbana-Champaign campus). Engineering Experiment Station (page images at HathiTrust; US access only)
• A computational model for the prediction of jet entrainment in the vicinity of nozzle boattails (The BOAT code) / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Service ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Sanford M. Dash, Harold S. Pergament, Aeronautical Research Associates of Princeton, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Summary of studies to reduce wing-mounted propfan installation drag on an M = 0.8 transport / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by Ronald C. Smith, Richard D. Wood, Alan D. Levin, and Ames Research Center (page images at HathiTrust)
• Effects of afterbody boattail design and empennage arrangement on aeropropulsive characteristics of a twin-engine fighter model at transonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service,), by Linda S. Bangert, David E. Reubush, Laurence D. Leavitt, and Langley Research Center (page images at HathiTrust)
• Effect of a trade between boattail angle and wedge size on the performance of a nonaxisymmetric wedge nozzle / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by George T. Carson, James R. Burley, E. Ann Bare, and Langley Research Center (page images at HathiTrust)
• Evaluation of installed performance of a wing-tip-mounted pusher turboprop on a semispan wing / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by James C. Patterson, Glynn R. Bartlett, and Langley Research Center (page images at HathiTrust)
• Drag measurements of blunt stores tangentially mounted on a flat plate at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by Floyd J. Wilcox and Langley Research Center (page images at HathiTrust)
• Planform effects on the supersonic aerodynamics of multibody configurations / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by S. Naomi McMillin, Richard M. Wood, and Langley Research Center (page images at HathiTrust)
• An economical semi-analytical orbit theory for microcomputer applications / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service,), by R. A. Gordon and Goddard Space Flight Center (page images at HathiTrust)
• Influence of base modifications on in-flight base drag in the presence of jet exhaust for Mach numbers from 0.7 to 1.5 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1988), by Sheryll Goecke Powers and Ames Research Center (page images at HathiTrust)
• The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil : design overview / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service,), by Charles D. Harris, Cuyler W. Brooks, William D. Harvey, and Langley Research Center (page images at HathiTrust)
• Flight Reynolds number effects on a contoured boattail nozzle at subsonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Roger Chamberlin and Lewis Research Center (page images at HathiTrust)
• Structural performance of two aerobrake hexagonal heat shield panel concepts / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by John T. Dorsey, James W. Dyess, and Langley Research Center (page images at HathiTrust)
• Effect of several airframe/nozzle modifications on the drag of a variable-sweep bomber configuration / (Washington, D.C. : National Aeronautics and Space Administrat ion, Scientific and Technical Information Branch ; [Springfield, Va. : Fo r sale by the National Technical Information Service], 1979), by Richard J. Re, David E. Reubush, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Exhaust-nozzle characteristics for a twin-jet variable-wing-sweep fighter airplane model at Mach numbers to 2.2 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by David E. Reubush, Charles E. Mercer, and Langley Research Center (page images at HathiTrust)
• Longitudinal aerodynamic performance of a series of power-law and minimum-wave-drag bodies at Mach 6 and several Reynolds numbers / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by George C. Ashby and Langley Research Center (page images at HathiTrust)
• Exploratory wind-tunnel investigation of a wingtip-mounted vortex turbine for vortex energy recovery / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1985), by James C. Patterson, Stuart G. Flechner, and Langley Research Center (page images at HathiTrust)
• Transonic off-design drag and performance of an axisymmetric inlet with 40 percent internal contraction on design / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by Richard R. Woollett, David A. Choby, Edward T. Meleason, and Lewis Research Center (page images at HathiTrust)
• The natural flow wing-design concept / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Richard M. Wood, Steven X. S. Bauer, and Langley Research Center (page images at HathiTrust)
• Flight Reynolds number effects on a fighter-type, circular-arc - 19 ̊conic boattail nozzle at subsonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Roger Chamberlin and Lewis Research Center (page images at HathiTrust)
• Experimental evaluation of compliant surfaces at low speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Kenneth W. McAlister, Tom M. Wynn, U.S. Army Air Mobility Research and Development Laboratory, and Ames Research Center (page images at HathiTrust)
• Transonic off-design drag and performance of three mixed-compression axisymmetric inlets / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Richard R. Woollett, David A. Choby, Edward T. Meleason, and Lewis Research Center (page images at HathiTrust)
• The NASA Langley laminar-flow-control experiment on a swept supercritical airfoil : basic results for slotted configuration / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1989), by Charles D. Harris (page images at HathiTrust)
• Effects of wing leading-edge flap deflections on subsonic longitudinal aerodynamic characteristics of a wing-fuselage configuration with a 44 ̊swept wing / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by William P. Henderson, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Computation of transonic boattail flow with separation / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Richard G. Wilmoth and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Improved tangent-cone method for the Aerodynamic Preliminary Analysis System (APAS) version of the Hypersonic Arbitrary-Body Program / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1990), by Christopher I. Cruz, Gregory J. Sova, and Langley Research Center (page images at HathiTrust)
• Effects of roughness size on the position of boundary-layer transition and on the aerodynamics characteristics of a 55 ̊swept delta wing at supersonic speeds / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Robert L. Stallings, Milton Lamb, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Effects of forward contour modification on the aerodynamic characteristics of the NACA 64₁-212 airfoil section / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by R. M. Hicks, Angelo Bandettini, Joel P. Mendoza, and Ames Research Center (page images at HathiTrust)
• An experimental and analytical study of the aerodynamic interference effects between two Sears-Haack bodies at Mach 2.7 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1985), by Jeffrey W. Bantle and Langley Research Center (page images at HathiTrust)
• Determination of the hypersonic-continuum/rarefield-flow drag coefficient of the Viking Lander Capsule 1 aeroshell from flight data / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by Robert C. Blanchard, Gerald D. Walberg, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Experimental investigation of porous-floor effects on cavity flow fields at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1990), by Floyd J. Wilcox and Langley Research Center (page images at HathiTrust)
