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Aerodynamics, Hypersonic

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• Aerodynamics, Supersonic
• Mach number
• Sound pressure
• Aerodynamics

• Aerodynamics, Hypersonic -- Experiments
• Hypersonic planes
• Hypersonic wind tunnels
• Plasma sheaths

• Aerodynamics of hypersonic flight
• Hypersonic aerodynamics
• Hypersonics
• Hypersonic speeds

• Measurements of the surface flows, heat transfer, pressure distribution, and longitudinal stability of a mercury capsule model at Mach numbers of 6.9 and 9.6 / (Washington, D.C. : National Aeronautics and Space Administration, 1961), by Philip E. Everhart, Peter T. Bernot, and Langley Research Center (page images at HathiTrust)
• A preliminary assessment of the impact of 2-D exhaust-nozzle geometry on the cruise range of a hypersonic aircraft with top-mounted ramjet propulsion / (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 Walter A. Vahl, John P. Weidner, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• A study of infrared emission from hypersonic air flows; semi-annual report (Buffalo, 1962-), by Cornell Aeronautical Laboratory (page images at HathiTrust; US access only)
• Gas dynamics in space exploration ; [scientific papers] (Washington, National Aeronautics and Space Administration, Office of Scientific and Technical Information ; [for sale by the Superintendent of Documents, U.S.Govt. Print.Off.], 1962 [i.e. 1963]), by Chicago NASA-University Conference on the Science and Technology of Space Exploration (page images at HathiTrust)
• X-15 : extending the frontiers of flight / (Washington DC : NASA, [2007]), by Dennis R. Jenkins (page images at HathiTrust)
• Engineering prediction of turbulent skin friction and heat transfer in high-speed flow / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Aubrey M. Cary, Mitchel H. Bertram, and Langley Research Center (page images at HathiTrust)
• Enhancing U.S. competitiveness : NASA hypersonics research and wind tunnel programs : hearing before the Subcommittee on Technology, Environment, and Aviation of the Committee on Science, Space, and Technology, U.S. House of Representatives, One Hundred Third Congress, second session, March 15, 1994. (Washington : U.S. G.P.O. : For sale by the U.S. G.P.O., Supt. of Docs., Congressional Sales Office, 1994), by Space United States. Congress. House. Committee on Science (page images at HathiTrust)
• Hypersonic viscous shock layer of nonequilibrium dissociating gas / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1961), by Paul M. Chung (page images at HathiTrust)
• Weak incident shock interactions with Mach 8 laminar boundary layers / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Louis G. Kaufman, Charles B. Johnson, and Langley Research Center (page images at HathiTrust)
• A study of boundary layer transition on outgassing cones in hypersonic flow / (Washington, D.C. : National Aeronautics and Space Administration, 1971), by C. J. Stalmach, United States National Aeronautics and Space Administration, Vought Aeronautics Company, and Langley Research Center (page images at HathiTrust)
• Nonparallel instability of supersonic and hypersonic boundary layers / (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, 1991), by Nabil M. El-Hady, Langley Research Center, and Inc Analytical Services & Materials (page images at HathiTrust)
• Experimental investigation of a Mach 6 fixed-geometry inlet featuring a swept external-internal compression flow field / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Marvin G. Torrence and Langley Research Center (page images at HathiTrust)
• Hypersonic longitudinal trim, stability, and control characteristics of a delta-wing configuration at high angles of attack / (Washington [D.C.] : National Aeronautics and Space Administration, [1960]), by William H. Close and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Investigation of the rolling stability derivatives of two hypersonic gliders of parabolic plan form at high subsonic speeds / (Washington [D.C.] : National Aeronautics and Space Administration, [1960]), by Donald D. Arabian and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Asymmetric hypersonic flow / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by Stephen H. Maslen, Langley Research Center, and Md.) Research Institute for Advanced Study (Baltimore (page images at HathiTrust)
• Assessment of a transitional boundary layer theory at low hypersonic mach numbers / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by S. J. Shamroth, H. McDonald, Langley Research Center, and United Aircraft Corporation (page images at HathiTrust)
• Effect of geometry variations on lee-surface vortex-induced heating for flat-bottom three-dimensional bodies at Mach 6 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Jerry N. Hefner and Lanley Research Center (page images at HathiTrust)
• Experimental studies of hypersonic boundary-layer transition and effects of wind-tunnel disturbances / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by P. Calvin Stainback and Langley Research Center (page images at HathiTrust)
• Hot-wire anemometry in hypersonic helium flow / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Richard D. Wagner, Leonard M. Weinstein, and Langley Research Center (page images at HathiTrust)
• Fluctuating pressures measured beneath a high-temperature, turbulent boundary layer on a flat plate at a Mach number of 5 / (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 Tony L. Parrott, Cindy W. Albertson, Michael G. Jones, and Langley Research Center (page images at HathiTrust)
• An upwind-biased, point-implicit relaxation algorithm for viscous, compressible perfect-gas flows / (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 Peter A. Gnoffo and Langley Research Center (page images at HathiTrust)
• Measured and predicted aerodynamic coefficients and shock shapes for Aeroassist Flight Experiment (AFE) 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, 1990), by William L. Wells and Langley Research Center (page images at HathiTrust)
• NASA Aerodynamics Program : annual report 1990 / ([Washington, D.C.] : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991), by Louis J. Williams and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program (page images at HathiTrust)
• Design and performance at a local Mach number of 6 of an inlet for an integrated scramjet concept / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Carl A. Trexler, Sue W. Souders, and Langley Research Center (page images at HathiTrust)
• Numerical solution of the hypersonic viscous-shock-layer equations for laminar, transitional, and turbulent flows of a perfect gas over blunt axially symmetric bodies / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by E. Clay Anderson, James N. Moss, and Langley Research Center (page images at HathiTrust)
• Experimental study of sharp- and blunt-nose streamwise corners at Mach 20 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Ralph D. Watson and Langley Research Center (page images at HathiTrust)
• Comparisons of two-dimensional shock-expansion theory with experimental aerodynamic data for delta-planform wings at high supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Lloyd S. Jernell and Langley Research Center (page images at HathiTrust)
• Data on effects of incident-reflecting shocks on the turbulent boundary layer / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1966]), by S. Z. Pinckney and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Simulation of hypersonic scramjet exhaust / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by R. A. Oman, Langley Research Center, and Grumman Aerospace Corporation (page images at HathiTrust)
• A study to determine the flight characteristics and handling qualities of variable geometry spacecraft. (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1970), by B. J. Kuchta, Langley Research Center, and General Dynamics Corporation (page images at HathiTrust)
• Aerodynamic heating and loading within large open cavities in cone and cone-cyclinder-flare models at Mach 6.7 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by L. Roane Hunt and Langley Research Center (page images at HathiTrust)
• Aerodynamic pressure and heating-rate distributions in tile gaps around chine regions with pressure at a Mach number of 6.6 / (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 L. Roane Hunt, Kristopher K. Notestine, and Langley Research Center (page images at HathiTrust)
• An approximate method for calculating three-dimensional inviscid hypersonic flow fields / (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 J. Riley, Fred R. DeJarnette, and Langley Research Center (page images at HathiTrust)
• An upwind-biased space marching algorithm for supersonic viscous flow / (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, 1991), by Francis A. Greene and Langley Research Center (page images at HathiTrust)
• Parametric experimental investigation of a scramjet nozzle at Mach 6 with freon and argon or air used for exhaust simulation / (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, 1991), by James M. Cubbage, William J. Monta, and Langley Research Center (page images at HathiTrust)
• An explicit upwind algorithm for solving the parabolized Navier-Stokes equations / (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, 1991), by John J. Korte and Langley Research Center (page images at HathiTrust)
• The Rotornet : a high performance hypersonic decelerator for planetary entry / (Washington, D.C. : NASA, 1965), by A. C. Kyser, Astro Research Corporation, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Mechanics of a coned rotating net / ([Washington] : National Aeronautics and Space Administration, [1965]), by Richard H. MacNeal, Astro Research Corporation, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Hypersonic aerodynamic characteristics of a family of power-law, wing-body configuratioons / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by James C. Townsend and Langley Research Center (page images at HathiTrust)
• Safe atmosphere entry of an isotope heat source with a single stable trim attitude at hypersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by Lionel L. Levy, Raymond K. Burns, and Ames Research Center (page images at HathiTrust)
• Theoretical and experimental studies of reentry plasmas / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by M. G. Dunn, Sang-Wook Kang, Langley Research Center, and Cornell Aeronautical Laboratory (page images at HathiTrust)
• Discrete sonic jets used as boundary-layer trips at Mach numbers of 6 and 8.5 (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by David R. Stone, Aubrey M. Cary, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Hypersonic and transonic buzz measurements on the lower pitch flap of M2-F2 lifting entry configuration (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by Robert W. Warner, Phillip R. Wilcox, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• Hypersonic aerodynamics and entry-maneuver--aerothermodynamic interactions for two lifting entry vehicles / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by James P. Arrington, William C. Woods, and Langley Research Center (page images at HathiTrust)
• Evaluation of compressible-flow Preston tube calibrations / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Jerry M. Allen and Langley Research Center (page images at HathiTrust)
• Investigation of flow fields within large-scale hypersonic inlet models (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by A. Vernon Gnos, Joseph P. DeCarlo, Robert J. Sanator, William R. Seebaugh, Earl C. Watson, United States National Aeronautics and Space Administration, Fairchild Industries. Fairchild Republic Division, and Ames Research Center (page images at HathiTrust)