• Subsonic sphere drag measurements at intermediate Reynolds numbers / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1969), by Kenneth R. Sivier, J. A. Nicholls, University of Michigan. Dept. of Aerospace Engineering, and Lewis Research Center (page images at HathiTrust)
• Experimental investigation of magnetoaerodynamic flow around blunt bodies / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1969), by S. Kranc, A. B. Cambel, M. C. Yuen, and Ill.) Northwestern University (Evanston (page images at HathiTrust)
• Theoretical and experimental study of a new method for prediction of profile drag of airfoil sections / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1975]), by Suresh H. Goradia, D. G. Lilley, Langley Research Center, and Lockheed-Georgia Company (page images at HathiTrust)
• The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil : drag euqations / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1989), by Cuyler W. Brooks, William D. Harvey, and Charles D. Harris (page images at HathiTrust)
• Prediction of compliant wall drag reduction, part I / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Steven A. Orszag, inc Cambridge Hydrodynamics, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• On the theory of compliant wall drag reduction in turbulent boundary layers / (Washington, D.C. : National Aeronautics and Space Administration, 1974), by Robert L. Ash, Langley Research Center, and Old Dominion University (page images at HathiTrust)
• Dynamic response of some tentative compliant wall structures to convected trubulence fields / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by H. H. Nijim, Y. K. Lin, University of Illinois at Urbana-Champaign, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• An analysis of flight test data on the C-141A aircraft / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1970), by J. H. Paterson, Langley Research Center, and Lockheed-Georgia Company (page images at HathiTrust)
• An improved analytical model of the separation region on boattail nozzles at subsonic speeds / (Washington : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Walter M. Presz, John D. Buteau, Ronald W. King, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• A unified viscous theory of lift and drag of 2-D thin airfoils and 3-D thin wings / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ; Springfield, Va. : For sale by the National Technical Information Service, 1991), by John E. Yates and Titan Corporation. California Research & Technology Division. A.R.A.P. Group (page images at HathiTrust)
• A nonlinear structural concept for compliant walls / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1982), by Edward L. Reiss, Applied Institute of Mathematics, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
• Minimization theory of induced drag subject to constraint conditions / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by John DeYoung, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• The theory of induced lift and minimum induced drag of nonplanar lifting systems / (Washington, D. C. : National Aeronautics and Space Administration ; Springfield, Va. : for sale by the Clearinghouse for Federal Scientific and Technical Information, 1962), by Clarence D. Cone and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Transition fixing for hypersonic flow / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1967]), by James R. Sterrett and Langley Research Center (page images at HathiTrust)
• Drag characteristics of several towed decelerator models at Mach 3 [electronic resource] / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151], 1970), by Robert Miserentino, Herman L. Bohon, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• A study of the aerodynamic characteristics of a fixed geometry paraglider configuration and three canopies with simulated variable canopy inflation at a mach number of 6.6 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce], [1962]), by Jim A. Penland and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Deployment and performance characteristics of 5-foot-diameter (1.5 m) attached inflatable decelerators from Mach number 2.2 to 4.4 / (Washington, DC : National Aeronautics and Space Administration, 1970), by Herman L. Bohon, Robert Miserentino, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Aerodynamic characteristics of an all-body hypersonic aircraft configuration at Mach numbers from 0.65 to 10.6 / (Washington : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], 1971), by Walter P. Nelms, Charles L. Thomas, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Experimental stability and control results at Mach 19 of an entry vehicle designed for an intermediate lift-drag ratio / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1968]), by Patrick J. Johnston, Robert D. Witcofski, and Langley Research Center (page images at HathiTrust)
• Rocket trajectories, drag, and stability / (Washington, D.C. : National Aeronautics and Space Administration, 1968), by Roger W. Luidens and Lewis Research Center (page images at HathiTrust)
• Investigation of the aerodynamic characteristics of a supersonic horizontal- attitude VTOL airplane model at Mach numbers of 1.57, 2.14, 2.54, and 2.87 / (Washington, D.C. : National Aeronautics and Space Administration, 1960), by Arthur E. Franklin, Robert M. Lust, and Langley Research Center (page images at HathiTrust)
• Some measurements of the dynamic and static stability of two blunt-nosed, low-fineness-ratio bodies of revolution in free flight at M=4 / (Washington, D.C. : National Aeronautics and Space Administration, 1959), by Barbara J. Sort, Simon C. Sommer, and Ames Research Center (page images at HathiTrust)
• Induced pressures on cylindrical rods with various nose drags and nose shapes at mach numbers of 17 and 21 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, 1962]), by Robert D. Witcofski, Arthur Henderson, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Some requirements of electric and chemical thrust systems for space station drag cancellations / (Washington, D.C. : National Aeronautics and Space Administration : For sale by the Office of Technical Services, Dept. of Commerce, [1964]), by Dennis W. Brown and Lewis Research Center (page images at HathiTrust)
• Drag coefficients for partially inflated flat circular parachutes / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971), by Stanley H. Scher, Irene G. Young, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Installation effects of wing-mounted turbofan nacelle-pylons on a 1/17 scale, twin-engine, low-wing transport model / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Odis C. Pendergraft and Langley Research Center (page images at HathiTrust)
• The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil : suction coefficient analysis / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ; Springfield, Va. : For sale by the National Technical Information Service, 1991), by Cuyler W. Brooks, William D. Harvey, Charles D. Harris, and Langley Research Center (page images at HathiTrust)
• F-8 supercritical wing flight pressure, boundary-layer, and wake measurements and comparisons with wind tunnel data / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Lawrence C. Montoya, Richard D. Banner, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Drag and distribution measurements of single-element fuel injectors for supersonic combustors / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Louis A. Povinelli and Lewis Research Center (page images at HathiTrust)
• An experimental and theoretical investigation of the effect of nonmetric over-the-wing nacelles on wing-body aerodynamics / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1979), by David E. Reubush and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Measurement of non-continuum and turbulence effects on subsonic sphere drag / (Washington, D.C. : National Aeronautics and Space Administration, [1970]), by Neil A. Zarin, University of Michigan, and Lewis Research Center (page images at HathiTrust)
• Prediction of compliant wall drag reduction, part II / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1979), by Steven A. Orszag, inc Cambridge Hydrodynamics, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Induced drag ideal efficiency factor of arbitrary lateral-vertical wing forms / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by John DeYoung, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Modification in drag of turbulent boundary layers resulting from manipulation of large-scale structures / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by T. C. Corke, Hassan M. Nagib, Y. Guezennec, Illinois Institute of Technology, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
• Combined linear theory/impact theory for analysis and design of high speed configurations / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1980), by D. Brooke, Langley Research Center, McDonnell Aircraft Company, and D. V. Vondrasek (page images at HathiTrust)
• Numerical optimization techniques for bound circulation distribution for minimum induces drag of nonplanar wings : basic formulations (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by John Kuhlman, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Analytical and design techniques for drag reduction studies on wavy surfaces / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Services], 1980), by R. Balasubramanian, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Theoretical/numerical study of feasibility of use of winglets on low aspect ratio wings at subsonic and transonic Mach numbers to reduce drag / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division ; [Springfield, Va. : For sale by the National Technical Information Service], 1988), by John Kuhlmann, Michael J. Cerney, Paul Liaw, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division (page images at HathiTrust)
• Extension of leading-edge-suction analogy to wings with separated flow around the side edges at subsonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by John E. Lamar and Langley Research Center (page images at HathiTrust)
• Effects of jet exhaust gas properties on exhaust simulation and afterbody drag / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by William B. Compton and Langley Research Center (page images at HathiTrust)
• Static longitudinal aerodynamic characteristics of some supersonic decelerator models at Mach numbers of 2.30 and 4.63 / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151], 1969), by Edwin E. Davenport, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effects of lee-surface volume addition on longitudinal aerodynamics of a high-lift-drag-ratio wing-body configuration at Mach 6.0 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1968), by David R. Stone, George C. Ashby, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Inflation and performance of three parachute configurations from supersonic flight tests in a low-density environment / (Washington, D.C. : NASA, 1969), by Charles H. Whitlock, Richard J. Bendura, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Effect of nonlifting empennage surfaces on single-engine afterbody/nozzle drag at Mach numbers from 0.5 to 2.2 / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Bobby L. Berrier and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effect of Reynolds number on the subsonic boattail drag of several wing-body configurations / (Washington : U.S. National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by David E. Reubush, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Some anomalies observed in wind-tunnel tests of a blunt body at transonic and supersonic speeds / (Washington : National Aeronautics and Space Administration ; Springfield, Va. for sale by the National Technical Information Service, 1976), by Joseph D. Brooks, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• A high subsonic speed wind-tunnel investigation of winglets on a representative second-generation jet transport wing / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by Stuart G. Flechner, Richard T. Whitcomb, Peter F. Jacobs, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Bodies of revolution having minimum total drag in hypersonic flow / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va. 22151], 1969), by Waldo I. Oehman, Sylvia A. Wallace, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• An experimental and analytical investigation of the effect on isolated boattail drag of varying Reynolds number up to 130 x 106 / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by David E. Reubush, Lawrence E. Putnam, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• A design approach and selected wind-tunnel results at high subsonic speeds for wing-tip mounted winglets / (Washington : National Aeronautics and Space Administration ; Springfield, Va. for sale by the National Technical Information Service, 1976), by Richard T. Whitcomb, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Application of the leading-edge-suction analogy of vortex lift to the drag due to lift of sharp-edge delta wings / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1968), by Edward C. Polhamus, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Boundary-layer velocity profiles downstream of three-dimensional transition trips on a flat plate at Mach 3 and 4 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1969]), by John B. Peterson, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Aerodynamic characteristics of an oblate spheroid and a sphere at Mach numbers from 1.70 to 10.49 / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by Lloyd S. Jernell, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• An approximate solution of additive-drag coefficient and mass-flow ratio for inlets utilizing right circular cones at zero angle of attack / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Vincent R. Mascitti, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Flow-field and drag characteristics of several boundary-layer tripping elements in hypersonic flow / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va. 22151], 1969), by Allen H. Whitehead, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Fan and wing force data from wind-tunnel investgation of a 0.38-meter (15-IN.) diameter VTOL model lift fan installed in a two-dimensional wing / (Washington, DC : National Aeronautics and Space Administration, 1972), by Joseph A. Yuska, James H. Diedrich, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Calculated pressure distributions and components of total-drag coefficients for 18 constant-volume slender bodies of revolution at zero incidence for Mach numbers from 2.0 to 12.0, with experimental aerodynamic characteristics for three of the bodies / (Washington, D.C. : National Aeronautics and Space Administration, 1971), by Louis S. Stiver, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• Investigation of the flow over a spiked-nose hemisphere-cylinder at a Mach number of 6.8 / (Washington : National Aeronautics and Space Administration, [1959]), by Davis H. Crawford and Langley Research Center (page images at HathiTrust)
• Vaporization rates of ethanol sprays in a combustor with low-frequency fluctuations of combustion-gas pressure / Robert D. Ingebo. (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce], [1962]), by Robert D. Ingebo and United States National Aeronautics and Space Administration (page images at HathiTrust)