• Analytical and experimental studies of shock interference heating in hypersonic flows (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by J. Wayne Keyes, Frank D. Hains, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Aerodynamic and flow-visualization studies of variations in the geometry of irregular planform wings at a Mach number of 20.3 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by David R. Stone, Bernard Spencer, and Langley Research Center (page images at HathiTrust)
• Interference heating from interactions of shock waves with turbulent boundary layers at Mach 6 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Charles B. Johnson, Louis G. Kaufman, and Langley Research Center (page images at HathiTrust)
• Pilot model expansion tunnel test flow properties obtained from velocity, pressure, and probe measurements (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Wilfred J. Friesen, John A. Moore, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Synthesis of an airfoil at supersonic mach number / ([Washington] : National Aeronautics and Space Administration, [1964]), by Lucien A. Schmit, William A. Thornton, Case Institute of Technology, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• A parametric study of effect of forebody shape on flow angularity at Mach 8 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Charles B. Johnson, Don C. Marcum, and Langley Research Center (page images at HathiTrust)
• Investigation of an anomalous flow condition of the Langley pilot model expansion tube / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Wilfred J. Friesen 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)
• 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)
• Shock shapes on blunt bodies in hypersonic-hypervelocity helium, air, and CO₂ flows, and calibration results in Langley 6-inch expansion tube / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Charles G. Miller and Langley Research Center (page images at HathiTrust)
• A comparison of measured and predicted sphere shock shapes in hypersonic flows with density ratios from 4 to 19 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Charles G. Miller and Langley Research Center (page images at HathiTrust)
• Second-order small-disturbance solutions for hypersonic flow over power-law bodies / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by James C. Townsend and Langley Research Center (page images at HathiTrust)
• Experimental and numerical investigation of boundary-layer development and transition on the walls of a Mach 5 nozzle / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by William D. Harvey, Julius E. Harris, Aubrey M. Cary, and Langley Research Center (page images at HathiTrust)
• Experimental study of a free turbulent shear flow at Mach 19 with electron-beam and conventional probes / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by William D. Harvey, William W. Hunter, and Langley Research Center (page images at HathiTrust)
• Pressure measurements on a hypersonic glide configuration having 79.5° sweepback and 45° dihedral at a Mach number of 4.95 / (Washington, D.C. : National Aeronautics and Space Administration, 1959), by Morton Cooper, Charles R. Gunn, and Langley Research Center (page images at HathiTrust)
• Kinetic study of the hypersonic flow past the leading edge of a flat plate. (Urbana. Ill. : Dept. of Computer Science ;, 1968), by Rateb Jaber El Assar (page images at HathiTrust)
• Studies of optimum body shapes at hypersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, 1967), by Louis S. Stivers, Bernard Spender, Langley Research Center, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• High speed aeronautics : hearing before the Subcommittee on Transportation, Aviation, and Materials of the Committee on Science and Technology, U.S. House of Representatives, Ninety-ninth Congress, first session, July 24, 1985. (Washington : U.S. G.P.O., 1985), by Aviation United States. Congress. House. Committee on Science and Technology. Subcommittee on Transportation (page images at HathiTrust)
• Variational approach to problems of hypervelocity flight; final report. ([Lafayette, Ind., Purdue University, School of Aeronautical Engineering, 1959]), by Angelo Miele (page images at HathiTrust; US access only)
• Analysis of hypersonic pressure and heat transfer tests on delta wings with laminar and turbulent boundary layers / ([Washington, D.C.] : National Aeronautics and Space Administration, [1966]), by A. L. Nagel, L. B. Doyle, H. D. Fitzsimmons, and Langley Research Center (page images at HathiTrust)
• Use of tetrafluoromethane to simulate real-gas effects on the hypersonic aerodynamics of blunt vehicles / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : for sale by the National Technical Information Service, [1969]), by Robert A. Jones and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Wave superheater hypersonic tunnel; semiannual report, (Buffalo, 1959-), by Cornell Aeronautical Laboratory and James E. Carpenter (page images at HathiTrust)
• The blunt-body problem in hypersonic flow at low Reynolds number. (Buffalo, Cornell Aeronautical Laboratory, Inc., 1963), by Hsien Kei Cheng (page images at HathiTrust)
• Engineering design of a wave superheater facility for hypersonic research and development. (Buffalo, Cornell Aeronautical Laboratory, Inc., 1959), by James E. Carpenter (page images at HathiTrust)
• Hypersonic flow with combined leading-edge bluntness and boundary-layer displacement effect. (Buffalo, Cornell Aeronautical Laboratory, 1960), by Hsien Kei Cheng (page images at HathiTrust)
• Expansion of gas clouds and hypersonic jets bounded by a vacuum. (El Segundo, Calif., Aerospace Corp., 1962), by Harold Mirels, James Francis Mullen, and Aerospace Corporation (page images at HathiTrust)
• 48-inch hypersonic shock tunnel; description and capabilities. (Buffalo, 1962), by Cornell Aeronautical Laboratory (page images at HathiTrust)
• Six-degree-of-freedom equations of motion for a maneuvering re-entry vehicle (Buffalo, Cornell Aeronautical Laboratory, 1962), by John M. Schuler, Francis E. Pritchard, and Cornell Aeronautical Laboratory (page images at HathiTrust)
• Low-density research in the hypersonic shock tunnel ([Buffalo?, 1960?]), by Charles E. Wittliff and Merle R. Wilson (page images at HathiTrust)
• Extended hypervelocity gas dynamic charts for equilibrium air. (Los Angeles, Physical Research Laboratory, Space Technology Laboratories, 1960), by Richard W. Ziemer (page images at HathiTrust)
• Hypersonic research summary. (Buffalo, Cornell Aeronautical Laboratory, 1960), by Gardner J. Fabian (page images at HathiTrust)
• Hypersonic dynamic stability. (Wright-Patterson Air Force Base, Ohio, Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, 1967-), by General Electric Company (page images at HathiTrust)
• Aerothermodynamic consequences of nozzle nonequilibrium ([Arnold Air Force Station, Tenn., Arnold Engineering Development Center, Air Force Systems Command, 1966]), by A. F. Burke and J. E. Wallace (page images at HathiTrust)
• The shock layer concept and three-dimensional hypersonic boundary layers. (Buffalo, Cornell Aeronautical Laboratory, 1961), by Hsien Kei Cheng (page images at HathiTrust)
• Effects of ambient nonuniformities in flow over hypersonic test bodies. (Buffalo, Cornell Aeronautical Laboratory, Inc., 1963), by J. Gordon Hall (page images at HathiTrust)
• Instrumentation for force and pressure measurements in a hypersonic shock tunnel (Buffalo, Cornell Aeronautical Laboratory, Inc., 1962), by James F. Martin, Leroy M. Stevenson, and George R. Duryea (page images at HathiTrust)
• Radiation at hypersonic speeds. (Buffalo, Cornell Aeronautical Laboratory, 1961), by Charles E. Treanor (page images at HathiTrust)
• Hypersonic research in the shock tunnel. ([New York?] Institute of the Aeronautical Sciences, [1960?]), by Charles E. Wittliff (page images at HathiTrust)
• Nonequilibrium scaling criterion for inviscid hypersonic airflows, (Buffalo, Cornell Aeronautical Laboratory, Inc., 1962), by Walter E. Gibson and Paul V. Marrone (page images at HathiTrust)
• A similitude for nonequilibrium phenomena in hypersonic flight, (Buffalo, Cornell Aeronautical Laboratory, Inc., 1962), by Walter E. Gibson, Paul V. Marrone, and Cornell Aeronautical Laboratory (page images at HathiTrust)
• An investigation of laminar heat transfer to slender cones in the hypersonic shock tunnel (Buffalo, Cornell Aeronautical Laboratory, 1961), by Charles E. Wittliff and Merle R. Wilson (page images at HathiTrust)
• Shock tunnel studies of high-enthalpy ionized airflows, (Buffalo, 1962), by Cornell Aeronautical Laboratory and Alan Eschenroeder (page images at HathiTrust)
• Shock-bounded, self-similar flows with volumetric mass, momentum, and energy addition. (El Segundo, Calif., Aerospace Corp., 1962), by Harold Mirels, Mullen James Francis, and Aerospace Corporation (page images at HathiTrust)
• An analysis of nonequilibrium inviscid flow, (Buffalo, Cornell Aeronautical Laboratory, Inc., 1962), by Walter E. Gibson and Alexander Sowyrda (page images at HathiTrust)
• An experimental study of the effect of mass injection at the stagnation point of a blunt body, (Pasadena, Guggenheim Aeronautical Laboratory, California Institute of Technology, 1958), by Howard K. McMahon (page images at HathiTrust)
• Inviscid radiating shock layers about spheres traveling at hyperbolic speeds in air / (Washington, D. C. : National Aeronautics and Space Administration ; Springfield, Va. : for sale by the Clearinghouse for Federal Scientific and Technical Information, 1969), by Richard W. Barnwell, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust; US access only)
• Hypersonic shock-heated flow parameters for velocities to 46,000 feet per second and altitudes to 323,000 feet / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Office of Technical Services, Department of Commerce, Washington, D.C. 20230], 1963), by Paul W. Huber, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Experimental investigation of multiple-jet liquid injection into hypersonic flow / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and technical Information, Springfield, Va. 22151], 1970), by William F. Hinson, Dennis M. Bushnell, Paul B. Gooderum, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Aerodynamic characteristics of a hypersonic transport configuration at Mach 6.86 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 20230], 1970), by William J. Small, David E. Fetterman, Frank S. Kirkham, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Water injection from a 9⁰ hemisphere-cone into a hypersonic airstream / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by William L. Weaver, William F. Hinson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Summary of research results: Hypersonic Research Laboratory, 1 July 1969 - 31 December 1971. (Wright-Patterson Air Force Base, Ohio, Aerospace Research Laboratories, Air Force Systems Command, [1972?]), by Hypersonic Research Laboratory (U.S.) (page images at HathiTrust; US access only)
• Hypersonic flow past blunt cones with consideration of the equilibrium physicochemical transformations, ([Washington] National Aeronautics and Space Administration; for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va., [1970]), by Vladimir Lunev, V. G. Pavlov, and K. M. Magomedov (page images at HathiTrust; US access only)