• The aerodynamic design of wings with cambered span having minimum induced drag / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1963), by Clarence D. Cone, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Definition of lateral-range and lift-drag-ratio requirements for return to both optimum and nonoptiumum recovery sites / (Washington, D.C. : National Aeronautics and Space Administration, 1966), by Paul F. Holloway and E. Brian Pritchard (page images at HathiTrust; US access only)
• Afterbody pressures on two-dimensional boattailed bodies having turbulent boundary layers at Mach 5.98 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1964), by W. Frank Staylor, Theodore J. Goldberg, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Evaluation of boundary-layer and wake-survey data-reduction techniques in compressible flows / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1968), by K. R. Czarnecki, Russell B. Sorrells, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• A method for determining the total drag of a pointed body of revolution in supersonic flow with turbulent boundary layer / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Charlie M. Jackson, Rudeen S. Smith, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Prediction of lift and drag for slender sharp-edge delta wings in ground proximity / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Charles H. Fox, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Shock tube determination of the drag coefficient of small spherical particles / (Washington, D.C. : National Aeronautics and Space Administration, 1966), by Bruce P. Selberg (page images at HathiTrust; US access only)
• Characteristics of dilute gas-solids suspensions in drag reducing flow / (Washington, D.C. : National Aeronautics and Space Administration, 1973), by Ronald Steven Kane (page images at HathiTrust; US access only)
• Magnetic field properties related to the design of a one-component magnetic support-and-balance system / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by K. R. Sivier, University of Michigan, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• One component, magnetic, support and balance system for wind tunnel models / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by K. R. Sivier, M. Henderson, University of Michigan, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Further experimental investigations of delta and double-delta wing flow fields at low speeds / (Washington, D.C. : National Aeronautics and Space Administration, 1967), by William H. Wentz and Michael C. McMahon (page images at HathiTrust; US access only)
• Drag associated with separated flow over two-dimensional V-shaped notches under transonic and supersonic conditions / (Washington, D.C. : National Aeronautics and Space Administration, 1968), by Ronald H. Howell and Helmut H. Korst (page images at HathiTrust; US access only)
• The flutter of towed rigid decelerators / (Washington, D.C. : National Aeronautics and Space Administration, 1967), by Richard H. MacNeal (page images at HathiTrust; US access only)
• Exploratory investigation of the effect of a forward-facing jet on the bow shock of a blunt body in a Mach number 6 free stream / (Washington, D.C. : National Aeronautics and Space Administration, 1963), by David J. Romeo, James R. Sterrett, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• The effect of a rotating cylinder at the leading and trailing edges of a hydrofoil / (China Lake, Calif. : U.S. Naval Ordnance Test Station, [1963]), by John D Brooks and Calif.) Naval Ordnance Test Station (China Lake (page images at HathiTrust; US access only)
• Divergence of some all-movable control surfaces including drag loadings / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1968), by Robert C. Goetz, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Effect on base drag of recessing the bases of conical afterbodies at subsonic and transonic speeds / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia], 1968), by William B. Compton, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust; US access only)
• A wind-tunnel investigation of jet-wake effect of a high-bypass engine on wing-nacelle interference drag of a subsonic transport / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1968), by James C. Patterson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Polymer injection for drag reduction / ([Bethesda, Md.] : Naval Ship Research and Development Center, 1972), by J. Paul Tullis, Lance F. Lindeman, and Naval Ship Research and Development Center (page images at HathiTrust)
• Airfoil theory at supersonic speed / (Washington, D.C. : National Advisory Committee for Aeronautics, 1939), by H. Schlichting and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Drag due to lift of a not-so-slender configuration /, by Hsien K. Cheng, United States. Air Force. Air Research and Development Command. sponsor, Inc Cornell Aeronautical Laboratory, and Wright Air Development Center (page images at HathiTrust)
• Aerodynamic characteristics of a wing with quarter-chord line swept back 35©�, aspect ratio 6, taper ratio 0.6, and NACA 65A006 airfoil section. Transonic-bump method / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by William C. Sleeman, William D. Morrison, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Transonic flight tests to compare the zero-lift drag on underslung and symmetrical nacelles varied chordwise at 40 percent semispan of a 45©� sweptback, tapered wing / (Washington, D.C. : National Advisory Committee for Aeronautics, 1950), by William B. Pepper, Sherwood Hoffman, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Large-scale flight measurements of zero-lift drag and low-lift drag of 10 wing-body configurations at Mach numbers from 0.8 to 1.6 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by John D. Morrow, Robert L. Nelson, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• A note on the drag due to lift of delta wings at Mach numbers up to 2.0 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by Robert S. Osborne, Thomas C. Kelly, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Some effects of external wing tip stores on the rolling effectiveness and drag of plain and half-delta tip ailerons on a 4-percent-thick tapered, unswept wing / (Washington, D.C. : National Advisory Committee for Aeronautics, 1954), by Roland D. English, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Flight determination of drag and pressure recovery of two scoop inlets located at maximum-body-diameter station at Mach numbers from 0.8 to 1.8 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1955), by Leonard W. Putland, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Factors affecting the maximum lift-drag ratio at high supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1956), by Charles H. McLellan, Robert W. Dunning, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Effect of convergent ejector nozzles on the boattail drag of a 16©� conical afterbody at Mach number of 0.6 to 1.26 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1958), by James M. Cubbage, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Drag due to lift at Mach numbers up to 2.0 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by Edward C. Polhamus, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Linearized lifting-surface theory for swept-back wings with slender plan forms / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by Harvard Lomax, Max A. Heaslet, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Average skin-friction drag coefficients from tank tests of a parabolic body of revolution (NACA RM-10) / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by Elmo J. Mottard, J. Dan Loposer, 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 / (Washington, D.C. : National Advisory Committee for Aeronautics, [1957]), by Allen B. Henning and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Test of NACA 66,2-116, a = 0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane / (Washington, D.C. : 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)
• The drag properties of several winged and finned cone-cylinder models /, by Leonard C. MacAllister, E. J. Roschke, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Drag of several surface protrusion patterns at M = 5.0 /, by John A. Darling and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Flight techniques for determining airplane drag at high Mach numbers / (Washington, D.C. : National Advisory Committee for Aeronautics, [1956]), by De E. Beeler, Edwin J. Saltzman, Donald R. Bellman, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation of the effects of leading-edge chord-extensions and fences in combination with leading-edge flaps on the aerodynamic characteristics at Mach numbers of 0.40 to 0.93 of a 45©� sweptback wing of aspect ratio 4 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1957), by Kenneth P. Spreemann, William J. Alford, Langley Aeronautical Laboratory, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Altitude-wind-tunnel investigation of a 4000-pound-thrust axial-flow turbojet engine (Washington, D.C. : National Advisory Committee for Aeronautics, [1948]), by William A. Fleming, United States. National Advisory Committee for Aeronautics. NACA research memorandum, and Flight Propulsion Research Laboratory (page images at HathiTrust)
• Drag measurements at transonic speeds of two bodies of fineness ratio 9 with different locations of maximum body diameter / (Washington, D.C. : National Advisory Committee for Aeronautics, 1948), by Jim Rogers Thompson, Max C. Kurbjun, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Estimation of lift and drag of airfoils at near sonic speeds and in the presence of detached shock waves / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by John P. Mayer, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (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 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by William C. Sleeman, Robert E. Becht, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, 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 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1950), by John D. Morrow, Ellis Katz, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Flight determination of the drag and pressure recovery of an NACA 1-40-250 nose inlet at Mach numbers from 0.9 to 1.8 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1951), by R. I. Sears, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Transonic flight tests to determine the effect of thickness ratio and plan-form modification on the zero-lift drag of a 45©� sweptback wing / (Washington, D.C. : National Advisory Committee for Aeronautics, 1952), by William B. Pepper, Sherwood Hoffman, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Investigation of the variation with Reynolds number of the base, wave, and skin-friction drag of a parabolic body of revolution (NACA RM-10) at Mach numbers of 1.62, 1.93, and 2.41 in the Langley 9-inch supersonic tunnel / (Washington, D.C. : National Advisory Committee for Aeronautics, 1952), by Eugene S. Love, August F. Bromm, Donald E. Coletti, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Flight investigation of the zero-lift drag of two ram-jet missile configurations at Mach numbers from 1.0 to 1.89 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by Clarence A. Brown, Walter E. Bressette, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Investigation of the drag of blunt-nosed bodies of revolution in free flight at Mach numbers from 0.6 to 2.3 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by Harvey A. Wallskog, Roger G. Hart, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Investigation at supersonic speeds of the variation with Reynolds number and Mach number of the total, base, and skin-friction drag of seven boattail bodies of revolution designed for minimum wave drag / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by August F. Bromm, Julia M. Goodwin, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Effect of some section modifications and protuberances on the zero-lift drag of delta wings at transonic and supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1954), by Carl A. Sandahl, William E. Stoney, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Normal force, center of pressure, and zero-lift drag of several ballistic-type missiles at Mach numbers of 4.05 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1954), by Edward F. Ulmann, Robert W. Dunning, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Effects of some external-store mounting arrangements and store shapes on the buffet and drag characteristics of wingless rocket-powered models at Mach numbers from 0.7 to 1.4 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1954), by Homer P. Mason, Allen B. Henning, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• An experimental study of a method of designing the sweptback-wing - fuselage juncture for reducing the drag at transonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1955), by Robert R. Howell, Albert L. Braslow, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• A free-flight investigation of the effects of simulated sonic turbojet exhaust on the drag of a boattail body with various jet sizes from Mach number 0.87 to 1.50 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1955), by Ralph A. Falanga, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• A free-flight investigation of the drag coefficients of two single-engine supersonic interceptor configurations from Mach number 0.8 to 1.90 to determine the effect of inlet and engine locations / (Washington, D.C. : National Advisory Committee for Aeronautics, 1955), by Joseph H. Judd, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Lift, drag, and static longitudinal stability data from an exploratory investigation at a Mach number of 6.86 of an airplane configuration having a wing of trapezoidal plan form / (Washington, D.C. : National Advisory Committee for Aeronautics, 1955), by Jim A. Penland, David E. Fetterman, Herbert W. Ridyard, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil section. Transonic-bump method / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by Boyd C. Myers, Thomas J. King, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Flight investigation at high-subsonic, transonic, and supersonic speeds to determine zero-lift drag of fin-stabilized bodies of revolution having fineness ratios of 12.5, 8.91, and 6.04 and varying positions of maximum diameter / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by Roger G. Hart, Ellis R. Katz, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Aerodynamic investigation at Mach number 1.92 of a rectangular wing and tail and body configuration and Its components / (Washington, D.C. : National Advisory Committee for Aeronautics, XXXX), by Macon C. Ellis, Carl E. Grigsby, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Experimental investigation of the effects of support interference on the drag of bodies of revolution at a Mach number of 1.5 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1951), by Edward W. Perkins and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Concerning the flow about ring-shaped cowlings. Part 8 - Further measurements on annular profiles / (Washington, D.C. : National Advisory Commitee for Aeronautics ;, [1952]), by Dietrich K©·uchemann, Johanna Weber, and United States. National Advisory Commitee for Aeronautics (page images at HathiTrust)