• Numerical solution of the equations for compressible laminar, transitional, and turbulent boundary layers and comparisons with experimental data / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Office of Technical Services, Department of Commerce, Washington, D.C. 20230], 1971), by Julius E. Harris, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Studies of airframe-propulsion-system integration for Mach 6 cruise vehicles / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1967), by Frank S. Kirkham and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Analytical chemical kinetic study of the effect of carbon dioxide and water vapor on hydrogen-air constant-pressure combustion / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151], 1970), by Wayne D. Erickson, George F. Klich, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• The Ames M-50 helium tunnel / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151], 1970), by Joseph H. Kemp, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Experimental study of the shock wave due to a blunt leading edge in the hypersonic merged-flow regime / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by Roger M. Winebarger, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Effects of two-dimensional sinusoidal waves on heat transfer and pressure over a plate at Mach 8.0 / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by Leonard M. Weinstein, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Local flow field around a pylon-mounted dummy ramjet engine on the X-15-2 airplane for Mach numbers from 2.0 to 6.7 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and technical Information, Springfield, Va. 22151], 1970), by Frank W. Burcham, Jack Nugent, Flight Research Center (U.S.), and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Real-air data-reduction procedures based on flow parameters measured in the test section of supersonic and hypersonic facilities / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1972), by Charles G. Miller, Sue E. Wilder, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• A new method for providing continuous high-temperature air flow for hypersonic research, (Buffalo, N.Y., Cornell Aeronautical Laboratory, 1956), by Alexander H. Flax, William E. Smith, and Abraham Hertzberg (page images at HathiTrust)
• Study of hypersonic contaminated wake by an exact numerical solution. ([Philadelphia?] Missile and Space Division, General Electric, 1963), by Huon Li and Philadelphia General Electric Company. Space Sciences Laboratory (page images at HathiTrust)
• Comparison of turbulent wake characteristics with different eddy viscosity coefficients, ([Philadelphia?] Missile and Space Division, General Electric, 1963), by K. S. Wan and Philadelphia General Electric Company. Space Sciences Laboratory (page images at HathiTrust)
• Investigation of test time at undertailored conditions in a shock tunnel. (Buffalo, Cornell Aeronautical Laboratory, Inc., [195-?]), by James F. Martin and Cornell Aeronautical Laboratory Hypersonic Research Dept (page images at HathiTrust)
• On local flat-plate similarity in the hypersonic boundary layer, (Buffalo, Cornell Aeronautical Laboratory, Inc. of Cornell Laboratory, 1960), by Franklin Kingston Moore (page images at HathiTrust)
• Experimental determination of flow-interference effects of wing-mounted two-dimensional, full-capture propulsion nacelles in close proximity to a vehicle body at a Mach number of 6 / (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 Walter A. Vahl, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• An analysis of combustion studies in shock expansion tunnels and reflected shock tunnels / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Casimir J. Jachimowski and Langley Research Center (page images at HathiTrust)
• Effect of Reynolds number variation on aerodynamics of a hydrogen-fueled transport concept at Mach 6 / (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 Jim A. Penland, Don C. Marcum, and Langley Research Center (page images at HathiTrust)
• Mach 6 experimental and theoretical stability and performance of a cruciform missile at angles of attack up to 65⁰ / (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 Edward R. Hartman, Patrick J. Johnston, and Langley Research Center (page images at HathiTrust)
• Aerodynamic characteristics of wings designed with a combined-theory method to cruise at a Mach number of 4.5 / (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 Robert J. Mack and Langley Research Center (page images at HathiTrust)
• Conservation equations and physical models for hypersonic air flows in thermal and chemical nonequilibrium / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1989), by Peter A. Gnoffo, Judy L. Shinn, Roop N. Gupta, and United States. National Aeronautics and Space Administration. Office of Management (page images at HathiTrust)
• Viscous hypersonic flow past a slender cone / ([Washington, D.C. :] National Aeronautics and Space Administration, [1967]), by V. S. Nikolaev (page images at HathiTrust)
• Loading tests of a wing structure for a hypersonic aircraft / (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 Roger A. Fields, William H. Siegel, Lawrence F. Reardon, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Aerothermal test results from the first flight of the Pegasus air-launched space booster / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991), by Gregory Noffz and Dryden Flight Research Facility (page images at HathiTrust)
• An Inlet analysis for the NASA hypersonic research engine aerothermodynamic integration model / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Earl H. Andrews and Langley Research Center (page images at HathiTrust)
• Experimental investigation at Mach 8 of the effects of projections and cavities on heat transfer to a model of the Viking aeroshell / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Theodore R. Creel and Langley Research Center (page images at HathiTrust)
• An exploratory investigation of a wake disruption technique for studying wake reestablishment time / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Louis E. Clark, Robert A. Jones, 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)
• Heat transfer distributions induced by elevon deflections on swept wings and adjacent surfaces at Mach 6 / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Charles B. Johnson, Louis G. Kàufman, Grumman Aerospace Corporation, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Aerodynamic characteristics at Mach 6 of a hypersonic research airplane concept having a 70 ̊swept delta wing / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Louis E. Clark, Christine B. Richie, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Mach 6 flow field surveys beneath the forebody of an airbreatinng missile / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1986), by Patrick J. Johnston, James L. Hunt, and Langley Research Center (page images at HathiTrust)
• Aeordynamic characteristics of a distinct wing-body configuration at Mach 6 : experiment, theory, and the hypersonic isolation principle / (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 Jim A. Penland, Jimmy L. Pittman, and Langley Research Center (page images at HathiTrust)
• Aerodynamic characteristics, including effect of body shape, of a Mach 6 aircraft concept / (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 Gregory D. Riebe and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Laminar heat-transfer distributions on biconics at incidence in hypersonic-hypervelocity flows / (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 Charles G. Miller, Peter A. Gnoffo, John R. Micol, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Experimental and analytical study of an inlet forebody for an airframe-integrated scramjet concept / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Earl H. Andrews, S. Z. Pinckney, Anthony M. Agnone, and Langley Research Center (page images at HathiTrust)
• Abort separation study of a shuttle orbiter and external tank at hypersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Peter T. Bernot and Langley Research Center (page images at HathiTrust)
• Measured pressure distributions, aerodynamic coefficients, and shock shapes on blunt bodies at incidence in hypersonic air and CF₄ / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1982), by Charles G. Miller, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Langley Research Center (page images at HathiTrust)
• Longitudinal aerodynamic characteristics at Mach 0.60 to 2.86 of a fighter configuration with strut braced wing / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Samuel M. Dollyhigh, Giuliana Sangiorgio, William J. Monta, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Pressure and thermal distributions on wings and adjacent surfaces induced by elevon deflections at Mach 6 / ([Washington, D.C.] : National Aeronautics and Space Administration, Scientific and Technical Information Office, 1979), by Louis G. Kaufman and Charles B. Johnson (page images at HathiTrust)
• Effect of modifications on aerodynamic characteristics of a single-stage-to-orbit vehicle at Mach 5.9 / (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, 1983]), by Peter T. Bernot, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Flow-field surveys on the windward side of the NASA 040A space shuttle orbiter at 31 ̊angle of attack and Mach 20 in helium / ([Washington] : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by George C. Ashby, V. T. Helms, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Aerodynamic characteristics at Mach number 0.2 of a wing-body concept for a hypersonic research airplane / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by James L. Dillon, Theodore R. Creel, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Aerodynamic testing technique for twin-fuselage models at hypersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by George C. Ashby and Langley Research Center (page images at HathiTrust)
• Aerodynamic characteristics at Mach numbers from 0.33 to 1.20 of wing-body design concept for a hypersonic research airplane / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by James L. Dillon, Jimmy L. Pittman, 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)
• Real-time aerodynamic heating and surface temperature calculations for hypersonic flight simulation / (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 Robert D. Quinn, Leslie Gong, and Dryden Flight Research Facility (page images at HathiTrust)
• A method for calculating a real-gas two-dimensional nozzle contour including the effects of gamma / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Charles B. Johnson, Lillian R. Boney, and Langley Research Center (page images at HathiTrust)
• Exploratory investigation of the aerodynamic characteristics of a biwing vehicle at Mach 20.3 / (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 Peter T. Bernot and Langley Research Center (page images at HathiTrust)
• Hypersonic characteristics of an advanced aerospace plane at Mach 20.3 / (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 Ronald S. McCandless and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Longitudinal aerodynamic characteristics of a fighter model with a close-coupled canard at Mach numbers from 0.40 to 1.20 / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Richard J. Re, Francis J. Capone, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Wall-temperature effects on the aerodynamics of a hydrogen-fueled transport concept in Mach 8 blowdown and shock tunnels / (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 Jim A. Penland, Sharon H. Stack, Don C. Marcum, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (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)
• Stagnation point heat transfer during hypervelocity atmospheric entry / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1970), by W. S. Rigdon, M. Thomas, R. B. Dirling, McDonnell Douglas Astronautics Company. Western Division, and Langley Research Center (page images at HathiTrust)
• Aerodynamic effects of bulbous bases / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information [distributor], 1969), by Lars E. Ericsson, J. Peter Reding, Lockheed Missiles and Space Company, and Langley Research Center (page images at HathiTrust)
• Analytical comparison of hypersonic flight and wind tunnel viscous/inviscid flow fields / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1975]), by H. J. Fivel, L. J. Mockapetris, R. V. Masek, Langley Research Center, and McDonnell Douglas Astronautics Company-East (page images at HathiTrust)
• Hypersonic ionizing air viscous shock-layer flows over nonanalytic blunt bodies / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1975]), by Miner. E. W. (Earnest Wade), Clark H. Lewis, Lyndon B. Johnson Space Center, and Virginia Polytechnic Institute and State University. Aerospace and Ocean Engineering Dept (page images at HathiTrust)
• A study of surface pressure fluctuations in hypersonic turbulent boundary layers / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1974]), by K. R. Raman, Ames Research Center, and Nielsen Engineering & Research (page images at HathiTrust)
• Viscous computations of cold air/air flow around scramjet nozzle afterbody / (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 Oktay Baysal, Walter C. Englelund, Old Dominion University. Dept. of Mechanical Engineering and Mechanics, and Langley Research Center (page images at HathiTrust)
• Flow analysis and design optimization methods for nozzle afterbody of a hypersonic vehicle / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Oktay Baysal, Langley Research Center, and Old Dominion University. Dept. of Mechanical Engineering and Mechanics (page images at HathiTrust)
• Thermal-structural design study of an airframe-integrated scramjet : summary report / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Information Service], 1979), by O. A. Buchmann, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Hypersonic airframe structures technology needs and flight test requirements / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by National Technical Information Service], 1979), by J. E. Stone, McDonnell Douglas Corporation, Langley Research Center, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and L. C. Koch (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)
• Charts for equilibrium flow properties of air in hypervelocity nozzles / (Washington : National Aeronautics and Space Administration, [1962]), by Leland H. Jorgensen, Geyle M. Baum, and Ames Research Center (page images at HathiTrust)
• Secondary flow fields embedded in hypersonic shock layers / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, 1962]), by Alvin Seiff and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Real-gas correction factors for hypersonic flow parameters in helium. / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1960]), by Wayne D. Erickson and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Investigation of the aerodynamic characteristics of a hypersonic transport model at Mach numbers to 6 / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1971), by James C. Ellison, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Spectroscopic analysis of electron-beam-induced fluorescence in hypersonic helium flow / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by Mervin E. Hillard, Richard W. Storey, Stewart L. Ocheltree, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Operational and performance characteristics of the X-15 spherical, hypersonic flow-direction sensor / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1965]), by Chester H. Wolowicz, Terrence D. Gossett, and Flight Research Center (U.S.) (page images at HathiTrust)
• The influence of low wall temperature on boundary-layer transition and local heat transfer on 2-inch-diameter hemispheres at a Mach number of 4.95 and a Reynolds number per foot of 73.2 x 10⁶ / (Washington : National Aeronautics and Space Administration, [1960]), by Morton Cooper, Jerome D. Julius, Edward E. Mayo, and Langley Research Center (page images at HathiTrust)
• Heat transfer to cylinders in crossflow in hypersonic rarefied gas streams / (Washington : National Aeronautics and Space Administration, [1960]), by Ruth N. Weltmann, Perry W. Kuhns, and Lewis Research Center (page images at HathiTrust)
• Methods of predicting laminar heat rates on hypersonic vehicles / (Washington : National Aeronautics and Space Administration, [1959]), by Richard J. Wisniewski and Lewis Research Center (page images at HathiTrust)
• A simplified study on the nonequilibrium Couette and boundary-layer flows with air injection / (Washington : National Aeronautics and Space Administration, [1960]), by Paul M. Chung and Ames Research Center (page images at HathiTrust)
• Effects of leading-edge bluntness and ramp deflection angle on laminar boundary-layer separation in hypersonic flow / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1966]), by James C. Townsend and Langley Research Center (page images at HathiTrust)
• Experimental separation studies for two-dimensional wedges and curved surfaces at Mach numbers of 4.8 to 6.2 / (Washington : National Aeronautics and Space Administration, [1962]), by James R. Sterrett, James C. Emery, and Langley Research Center (page images at HathiTrust)
• A study of equilibrium real-gas effects in hypersonic air nozzles, including charts of thermodynamic properties for equilibrium air / (Washington : National Aeronautics and Space Administration, [1960]), by Wayne D. Erickson, Helen S. Creekmore, and Langley Research Center (page images at HathiTrust)
• Experimental determination of the recovery factor and analytical solution of the conical flow field for a 20 ̊included angle cone at Mach numbers of 4.6 and 6.0 and stagnation temperatures to 2600 ̊R / (Washington : National Aeronautics and Space Administration, [1961]), by Frank A. Pfyl, Leroy L. Presley, and Ames Research Center (page images at HathiTrust)
• Experimental boundary-layer edge Mach numbers for two space shuttle orbiters at hypersonic speeds / (Washington, DC : National Aeronautics and Space Administration, 1972), by George C. Ashby, 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)
• Ideal-gas tables for helium flow in the Mach number range from 40 to 100 / (Washington : National Aeronautics and Space Administration, [1962]), by James N. Mueller and Langley Research Center (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)
• Heat transfer and pressure distribution at a mach number of 6.8 on bodies with conical flares and extensive flow separation.&bJonh V. Becker and Peter F. Korycinski. (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce], [1962]), by John V. Becker, Peter F. Korycinski, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• A theoretical and experimental study of hypersonic flow over flared bodies at incidence / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1966]), by John V. Rakich, Gene P. Menees, and Ames Research Center (page images at HathiTrust)
• Inviscid hypersonic flow over a blunt body with high rates of mass and heat transfer / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1968]), by E. Dale Martin and Ames Research Center (page images at HathiTrust)
• An investigation of heat transfer within regions of separated flow at a Mach number of 6.0 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1965]), by Paul F. Holloway, Helen S. Creekmore, James R. Sterrett, and Langley Research Center (page images at HathiTrust)
• Interference heating on a swept cylinder in region of intersection with a wedge at Mach number 8 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1965]), by Dennis M. Bushnell and Langley Research Center (page images at HathiTrust)
• A simplified method for thermal analysis of a cowl leading edge subject to intense local shock-wave-interference heating / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by David M. McGowan, Stephen J. Scotti, Charles J. Camarda, and Langley Research Center (page images at HathiTrust)
• Simulation of real-gas effects on pressure distributions for aeroassist flight experiment vehicle and comparison with prediction / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by John R. Micol and Langley Research Center (page images at HathiTrust)
• Evaluation of a technique to generate artificially thickened boundary layers in supersonic and hypersonic flows / (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 A. Robert Porro and Lewis Research Center (page images at HathiTrust)
• Measured and predicted shock shapes and aerodynamic coefficients for blunted cones at incidence in helium at Mach 20.3 / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1979), by Robert L. Calloway, Nancy H. White, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Langley Research Center (page images at HathiTrust)
• Aerodynamic characteristics of two single-stage-to-orbit vehicles at Mach 20.3 / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Peter T. Bernot 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)
• A hybridized method for computing high-reynolds-number hypersonic flow about blunt bodies / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by K. James Weilmuenster, H. Harris Hamilton, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• A modified T-value method for selection of strain gages for measuring loads on a low aspect ratio wing / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Informaion Branch; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by Ming Han Tang, Robert G. Sheldon, Hugh L. Dryden Flight Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Analysis of hypersonic pressure and heat transfer tests on a flat plate with a flap and a delta wing with body, elevons, fins, and rudders / ([Washington] : National Aeronautics and Space Administration : For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va., 1966), by H. L. Giles, J. W. Thomas, and Langley Research Center (page images at HathiTrust)
• Development of a computer code for calculating the steady super/hypersonic inviscid flow around real configurations : volume I-computational technique / (Washington : U.S. National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by Frank Marconi, Larry Yaeger, Manuel Salas, United States National Aeronautics and Space Administration, and Grumman Aerospace Corporation (page images at HathiTrust)
• Development of a computer code for calculating the steady super/hypersonic inviscid flow around real configurations : volume II - code description / (Washington : U.S. National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by Frank Marconi, Larry Yaeger, United States National Aeronautics and Space Administration, Langley Research Center, and Grumman Aerospace Corporation (page images at HathiTrust)
• Computer user's guide for a chemically reacting viscous shock-layer program / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1975]), by E. W. Miner, Clark H. Lewis, Lyndon B. Johnson Space Center, and Virginia Polytechnic Institute and State University. Aerospace and Ocean Engineering Dept (page images at HathiTrust)