• An investigation at transonic speeds of the effects of thickness ratio and of thickened root sections on the aerodynamic characteristics of wings with 47©� sweepback, aspect ratio 3.5, and taper ratio 0.2 in the slotted test section of the Langley 8-foot high-speed tunnel / (Washington, D.C. : National Advisory Committee for Aeronautics, [1951]), by Ralph P. Bielat, Domenic A. Coppolino, Daniel E. Harrison, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• An aerodynamic and hydrodynamic investigation of two multi-jet water-based aircraft having low transonic drag rise / (Washington, D.C. : National Advisory Committee for Aeronautics, 1955), by Roland E. Olson, Ralph P. Bielat, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• A free-flight investigation at high subsonic and low supersonic speeds of the rolling effectiveness and drag of three spoiler controls having potentially low actuating-force requirements / (Washington, D.C. : National Advisory Committee for Aeronautics, 1955), by Eugene D. Schult, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Effects of two leading-edge modifications on the aerodynamic characteristics of a thin low-aspect-ratio delta wing at transonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, [1956]), by John P. Mugler and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• An investigation of the drag characteristics of speed brakes for Mach numbers from 0.20 to 1.30 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1958), by Allan R. Vick, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Effect of wing-mounted external stores on the lift and drag of the Douglas D-558-II research airplane at transonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1957), by Jack Nugent, Flight Research Center (U.S.), and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• The proper combination of lift loadings for least drag on a supersonic wing / (Washington, D.C. : National Advisory Committee for Aeronautics, [1955]), by Frederick C. Grant and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Summary of drag coefficients of various shaped cylinders / (Cincinnati, Ohio : General Electric, Aircraft Nuclear Propulsion Dept., Atomic Products Division, Technical Publications Sub-Section ; Washington, D.C. : Available from the Office of Technical Services, U.S. Dept. of Commerce, 1957), by C. F. Heddleson, General Electric Company. Aircraft Nuclear Propulsion Department. Atomic Products Division, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Air flow tests of a narrow collector passage with eight transverse feeder slots (applicable to 140E1 forward shield design studies) / (Cincinnati, Ohio : General Electric, Nuclear Materials and Propulsion Operation., 1961), by R. W. Bell, U.S. Atomic Energy Commission, and General Electric Company (page images at HathiTrust)
• Lift and drag characteristics of a cabin monoplane determined in flight / (Washington D.C. : National Advisory Committee for Aeronautics ;, 1931), by F. L. Thompson, P. H. Keister, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Interference effects and drag of struts on a monoplae wing / (Washington D.C. : National Advisory Committee for Aeronautics ;, 1931), by Kenneth E. Ward and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• The Aerodynamic characteristics of three tapered airfoils tested in the Variable Density Wind Tunnel / (Washington D.C. : National Advisory Committee for Aeronautics ;, 1931), by Raymond F. Anderson and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• A summary of drag results from recent Langley full-scale-tunnel tests of Army and Navy airplanes / (Washington, D.C. : National Advisory Committee for Aeronautics, [1945]), by Roy H. Lange, Langley Aeronautical Laboratory, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Charts for estimation of the characteristics of a helicopter rotor in forward flight. 1 - Profile drag-lift ratio for untwisted rectangular blades / (Washington, D.C. : National Advisory Committee for Aeronautics, [1944]), by F. J. Bailey, F. B. Gustafson, Langley Aeronautical Laboratory, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• The effect of boattailing on the drag coefficient of cone-cylinder projectiles at supersonic velocities /, by Elizabeth R. Dickinson, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Design and testing of aerodynamic brakes for controlled lowering of heavy objects over long distances /, by R. B. Harvey, E. A. Lewis, C. B. Kalakowsky, R. P. Harrison, V. C. Fields, and Air Force Cambridge Research Laboratories (U.S.) (page images at HathiTrust)
• Factors affecting the vertical motion of a zero-pressure, polyethylene, free balloon /, by James F. Dwyer and U.S. Air Force Geophysics Laboratory. Aerospace Instrumentation Division (page images at HathiTrust)
• The drag of slightly blunted slender cones /, by W. Carson Lyons, H. S. Brown, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• The effect of base bleed on the drag and magnus characteristics of a rotating body of revolution /, by Frank J Regan, Virginia L. Schermerhorn, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Summary of static stability and drag characteristics of axisymmetric low-drag shapes for the subsonic to hypersonic mach number range /, by Amado A. Trujillo, U.S. Atomic Energy Commission, and Sandia Corporation (page images at HathiTrust)
• Temperature-step effects on direct measurement of skin-friction drag /, by Robert L. P. Voisinet and Naval Surface Weapons Center. White Oak Laboratory (page images at HathiTrust)
• Integrated instruments : a drag indicator /, by Malcolm L. Ritchie, sponsor United States. Air Force. Air Research and Development Command, Wright Air Development Center, Aerospace Medical Laboratory (U.S.), and University of Illinois at Urbana-Champaign (page images at HathiTrust)
• Mass injection and jet flow simulation effects on transonic afterbody drag /, by Wladimiro Calarese, Ronald E. Walterick, issuing body United States. Air Force. Systems Command, and sponsor Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Proceedings of Retardation and Recovery Symposium /, by Peter R. Murray, L. E. Winebrenner, and issuing agency United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• Low-speed aerodynamic forces and moments acting on the human body : final report. /, by Peter R. Payne, sponsor Aerospace Medical Research Laboratory (U.S.), and inc. Payne (page images at HathiTrust)
• Drag measurements of upswept afterbodies and analytical study on axisymmetric separation /, by Mansop Hahn, Theodore C. Nark, Paul E. Rubbert, Gunter W. Brune, sponsor Air Force Flight Dynamics Laboratory (U.S.), and sponsor Boeing Commercial Airplane Company (page images at HathiTrust)
• Evaluation of the twin nozzle/afterbody drag and nozzle internal performance computer deck with ESIT free jet data /, by Phillip C. Everling, Douglas L. Bowers, and sponsor Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• The wave drag of arbitrary configurations in linearized flow as determined by areas and forces in oblique planes / (Washington, D.C. : National Advisory Committee for Aeronautics, [1955]), by Harvard Lomax, United States. National Advisory Committee for Aeronautics. NACA research memorandum, and Ames Research Center (page images at HathiTrust)
• General theory of wave-drag reduction for combinations employing quasi-cylindrical bodies with an application to swept-wing and body combinations / (Washington, D.C. : National Advisory Committee for Aeronautics, [1955]), by Jack N. Nielsen, United States. National Advisory Committee for Aeronautics. NACA research memorandum, and Ames Research Center (page images at HathiTrust)
• A transonic investigation of the effects of semisubmerged-store cavities and of slots on the zero-lift drag of a body of revolution / (Washington, D.C. : National Advisory Committee for Aeronautics, [1957]), by George H. Holdaway, Elaine W. Hatfield, Minor R. Wallace, United States. National Advisory Committee for Aeronautics. NACA research memorandum, and Ames Research Center (page images at HathiTrust)