• Method for obtaining aerodynamic data on hypersonic configurations with scramjet exhaust flow simulation / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by William R. Hartill and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NSEG : a segmented mission analysis program for low and high speed aircraft / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by D. S. Hague, H. L. Rozendaal, Aerophysics Research Corporation, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Flow separation in shock wave boundary layer interactions at hypersonic 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 A. Hamed, Langley Research Center, and Joint Institute for Advancement of Flight Sciences (page images at HathiTrust)
• Calculated radio attenuation due to plasma sheath on hypersonic blunt-nosed cone / (Washington, D.C. : National Aeronautics and Space Administration, [1963]), by John S. Evans, Paul W. Huber, and Langley Research Center (page images at HathiTrust)
• Prospects for obtaining aerodynamic heating results from analysis of meteor flight data / (Washington, D.C. : National Aeronautics and Space Administration : For sale by the Office of Technical Services, Dept. of Commerce, [1964]), by H. Julian Allen, Nataline A. James, and Ames Research Center (page images at HathiTrust)
• Effect of slight blunting of leading edge of an immersed body on the flow around it at hypersonic speeds / (Washington : National Aeronautics and Space Administration, 1960), by G. G. Chernyĭ (page images at HathiTrust)
• Surface pressure distributions with a sonic jet normal to adjacent flat surfaces at Mach 2.92 to 6.4 / (Washington : National Aeronautics and Space Administration, [1961]), by Robert W. Cubbison, James J. Ward, Bernhard H. Anderson, and Lewis Research Center (page images at HathiTrust)
• Hypersonic flutter analysis using measured static aerodynamic derivatives, and comparison with experiment / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151], 1969), by Robert C. Goetz, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• A parametric study of the aerodynamic characteristics of nose-cylinder-flare bodies at a Mach number of 6.0 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1965]), by George C. Ashby, Aubrey M. Cary, and Langley Research Center (page images at HathiTrust)
• Effect of two-dimensional multiple sine-wave protrusions on the pressure and heat-transfer distributions for a flat plate at Mach 6 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1968]), by Aubrey M. Cary, E. Leon Morrisette, and Langley Research Center (page images at HathiTrust)
• Pressure and heat transfer on blunt curved plates with concave and convex surfaces in hypersonic flow / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1968), by Davis H. Crawford, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Hypersonic aerodynamic characteristics of minimum-wave-drag bodies having variations in cross-sectional shape / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1967), by Bernard Spencer, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Exploratory study of transient unstart phenomena in a three-dimensional fixed-geometry scramjet engine / (Washington : U.S. National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by Allan R. Wieting and Langley Research Center (page images at HathiTrust)
• Comparison of prediction methods and studies of relaxation in hypersonic turbulent nozzle-wall boundary layers / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va. 22151], 1969), by Dennis M. Bushnell, William V. Feller, William D. Harvey, Charles B. Johnson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Angle-of-attack analysis of a spinning slender cone with slight aerodynamic and mass asymmetries (Reentry F) (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by Gerard E. Woodbury, W. Douglas Morris, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Model wind-tunnel and flight investigation of a parawing -- lifting-body landing system / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by Rodger L. Naeseth, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Experimental investigation of a swept-strut fuel-injector concept for scramjet application / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service,?, 1977), by Langley Research Center and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Thermodynamic properties of gaseous fluorocarbons and isentropic equilibrium expansions of two binary mixtures of fluorocarbons and argon / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Noel A. Talcott, Langley Research Center, and United States National Aeronautics and Space Administration (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)
• Fluctuating properties of turbulent boundary layers for Mach numbers up to 9 / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by William D. Harvey, Ivan E. Beckwith, Dennis M. Bushnell, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Hypersonic aerodynamic characteristics of two Delta-wing X-15 airplane configurations / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Theodore J. Goldberg, David R. Stone, Jerry N. Hefner, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Flutter design of stiffened-skin panels for hypersonic aircraft / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Herman L. Bohon, Walter L. Heard, Melvin S. Anderson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Upwash patterns on ablating and nonablating cones at hypersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by John B. McDevitt, Jack A. Mellenthin, Ames 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)
• Effect of unit Reynolds number, nose bluntness, angle of attack, and roughness on transition on a 5° half-angle cone at Mach 8 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1969), by P. Calvin Stainback, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Preliminary surveys of the wall boundary layer in a Mach 6 axisymmetric tunnel / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1970]), by Robert A. Jones, William V. Feller, and Langley Research Center (page images at HathiTrust)
• Shock-wave shapes and surface pressures on hemisphere- and cone-cylinders in low-density hypersonic flow including ablation / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by Daryl J. Monson, Donald M. Kuehn, Ames 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)
• Starting phenomena for hypersonic inlets with thick turbulent boundary layers at Mach 6 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971), by Theodore J. Goldberg, Jerry N. Hefner, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Some aspects of air-helium simulation and hypersonic approximations / (Washington : National Aeronautics and Space Administration, [1959]), by Eugene S. Love, Mitchel H. Bertram, Arthur Henderson, and Langley Research Center (page images at HathiTrust)
• Shock-tube heat-transfer measurements on inner surface of a cylinder (simulating a flat plate) for stagnation-temperature range 4,100 ̊to 8,300 ̊R / (Washington : National Aeronautics and Space Administration, [1959]), by Jim J. Jones and Langley 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)
• Laminar boundary-layer separation induced by flares on cylinders with highly cooled boundary layers at a Mach number of 15 / (Washington, D.C. : National Aeronautics and Space Administration : For sale by the Office of Technical Services, Dept. of Commerce, [1965]), by Donald M. Kuehn and Ames Research Center (page images at HathiTrust)
• Dissociative relaxation of oxygen over an adiabatic flat plate at hypersonic Mach numbers / (Washington : National Aeronautics and Space Administration, [1960]), by Paul M. Chung, Aemer D. Anderson, and Ames Research Center (page images at HathiTrust)
• Analysis of nonequilibrium air streams in the Ames 1-foot shock tunnel [electronic resource] / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1969]), by Robert Smith Hiers, John O. Reller, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• Laminar skin-friction and heat-transfer parameters for a flat plate at hypersonic speeds in terms of free-stream flow properties / (Washington : National Aeronautics and Space Administration, [1959]), by James F. Schmidt and Lewis Research Center (page images at HathiTrust)
• Hypersonic rarefied flow over sharp slender cones / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1972), by M. I. Kussoy, Clifford C. Horstman, David A. Stewart, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Heat-transfer and pressure distributions on hemisphere-cylinders in methane-air combustion products at Mach 7 [electronic resource] / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Irving Weinstein, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Effects of wing elevation, incidence, and camber on the aerodynamic characteristics of a representative hypersonic cruise configuration at Mach numbers from 0.65 to 10.70, (Washington, National Aeronautics and Space Administration; [for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], 1970), by Walter P. Nelms and John A. Axelson (page images at HathiTrust; US access only)
• Effect of nose bluntness and controlled roughness on the flow on two hypersonic inlet center bodies without cowling at mach 5.98 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, U.S. G.P.O.], 1965), by James M. Cubbage and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Theoretical laminar convective heat transfer and boundary-layer characteristics on cones at speeds to 24 km/sec / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia], 1964), by Gary T. Chapman, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust; US access only)
• Longitudinal characteristics of several configurations at hypersonic Mach numbers in conical and contoured nozzles / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Office of Technical Services, Department of Commerce, Washington, D.C. 20230], 1964), by James P. Arrington, Arthur Henderson, Roy C. Joiner, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• A supersonic/hypersonic aerodynamic investigation of the Saturn IB/Apollo upper stage / (Washington, D.C. : National Aeronautics and Space Administration, 1966), by David R. Carlson and William P. Walters (page images at HathiTrust; US access only)
• Flow-field investigations on the X-15 airplane and model up to hypersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1968), by L. J. McLain, Murray Palitz, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Low-density, leading-edge bluntness, and ablation effects on wedge-induced laminar-boundary-layer separation at moderate enthalpies in hypersonic flow / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1968), by C. L. W. Edwards, John B. Anders, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Viscous hypersonic flow : theory of reacting and hypersonic boundary layers. (New York : McGraw-Hill, 1962), by William H. Dorrance (page images at HathiTrust)
• The hypersonic revolution : case studies in the history of hypersonic technology. (Bolling AFB, D.C. : Air Force History and Museums Program, 1998), by Larry Schweikart, Richard Hallion, and Air Force History and Museums Program (U.S.) (page images at HathiTrust)
• Supersonic flutter trends as revealed by piston theory calculations /, by Holt Ashley, Garabed Zartarian, United States. Air Force. Air Research and Development Command. sponsor, and Wright Air Development Center issuing body (page images at HathiTrust)
• The downstream influence of mass transfer at the nose of a slender cone /, by Robert J. Cresci, Paul A. Libby, sponsor United States. Air Force. Air Research and Development Command, issuing body Wright Air Development Division, and United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• Hypersonic free flight research. (Wright-Patterson Air Force Base, Ohio, Aeronautical Research Laboratories, Air Force Research Division, Air Research and Development Command, U. S. Air Force, 1960-), by Robert Worthington Bogle and Aerospace Research Laboratories (U.S.) (page images at HathiTrust)
• Investigation of feasibility of utilizing available heat resistant materials for hypersonic leading edge applications. (Wright-Patterson Air Force Base, Ohio, Wright Air Development Center, Air Research and Development Command, U. S. Air Force, 19-), by Bell Aircraft Corporation (page images at HathiTrust)
• Review of hypersonic research /, by Seymour M. Bogdonoff, United States. Air Force. Air Research and Development Command. sponsor, Wright Air Development Center issuing body, and Princeton University. Gas Dynamics Laboratory (page images at HathiTrust)
• An analysis of the applicability of the hypersonic similarity law to the study of flow about bodies of revolution at zero angle of attack / (Washington, D.C. : National Advisory Committee for Aeronautics, 1950), by Dorris M. Ehret, Victor I. Stevens, Vernon J. Rossow, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• The hypersonic revolution: eight case studies in the history of hypersonic technology / (Wright-Patterson Air Force Base, Oh. : Aeronautical Systems Division, 1987), by United States. Air Force. Systems Command. Aeronautical Systems Division and Richard Hallion (page images at HathiTrust; US access only)
• Telemeter transmission at 219.5 megacycles from two rocket-powered models at Mach number up to 15.7 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1958), by George B. Graves, J. Thomas Markley, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Hypersonic pitch-damping support using water-cooled ball bearings /, by Frank J Regan, Eugene V. Horanoff, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• A Program for computing steady inviscid three-dimensional supersonic flow on reentry vehicles : volume I : analysis and programming /, by J. M. Solomon, A. B Wardlaw, J. B. Bell, R. E. Ferguson, M. Ciment, and Naval Surface Weapons Center. White Oak Laboratory (page images at HathiTrust)
• Flutter at very high speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1957), by Harry L. Runyan, Homer G. Morgan, 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 study of hypersonic small-disturbance theory / (Washington, D.C. : National Advisory Committee for Aeronautics, 1954), by Milton Van Dyke and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Hypersonic plasma thermocouple / (Los Alamos, N.M. : Los Alamos Scientific Laboratory of the University of California, 1961), by Theodore Cotter, U.S. Atomic Energy Commission, and Los Alamos Scientific Laboratory (page images at HathiTrust)
• Status of Sandia Laboratory hypersonic facilities /, by R. C. Maydew, U.S. Atomic Energy Commission, and Sandia Corporation (page images at HathiTrust)
• Measurements of hypersonic turbulent heat transfer on a highly cooled cone /, by Donald M Wilson and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Stagnation point heat transfer from a viscous nongray radiating shock layer : including the applicability of step model absorption coefficients and sensitivity to uncertainties in transport properties /, by John D. Anderson and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• A hot-wire stagnation temperature probe /, by William Joseph Yanta and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• On hypersonic blunt body flow fields obtained with a time-dependent technique /, by John D. Anderson, Allen E. Winkelmann, Lorenzo M. Albacete, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Hypersonic-turbulent boundary-layer separation over a cone-cylinder-flare configuration /, by Arnold Polak, Chris A. Kalivretenos, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• On the hypersonic flow past blunted, flat delta wings /, by Arnold Polak and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Effects of a magnetic field on the hypervelocity flow about a blunt body /, by Richard W. Ziemer and inc. Space Technology Laboratories (page images at HathiTrust)
• Further studies on high-speed unsteady flow /, by Garabed Zartarian, Harry Sauerwein, issuing agency United States. Air Force. Systems Command. Aeronautical Systems Division, and sponsor Massachusetts Institute of Technology. Aeroelastic and Structures Research Laboratory (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)
• Flow regimes for hypervelocity vehicles /, by Anthony Casaccio, Edgar Bendor, sponsor Republic Aviation Corporation, and issuing body United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• Relationship between flutter parameters and generalized aerodynamic forces for wings of low aspect ratio /, by Bernard Mazelsky, Harry B. Amey, issuing agency United States. Air Force. Systems Command. Aeronautical Systems Division, and sponsor Aerojet-General Corporation (page images at HathiTrust)
• Skin friction, heat transfer, and pressure measurements on hypersonic inlet compression surfaces in the Mach number range 7.5 to 16 /, by M. O. Ryder, sponsor Cornell Aeronautical Laboratory, and sponsor Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Similarity studies for dissociating gases in hypersonic, low density flow /, by K. Pearce, R. J. Whalen, S. Samet, sponsor Air Force Flight Dynamics Laboratory (U.S.), sponsor United States. Wright Air Development Division, and United States. Air Force. Air Research and Development Command. issuing body (page images at HathiTrust)
• Investigation of ablation effects on hypersonic dynamic stability of a 10 cone /, by Dave R. Moore, Thomas C. Pope, Charles J. Stalmach, issuing agency Air Force Flight Dynamics Laboratory (U.S.), and sponsor LTV Aerospace Corporation (page images at HathiTrust)
• Preliminary design and experimental investigation of the FDL-5A unmanned high L/D spacecraft., by C. F. Ehrlich, C. M. Onspaugh, R. S. Peyton, J. J. Rising, issuing agency Air Force Flight Dynamics Laboratory (U.S.), and sponsor Lockheed-California Company (page images at HathiTrust)
• Preliminary design and experimental investigation of the FDL-5A unmanned high L/D spacecraft.., by F. L. Guard, H. D. Schultz, issuing agency Air Force Flight Dynamics Laboratory (U.S.), and sponsor Lockheed-California Company (page images at HathiTrust)
• The Mark IV Supersonic-Hypersonic Arbitrary-body Program., by Arvel E. Gentry, Wayne R. Oliver, Douglas N. Smyth, sponsor Air Force Flight Dynamics Laboratory (U.S.), and sponsor Douglas Aircraft Company (page images at HathiTrust)
• Supplementary note on modified-impact-theory calculations for bodies of revolution having minimum drag at hypersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, [1952]), by Meyer M. Resnikoff, United States. National Advisory Committee for Aeronautics. NACA research memorandum, and Ames Research Center (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)
• Proceedings of the Third Symposium on the Plasma Sheath-Plasma Electromagnetics of Hypersonic Flight / (Bedford, Mass. : Office of Aerospace Research, United States Air Force, 1967), by Symposium on the Plasma Sheath-Plasma Electromagnetics of Hypersonic Flight (3d : 1965 : Boston), Walter Rotman, and Air Force Cambridge Research Laboratories (U.S.). Microwave Physics Laboratory (page images at HathiTrust; US access only)
• Preliminary studies of manned satellites wingless configuration : nonlifting / (Washington, D.C. : National Advisory Committee for Aeronautics, 1958), by Maxime A. Faget, James J. Buglia, Benjamine J. Garland, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Mach tables for real gas equilibrium flow of air in hypervelocity test facilities with total temperatures to 10,000°K / (Albuquerque, New Mexico : Sandia Corporation, Technical Information Division ; Washington, D.C. : Available from the Office of Technical Services, Dept. of Commerce, [1961]), by Kennith L. Goin, U.S. Atomic Energy Commission, and Sandia Corporation (page images at HathiTrust)
• Theoretical prediction of pressures in hypersonic flow with special reference to configurations having attached leading-edge shock., by Harold R. Mead, Stavros A. Hartofilis, Frank Koch, issuing agency United States. Air Force. Systems Command. Aeronautical Systems Division, and sponsor Grumman Aircraft Engineering Corporation (page images at HathiTrust)
• Theoretical and experimental studies on airloads related to hypersonic aeroelastic problems of general slender pointed configurations /, by Garabed Zartarian, Pao Tan Hsu, issuing agency United States. Air Force. Systems Command. Aeronautical Systems Division, sponsor Air Force Flight Dynamics Laboratory (U.S.), and sponsor Massachusetts Institute of Technology. Aeroelastic and Structures Research Laboratory (page images at HathiTrust)
• Tests to determine subsonic aerodynamic characteristics of hypersonic re-entry configurations /, by K. Mantz, R. Ross, D. B. Seager, sponsor Aeronautical Systems Center (U.S.), issuing agency United States. Air Force. Systems Command. Aeronautical Systems Division, and sponsor Lockheed-California Company (page images at HathiTrust)
• The Mark IV Supersonic-Hypersonic Arbitrary-body Program., by Arvel E. Gentry, Wayne R. Oliver, Douglas N. Smyth, sponsor Air Force Flight Dynamics Laboratory (U.S.), and sponsor Douglas Aircraft Company (page images at HathiTrust)
• Thermal protection of structural, propulsion, and temperature-sensitive materials for hypersonic and space flight /, by William P. Manos, Anthony J. Tuzzolino, Donald E. Taylor, issuing body Wright Air Development Center, and sponsor United States. Air Force. Air Research and Development Command (page images at HathiTrust)
• Pressure and heat transfer measurements for hypersonic flows over expansion corners and ahead of ramps / (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, 1963-1964), by Louis G. Kaufman, sponsor Air Force Flight Dynamics Laboratory (U.S.), issuing agency United States. Air Force. Systems Command. Aeronautical Systems Division, and sponsor Grumman Aircraft Engineering Corporation. Research Department (page images at HathiTrust)
• Pressure and laminar heat transfer results in three-dimensional hypersonic flow /, by Victor Zakkay, sponsor United States. Air Force. Air Research and Development Command, issuing body Wright Air Development Center, and sponsor Polytechnic Institute of Brooklyn. Department of Aeronautical Engineering and Applied Mechanics (page images at HathiTrust)
• Development design methods for predicting hypersonic aerodynamic control characteristics /, by Z. Popinski, C. F. Ehrlich, sponsor Lockheed-California Company, and sponsor Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Wave propagation and the method of characteristics in reacting gas mixtures with applications to hypersonic flow /, by Boa-Teh Chu, sponsor United States. Air Force. Air Research and Development Command, issuing body Wright Air Development Center, and sponsor Brown University. Division of Engineering (page images at HathiTrust)
• Mark IV supersonic-hypsersonic arbitrary-body program modifications and computer graphics., by S. Taylor, sponsor Air Force Flight Dynamics Laboratory (U.S.), sponsor Air Force Wright Aeronautical Laboratories, and inc. Science Applications (page images at HathiTrust)
• A study of hypersonic aerodynamic drag devices : final technical report /, by W. B. Champney, issuing body Wright Air Development Center, and sponsor United States. Air Force. Air Research and Development Command (page images at HathiTrust)
• A review of some recent developments in hypersonic flow /, by Antonio Ferri, sponsor United States. Air Force. Air Research and Development Command, issuing body Wright Air Development Center, and sponsor Polytechnic Institute of Brooklyn (page images at HathiTrust)