• Aerodynamic characteristics of a leading-edge slat on a 35 degree swept-back wing for Mach numbers from 0.30 to 0.88 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1951), by John A. Kelly, Nora-Lee F. Hayter, Ames Research Center, 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 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1951), by John C. Heitmeyer, Ames Research Center, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Investigation of the lift, center of pressure, and drag of a projectile at Mach number of 8.6 and a Reynolds number of 17 million / (Washington, D.C. : National Advisory Committee for Aeronautics, 1954), by Thomas N. Canning, Ames Research Center, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Aerodynamic characteristics in pitch of several triple-body missile configurations at Mach numbers 0.6 to 1.4 / (Washington, D.C. : National Advisory Committee for Aeronautics, [1956]), by Earl D. Knechtel, Arvid N. Andrea, Ames Research Center, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Wind-tunnel investigation of ailerons on a low-drag airfoil. 2 - The effect of thickened and beveled trailing edges / (Washington, D.C. : National Advisory Committee for Aeronautics, [1944]), by Robert M. Crane, Ralph W. Holtzclaw, Ames Research Center, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Wind-tunnel investigation of ailerons on a low-drag airfoil. 1 - The effect of aileron profile / (Washington, D.C. : National Advisory Committee for Aeronautics, [1944]), by Robert M. Crane, Ralph W. Holtzclaw, Ames Research Center, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Comparison of the energy method with the accelerometer method of computing drag coefficients from flight data / (Washington, D.C. : National Advisory Committee for Aeronautics, [1945]), by Thomas L. Keller, Robert F. Keuper, Ames Research Center, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Misers Bluff ; Phase II, Event I : Determination of the drag coefficient for a typical industrial structural member / (Vicksburg, Miss. : The Station, 1981), by J. W. Ball, Structures Laboratory (U.S.), United States. Army. Office of the Chief of Engineers, and United States. Defense Nuclear Agency (page images at HathiTrust)
• Tables and charts for the evaluation of profile drag from wake surveys at high subsonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, [1945]), by Myron J. Block, S. Katzoff, Langley Aeronautical Laboratory, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Langley full-scale tunnel investigation of the factors affecting the directional stability and trim characteristics of a fighter-type airplane / (Washington, D.C. : National Advisory Committee for Aeronautics, [1945]), by Harold H. Sweberg, Roy H. Lange, Eugene R. Guryanksy, Langley Aeronautical Laboratory, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Lift and drag characteristics of a low-drag airfoil with slotted flap submitted by Curtiss-Wright Corporation / (Washington, D.C. : 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)
• Satellite density measurements with the Rotatable Calibration Accelerometer (ROCA) /, by Frank A Marcos, K. S. W. Champion, and U.S. Air Force Geophysics Laboratory (page images at HathiTrust)
• Flow over a slender body of revolution at supersonic velocities / (Washington D.C. : National Advisory Committee for Aeronautics ;, 1946), by Robert T. Jones, Kenneth Margolis, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Wind-tunnel investigation of a systematic series of modifications to a flying-boat hull / (Washington, D.C. : National Advisory Committee for Aeronautics, 1948), by Felicien F. Fullmer and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• WInd-tunnel investigation of the opening characteristics, drag, and stability of several hemispherical parachutes / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by Stanley H. Scher, Lawrence J. Gale, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Technical Report No. 8 : I. The role of particle diffusion and interception in areosol filtration ; II. Determination of the drag on a cylindrical fiber at low Reynolds nubmer /, by William E. Ranz, R. K. Finn, U.S. Atomic Energy Commission, and University of Illinois at Urbana-Champaign. Engineering Experiment Station (page images at HathiTrust)
• Lower-thermosphere neutral density profiles derived from satellite accelerometer data /, by F. A. Marcos, J. L. Mendillo, and U.S. Air Force Geophysics Laboratory (page images at HathiTrust)
• The dynamics of a rigid body in the space plasma /, by Peter J. L. Wildman and U.S. Air Force Geophysics Laboratory (page images at HathiTrust)
• Application of the satellite triaxial accelerometer experiment to atmospheric density and wind studies /, by Frank A. Marcos, Everett R. Swift, and U.S. Air Force Geophysics Laboratory (page images at HathiTrust)
• Velocity distribution in the wake of bodies of revolution based on drag coefficient /, by Helmut G. Heinrich, Donald J. Eckstrom, sponsor Wright-Patterson Air Force Base (Ohio), sponsor United States. Air Force. Systems Command. Aeronautical Systems Division, and sponsor University of Minnesota. Department of Aerospace Engineering and Mechanics (page images at HathiTrust)
• Theoretical studies of configurations having high lift-to-drag rations in the viscous interaction regime /, by G. DaForno, issuing agency Air Force Flight Dynamics Laboratory (U.S.), and Nassau County General Applied Science Laboratories (Westbury (page images at HathiTrust)
• Drag and dynamics of single and clustered parachutes in freestream, and with wake and ground effects /, by Helmut G. Heinrich, R. A. Noreen, sponsor Air Force Flight Dynamics Laboratory (U.S.), and sponsor University of Minnesota (page images at HathiTrust)
• Optimization of lifting re-entry vehicles /, by Wilbur Leason Hankey, sponsor United States. Air Force. Systems Command. Aeronautical Systems Division, and sponsor Wright-Patterson Air Force Base (Ohio) (page images at HathiTrust)
• Study of parachute scale effects /, by William B. Walcott, sponsor Technology Incorporated, and sponsor United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• Development and flight calibration of a variable-drag device on a variable stability T-33 airplane /, by Frederick D. Newell, Arno E. Schelhorn, B. H. Dolbin, sposnor Wright-Patterson Air Force Base (Ohio), sponsor Cornell Aeronautical Laboratory, and sponsor United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• A study of flow fields about some typical blunt-nosed slender bodies /, by Roberto Vaglio-Laurin, Massimo Trella, United States. Air Force. Office of Scientific Research. issuing body, and Polytechnic Institute of Brooklyn. Department of Aerospace Engineering and Applied Mechanics. sponsor (page images at HathiTrust)
• Interference drag, air drag : theoretical and practical data on aerodynamic drag /, by Sighard F. Hoerner and issuing agency United States. Army Air Forces. Air Matériel Command (page images at HathiTrust)
• The reversibility theorem for thin airfoils in subsonic and supersonic flow / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by Clinton E. Brown and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Experimental and theoretical pressures on blunt cylinders for equilibrium and nonequilibrium air at hypersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, 1963), by Donald M. Kuehn, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Exhaust plume thermodynamic effects on nonaxisymmetric nozzle afterbody performance in transonic flow /, by C. E. Robinson, United States. Air Force. Systems Command. issuing body, sponsor Arnold Engineering Development Center, and Inc. ARO (page images at HathiTrust)
• An investigaion of boattail geometry and Reynolds number effects on forebody and afterbody drag at transonic Mach numbers /, by A. V. Spratley, United States. Air Force. Systems Command. issuing body, sponsor Arnold Engineering Development Center, and Inc. ARO (page images at HathiTrust)