• Investigation of hypersonic flow separation and its effects on aerodynamic control characteristics /, by Douglas E. Abbott, Jack N Nielsen, Maurice Holt, sponsor Itek Corporation, and sponsor United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• Critical evaluation of transition from laminar to turbulent shear layers with emphasis on hypersonically traveling bodies /, by Mark Vladimir Morkovin, issuing agency Air Force Flight Dynamics Laboratory (U.S.), and Md.) Research Institute for Advanced Study (Baltimore (page images at HathiTrust)
• Mark IV supersonic-hypsersonic arbitrary-body program modifications and computer graphics., by S. Taylor, sponsor Air Force Flight Dynamics Laboratory (U.S.), sponsor Air Force Wright Aeronautical Laboratories, and inc. Science Applications (page images at HathiTrust)
• Feasibility study of hypersonic parachute free flight test capability : phase I /, by B. A. Engstrom, W. M. Gran, sponsor Cook Electric Company. Cook Research Laboratories, and sponsor United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• Inviscid flow in the stagnation point region of very blunt-nosed bodies at hypersonic flight speeds /, by Ronald F. Probstein, sponsor United States. Air Force. Air Research and Development Command, issuing body Wright Air Development Center, and sponsor Brown University. Division of Engineering (page images at HathiTrust)
• An experimental investigation of the surface pressure and the laminar boundary layer on a blunt flat plate in hypersonic flow /, by G. M Gregorek, J. D. Lee, Theodore C. Nark, sponsor United States. Air Force. Systems Command. Aeronautical Systems Division, and sponsor Ohio State University (page images at HathiTrust)
• Results of ablation tests on several plastic models in a hypersonic wind tunnel /, by Constantino Economos, United States. Air Force. Air Research and Development Command. issuing agency, United States. Wright Air Development Center. sponsor, and sponsor Polytechnic Institute of Brooklyn (page images at HathiTrust)
• The blunt body viscous layer problem with and without an applied magnetic field /, by Hakurō Oguchi, United States. Air Force. Air Research and Development Command. issuing agency, United States. Wright Air Development Center. sponsor, and sponsor Brown University. Division of Engineering (page images at HathiTrust)
• Longitudinal aerodynamic characteristics of several fifth-stage scout reentry vehicles from Mach number 0.60 to 24.4 including some Reynolds number effects on stability at hypersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, 1963), by Patrick J. Johnston, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Turbulent heat transfer on blunt-nosed bodies in two-dimensional and general three-dimensional hypersonic flow /, by Roberto Vaglio-Laurin, sponsor United States. Air Force. Air Research and Development Command, issuing body Wright Air Development Center, and sponsor Polytechnic Institute of Brooklyn. Department of Aeronautical Engineering and Applied Mechanics (page images at HathiTrust)
• Tabulation of coordinates for hypersonic axisymmetric nozzles :, by Robert J. Cresci, sponsor United States. Air Force. Air Research and Development Command, issuing body Wright Air Development Center, and sponsor Polytechnic Institute of Brooklyn. Department of Aeronautical Engineering and Applied Mechanics (page images at HathiTrust)
• Conditions near a sonic line in rotational flow /, by Maurice Holt, sponsor United States. Air Force. Air Research and Development Command, issuing body Wright Air Development Center, and sponsor Brown University. Division of Engineering (page images at HathiTrust)
• Inversion of the Prandtl-Meyer relation for specific heat ratios of 5/3 and 5/4 /, by Ronald F. Probstein, sponsor United States. Air Force. Air Research and Development Command, issuing body Wright Air Development Center, and sponsor Brown University. Division of Engineering (page images at HathiTrust)
• Pressure measurement at Mach 19 for a winged re-entry configuration : part of an investigation of hypersonic flow separation and control characteristics /, by Stavros A. Hartofilis, issuing agency United States. Air Force. Systems Command. Aeronautical Systems Division, and sponsor Grumman Aircraft Engineering Corporation (page images at HathiTrust)
• Force balance determination of inlet performance for advanced vehicle applications to orbital velocities using internal drag measurements /, by Paul H. Kutschenreuter, sponsor United States. Air Force. Systems Command. Research and Technology Division, and issuing agency United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• Heat transfer to surfaces in the neighborhood of protuberances in hypersonic flow /, by M. H. Bloom, Adrian Pallone, sponsor United States. Air Force. Air Research and Development Command, issuing body Wright Air Development Center, and sponsor Polytechnic Institute of Brooklyn (page images at HathiTrust)
• Note on the flow fields on the rear part of blunt bodies in hypersonic flow /, by Antonio Ferri, Adrian Pallone, sponsor United States. Air Force. Air Research and Development Command, issuing body Wright Air Development Center, and sponsor Polytechnic Institute of Brooklyn (page images at HathiTrust)
• Design, calibration and simulation capability of the Rosemount aeronautical laboratories high temperature hypersonic facility /, by Rudolph Hermann, United States. Air Force. Air Research and Development Command. issuing agency, United States. Wright Air Development Center. sponsor, sponsor Aerospace Research Laboratories (U.S.), sponsor University of Minnesota, and sponsor Rosemount Aeronautical Laboratories (page images at HathiTrust)
• A review of the hypersonic research carried out at Princeton University from 1949-1955 /, by Seymour M. Bogdonoff, issuing body Wright Air Development Center, sponsor United States. Air Force. Air Research and Development Command, and sponsor Princeton University (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)
• Determination of factors governing selection and application of materials for ablation cooling of hypervelocity vehicles /, by John H. Bonin, Donald E. Taylor, Channon F. Price, issuing body Wright Air Development Center, and sponsor United States. Air Force. Air Research and Development Command (page images at HathiTrust; US access only)
• 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)
• An extension of estimated hypersonic flow parameters for helium as a real gas / (Washington, D.C. : National Aeronautics and Space Administration, 1963), by Wayne D. Erickson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Studies of microwave transmission through a hypersonic air plasma; final report. ([Albuquerque, N. M., Sandia Laboratories], 1967), by Donald Wayne Boyer, S. N. Andre, and G. P. Bein (page images at HathiTrust; US access only)
• Dominance of radiated aerodynamic noise on boundary-layer transition in supersonic-hypersonic wind tunnels : theory and application /, by Samuel R. Pate, United States. Air Force. Systems Command. issuing body, sponsor Arnold Engineering Development Center, and Inc. ARO (page images at HathiTrust)
• Study to determine aerodynamic characteristics on hypersonic re-entry configurations., by Frank S. Malvestuto, Vivan E. Huggins, Jules A. Larrivee, Herbert A. Mortzschky, William L. Marcy, Phillip J. Sullivan, Lockheed Aircraft Corporation. sponsor, United States. Air Force. Systems Command. Aeronautical Systems Division. issuing sponsor, and Air Force Flight Dynamics Laboratory (U.S.). issuing body (page images at HathiTrust)
• An experimental study of passive control of hypersonic cavity flow oscillations /, by D. S. Dolling, Y. L. Leu, S. W. Perng, sponsor University of Texas at Austin. Department of Aerospace Engineering and Engineering Mechanics, and issuing body United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• A Method of calculating turbulent-boundary-layer growth at hypersonic Mach numbers /, by James C. Sivells, Robert G. Payne, Inc. sponsor ARO, United States. Air Force. Arnold Air Force Base. sponsor, and Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• Artificially induced boundary-layer transition on blunt-slender cones using distributed roughness and spherical-type tripping devices at hypersonic speeds /, by A. H. Boudreau, United States. Air Force. Systems Command. issuing body, sponsor Arnold Engineering Development Center, and Inc. ARO (page images at HathiTrust)
• A computer study of hypersonic laminar boundary-layer/shock-wave interaction using the time-dependent compressible Navier-Stokes equations /, by B. K. Hodge, United States. Air Force. Systems Command. issuing body, sponsor Arnold Engineering Development Center, and Inc. ARO (page images at HathiTrust)
• An investigation of the effects of shock impingement on a blunt leading edge /, by A. D. Ray, R. L. Palko, Inc. sponsor ARO, United States. Air Force. Arnold Air Force Base. sponsor, and Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• Interaction of chemistry, turbulence, and shock waves in hypervelocity flow /, by Graham V. Candler, B. Sturtevant, D. I. Pullin, B. V. McKoy, Daniel I. Meiron, Anthony Leonard, H. G. Hornung, Paul E. Dimotakis, sponsor Daniel Guggenheim Aeronautical Laboratory, sponsor California Institute of Technology. Graduate Aeronautical Laboratories, and issuing body United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• An investigation of laminar, transitional and turbulent heat transfer on blunt-nosed bodies in hypersonic flow /, by Robert J. Cresci, Paul A. Libby, Donald A. MacKenzie, sponsor United States. Air Force. Air Research and Development Command, issuing body Wright Air Development Center, and Polytechnic Institute of Brooklyn. |b Department of Aerospace Engineering and Applied Mechanics. sponsor (page images at HathiTrust)
• A theoretical investigation on the use of combustion products for the simulation of hypersonic flow /, by Vito D. Agosta, sponsor United States. Air Force. Air Research and Development Command, issuing body Wright Air Development Center, and Polytechnic Institute of Brooklyn. |b Department of Aeronautical Engineering and Applied Mechanics. sponsor (page images at HathiTrust)
• Stability and transition analysis for reentry tool, STAR /, by Helen L. Reed, sponsor Texas A & M University. Aerospace Engineering Department, and issuing body United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Hypersonic lifting body windward surface flow-field analysis for high angles of incidence /, by John C. Adams, William R. Martindale, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• The shock shape and shock detachment distance for spheres and flat-faced bodies in low-density, hypervelocity, argon flow /, by A. B. Bailey, W. H. Sims, 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)
• Dynamic stability characteristics of a10-deg cone at Mach number 10 /, by A. E. Hodapp, G. E. Burt, B. L. Uselton, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Force and pressure tests of an AGARD Calibration Model B at a Mach number of 10 /, by R. K. Matthews, L. L Trimmer, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Problems underlying the numerical integration of the chemical and vibrational rate equations in a near-equilibrium flow /, by George Emanuel, sponsor Stanford University. Department of Aeronautics and Astronautics, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Method for calculation of the one-dimensional nonequilibrium flow of a general gas mixture through a hypersonic nozzle /, by George Emanuel, Walter G. Vincenti, sponsor Stanford University. Department of Aeronautics and Astronautics, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Analysis of the three-dimensional compressible turbulent boundary layer on a sharp cone at incidence in supersonic and hypersonic flow /, by John C. Adams, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Code validation studies of high-enthalpy flows /, by Graham V. Candler, Ioannis Nompelis, sponsor University of Minnesota. Department of Aerospace Engineering and Mechanics, and issuing body United States. Air Force. Office of Scientific Research (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)