• Wind tunnel verification of drag reduction by microelectromechanical systems (MEMS)-based flow control /, by Laurence Keefe, Daniel A. Pruzan, sponsor Nielsen Engineering & Research, and Ohio). Air Vehicles Directorate Air Force Research Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
• Theoretical and experimental studies of hypersonic viscous effects /, by Clark H. Lewis, Jack D. Whitfield, United States. Air Force. Arnold Air Force Base. sponsor, Arnold Engineering Development Center. issuing body, and Inc. ARO (page images at HathiTrust)
• Computation of axisymmetric separated nozzle-afterbody flow /, by James L. Jacocks, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Experimental determination of aerodynamic drag on a blunted 10-deg cone at angles of attack in hypersonic, rarefied flow /, by David E. Boylan, William H. Sims, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Aerodynamic characteristics of the HAST missile at Mach numbers 2.25, 3.0, and 4.0 /, by J. H. Jones, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Experimental method for correcting nozzle afterbody drag for the effects of jet temperature /, by W. L. Peters, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Investigation of drag reduction by boundary layer suction on a 50-deg swept tapered wing at M (free-stream) = 2.5 to 4 /, by S. R. Pate, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Unique stealth unmanned aerial vehicle (UAV) Houck aircraft design program., by Aaron Altman, sponsor University of Dayton, Ohio). Air Vehicles Directorate Air Force Research Laboratory (Wright-Patterson Air Force Base, and issuing body United States. Air Force Materiel Command (page images at HathiTrust)
• Longitudinal force charactristics of two AFFDL MDF-4 high lift-to-drag configurations at Mach number 19 /, by A. R. Wallace, L. G. Siler, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Viscous effects on zero-lift drag of slender blunt cones /, by Jack D. Whitfield, B. J. Griffith, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• A method for estimating jet entrainment effects on nozzle-afterbody drag /, by R. C. Bauer, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• The drag of cones, plates, and hemispheres in the wake of a forebody in subsonic flow /, by Helmut G. Heinrich, Eugene L. Haak, sponsor University of Minnesota. Department of Aerospace Engineering and Mechanics, and sponsor United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• A robust scheme for control of skin friction and heat transfer in turbulent boundary layers via new instability mechanism /, by Fazle Hussain, Wade Schoppa, sponsor University of Houston. Department of Mechanical Engineering, and issuing body United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Static stability and drag characteristics of a hypersonic aircraft design at Mach numbers 1.5 to 5.6 /, by J. T. Jr Best, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Static stability and drag characteristics of the HAST missile at Mach numbers 2.25, 3.0, and 4.0 /, by J. T. Best, R. W. Rhudy, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Exhaust plume temperature effects on nozzle afterbody performance over the transonic Mach number range /, by C. E. Robinson, M. Dean High, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Afterbody drag investigation of a twin-nozzle fighter-type model at Mach numbers from 0.6 to 1.5 /, by Earl A. Price, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• A Parametric investigation of the annular jet concept for obtaining afterbody drag data at transonic mach numbers /, by Earl A. Price, Inc. sponsor ARO, United States. Air Force. Arnold Air Force Base. sponsor, and United States. Air Force. Systems Command. Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• Experimental evaluation of inlet drag characteristics in the transonic mach number regime /, by F. D. McVey, E. J. Phillips, J. V. Rejeske, McDonnell Douglas Corporation. sponsor, United States. Air Force. Systems Command. sponsor, and Air Force Aero Propulsion Laboratory (U.S.). issuing body (page images at HathiTrust)
• Experimental evaluation of inlet drag characteristics in the transonic mach number regime /, by F. D. McVey, E. J. Phillips, J. V. Rejeske, McDonnell Douglas Corporation. sponsor, United States. Air Force. Systems Command. sponsor, and Air Force Aero Propulsion Laboratory (U.S.). issuing body (page images at HathiTrust)
• Visualization of the flow field about parachute canopy models and approximation of canopy pressure distributions /, by Charles A. Babish, Willard C. Hunter, Air Force Flight Dynamics Laboratory (U.S.). sponsor, and United States. Air Force. Systems Command. Research and Technology Division. issuing body (page images at HathiTrust)
• A Method to calculate uncertainties of drag coefficient wind tunnel data /, by Spence E. Peters, United States. Air Force. Systems Command. sponsor, and Air Force Armament Laboratory. issuing body (page images at HathiTrust)
• Wind tunnel tests of shrouded propellers at Mach numbers from 0 to 0.60 /, by Ronald M. Grose, United States. Air Force. Air Research and Development Command. issuing body, Wright Air Development Center sponsor, and sponsor United Aircraft Corporation. Research Laboratories (page images at HathiTrust)
• Aerodynamic investigation of submunition stabiliation, retardation and dispersion concepts /, by James E. Brunk, United States. Air Force. Systems Command. sponsor, and Air Force Armament Laboratory. issuing body (page images at HathiTrust)
• Subsonic characteristics of low aspect ratios., by J. K. Beamish, Eugene L. Crosthwait, G. J. Klein, United States. Air Force. Systems Command. issuing body, Air Force Flight Dynamics Laboratory (U.S.). sponsor, and General Dynamics Corporation. Fort Worth Division. sponsor (page images at HathiTrust)
• Investigation of boundary-layer suction on a 20-caliber Ogive cylinder at Mach numbers 2.5, 3.0, 3.5, and 4.0 /, by W. T. Strike, S. Pate, Inc. sponsor ARO, United States. Air Force. Air Research and Development Command. sponsor, and Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• An experimental study of boattail pressures at high subsonic Mach numbers and high Reynolds numbers /, by John D. Lee, issuing body Aerospace Research Laboratories (U.S.), and sponsor Ohio State University. Research Foundation (page images at HathiTrust)
• A note on the drag coefficient evaluation for conical vehicles in the low-density transitional flow regime /, by Charles R. Ortloff, issuing body United States. Air Force. Systems Command, sponsor Space and Missile Systems Organization (U.S.), and sponsor Aerospace Corporation (page images at HathiTrust)
• Boundary layer transition at supersonic speeds : three dimensional roughness effects (spheres) /, by E. R. Van Driest, C. B. Blumer, United States. Air Force. Office of Scientific Research. issuing body, and North American Aviation. Space and Information Systems Division. sponsor (page images at HathiTrust)
• Evaluation of an extendible aerodynamic drag brake for monorail rocket sleds /, by Daniel J. Krupovage and issuing body Air Force Missile Development Center (U.S.) (page images at HathiTrust)
• Compressibility effects on drag; air drag: theoretical and practical data on aerodynamic drag /, by Sighard F. Hoerner and issuing agency United States. Army Air Forces. Air Matériel Command (page images at HathiTrust)
• Bounds on errors in KD caused by random errors of measurement in a five station range /, by F. D. Bennett, J. M. Bartos, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Chronograph error in drag measurements /, by George D. Kahl, F. D. Bennett, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)

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