• Magneto-aerodynamic hypersonics /, by F. Witzeman and Ohio). Air Vehicles Directorate Air Force Research Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
• Model-based feedback control of cavity resonance : an experimental and computational approach /, by Clarence W. Rowley, David R. Williams, sponsor Illinois Institute of Technology. Department of Mechanical and Aerospace Engineering, and issuing body United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• The influence of slight leading-edge bluntness on boundary-layer transition at a Mach number of eight /, by Jack D. Whitfield, J. Leith Potter, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Calibration tests of a Litton conical air data probe at Mach numbers of 2 to 8 /, by Scott R. Mallard, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Three-dimensional laminar boundary-layer analysis of upwash patterns and entrained vortex formation on sharp cones at angle of attack /, by John C. Adams, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Simulation of turbulent hypersonic flows : subgrid-scale model for the temperature fluctuations in reacting turbulence /, by Graham V. Candler, M. Pino Martin, sponsor University of Minnesota. Department of Aerospace Engineering and Mechanics, and issuing body United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Hypersonic force, pressure, and heat transfer investigations of sharp and blunt slender cones /, by David B. Wilkinson, Shelby A. Harrington, sponsor Cornell Aeronautical Laboratory, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Direct numerical simulation and experimental validation of hypersonic boundary-layer receptivity and instability /, by Xiaolin Zhong, Los Angeles. Mechanical University of California, and issuing body United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Summary report on aerodynamic characteristics of standard models HB-1 and HB-2 /, by J. Don Gray, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Pre-flight ground testing of the full-scale HIFiRE-1 at fully duplicated flight conditions /, by Tim P. Wadhams, Erik Mundy, Michael S. Holden, Matthew G. MacLean, and issuing body United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Further experiments on impact-pressure probes in a low-density, hypervelocity flow /, by A. B. Bailey, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Pressure distribution and flow visualization tests of a 1.5 elliptic cone at Mach 10 /, by R. L. Palko, A. D. Ray, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Force and pressure tests on cones with simulated ablated noses at Mach numbers 8 and 16 /, by J. S. Hahn, H. R. Little, Arnold Engineering Development Center. sponsor, United States. Air Force. Systems Command. issuing body, and Inc. ARO (page images at HathiTrust)
• Research on the effects of collisions of small particles with bodies moving at hypersonic speed., by G. Whitnah, D. Rosenberg, W Torgeson, Arie Gaalswyk, J. Upton, G. Wehner, United States. Air Force. Air Research and Development Command. issuing body, Wright Air Development Center sponsor, and Inc. General Mills (page images at HathiTrust)
• Hypersonic maneuvering vehicle simulations using real-aas, unstructured Navier-Stokes software /, by William D. McGrory, Inc. AeroSoft, and issuing body United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Nonequilibrium inviscid flow about blunt bodies /, by R. H. Lee, S. T. Chu, issuing body United States. Air Force. Systems Command. Space Systems Division, and sponsor Aerospace Corporation (page images at HathiTrust)
• Highly nonequilibrium boundary layer flows of a multicomponent dissociated gas mixture /, by G. I. Inger, issuing body United States. Air Force. Systems Command. Space Systems Division, and sponsor Aerospace Corporation (page images at HathiTrust)
• Theoretical prediction of pressures in hypersonic flow with special reference to configurations having attached leading-edge shock., by Richard A. Scheuing, Robert E. Melnik, John W. Brook, Harold R. Mead, Aeronautical Research Associates of Princeton. sponsor, Grumman Aircraft Engineering Corporation. sponsor, United States. Air Force. Systems Command. Aeronautical Systems Division. issuing body, United States. Air Force. Systems Command. Aeronautical Systems Division. Directorate of Materials and Processesd States. sponsor, and United States. Aerospace Medical Division. sponsor (page images at HathiTrust)
• Control of boundary layer instability in hypervelocity flow /, by H. G. Hornung, sponsor California Institute of Technology, and issuing body United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Automated design optimization for hypersonic plasma-aerodynamics /, by Ramakanth Munipalli, Jennifer D. Goss, Donald R Wilson, Shashi Aithal, Kamesh Subbarao, and issuing body United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• An automated design optimization tool for electromagnetic control of hypersonic flows /, by Lei Tang, John Schmisseur, K. Xu, Andre C. Marta, Juan J. Alonso, Danny D. Liu, Yun Zheng, and issuing body United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Theoretical analysis of the downstream influence of stagnation point mass transfer /, by Robert J. Cresci, issuing body United States. Air Force. Systems Command. Aeronautical Systems Division, sponsor Polytechnic Institute of Brooklyn, and sponsor United States. Wright Air Development Division (page images at HathiTrust)
• Effect of contact surface bluntness on massive blowing from a wedge in hypersonic flow /, by George Emanuel, issuing body United States. Air Force. Systems Command. Space Systems Division, and sponsor Aerospace Corporation (page images at HathiTrust)
• Axisymmetric hypersonic flow with strong viscous interaction /, by John Webster Ellinwood, Harold Mirels, issuing body United States. Air Force. Systems Command. Space Systems Division, and sponsor Aerospace Corporation (page images at HathiTrust)
• Calculation of the boundary-layer flow in the windward symmetry plane of a spherically blunted axisymmetric body at angle of attack, including streamline-swallowing effects /, by Arloe W. Mayne, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Development of test facilities for studies in hypersonic range., by Henry Halle, Channon F. Price, issuing body United States. Air Force. Air Research and Development Command, sponsor United States. Wright Air Development Division, and sponsor University of Chicago (page images at HathiTrust)
• Ablation and viscous effects on the force and moment characteristics of slender cone models at Mach 10 under laminar flow conditions /, by B. J. Griffith, B. M. Majors, W. T. Strike, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Development of test facilities for studies in hypersonic range., by Henry Halle, Channon F. Price, issuing body United States. Air Force. Air Research and Development Command, sponsor United States. Wright Air Development Division, and sponsor University of Chicago (page images at HathiTrust)
• Restricted variational principle method for the mixing of parallel low-density streams /, by Charles R. Ortloff, issuing body United States. Air Force. Systems Command. Space Systems Division, and sponsor Aerospace Corporation (page images at HathiTrust)
• Analysis of laminar boundary layers on right circular cones at angle of attack, including streamline-swallowing effects /, by Arloe Wesley Mayne, Inc ARO, and Arnold Engineering Development Center (page images at HathiTrust)
• Vortex calculations using extended potential flow theory /, by Robert W. Guyton, sponsor Wright Research and Development Center, sponsor Air Force Flight Dynamics Laboratory (U.S.), and issuing body United States. Air Force. Systems Command (page images at HathiTrust)
• Fluctuating pressure loads for hypersonic vehicle structures : phase I /, by Henry G. Lew, Anthony L. Laganelli, Ohio) Wright Laboratory (Wright-Patterson Air Force Base, and sponsor Science Applications International Corporation (page images at HathiTrust)
• Nonequilibrium hypersonic stagnation flow at low reynolds numbers /, by G. I. Inger, issuing body United States. Air Force. Systems Command. Space Systems Division, and sponsor Aerospace Corporation. Laboratory Operations (page images at HathiTrust)
• An efficient numerical method for three-dimensional hypersonic flow /, by R. W. MacCormack, Ohio) Wright Laboratory (Wright-Patterson Air Force Base, and sponsor Stanford University. Department of Aeronautics and Astronautics (page images at HathiTrust)
• Computation of viscous shock/shock hypersonic interactions with an implicit flux split scheme /, by Datta Gaitonde, Inc. Universal Energy Systems, Ohio) Wright Laboratory (Wright-Patterson Air Force Base, sponsor Air Force Flight Dynamics Laboratory (U.S.), and issuing body United States. Air Force. Systems Command (page images at HathiTrust)
• The effect of pressure gradients on transition zone length in hypersonic boundary layers /, by Roger L. Kimmel and Ohio) Wright Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
• Shock wave - turbulent boundary layer interaction in high speed flow /, by Michael S. Holden, issuing body Aerospace Research Laboratories (U.S.), and sponsor Calspan Corporation (page images at HathiTrust)
• Free flight hypersonic heat transfer and boundary layer transition studies: HTV flights A-40 and A-41 /, by James E. Brunk, Warren N. White, issuing body Aerospace Research Laboratories (U.S.), and sponsor Curtiss-Wright Corporation (page images at HathiTrust)
• A study of flow separation in regions of shock wave-boundary layer interaction in hypersonic flow /, by Michael S. Holden, issuing body Aerospace Research Laboratories (U.S.), and sponsor New York University. Aerospace and Energetics Laboratory (page images at HathiTrust)
• Experimental studies of high temperature hypersonic diffusers /, by Richard T. Smith, United States. Air Force. Systems Command. issuing body, and Air Force Flight Dynamics Laboratory (U.S.). sponsor (page images at HathiTrust)
• Investigation of combined low-angle jets and variable wall geometry for hypersonic aerodynamic control /, by Rodney D. W. Bowersox, University of Alabama. Department of Aerospace Engineering. sponsor, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• Hypersonic dynamic stability, by R. B. Hobbs, United States. Air Force. Systems Command. issuing body, Air Force Flight Dynamics Laboratory (U.S.). sponsor, and General Electric Company. sponsor (page images at HathiTrust)
• Nonlinear thermoelastic effects on hypersonic stability and control., by James R. Batt, United States. Air Force. Systems Command. issuing body, Air Force Flight Dynamics Laboratory (U.S.). sponsor, Wright-Patterson Air Force Base. Flight Dynamics Laboratory, and Bell Aircraft Corporation. sponsor (page images at HathiTrust)
• Flat-plate boundary-layer transition at hypersonic speeds /, by R. E. Deem, J. S. Murphy, C. R. Erickson, Air Force Flight Dynamics Laboratory (U.S.). sponsor, North American Aviation. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Comments on hypersonic boundary-layer transition /, by Kenneth F. Stetson, sponsor Wright Research and Development Center, sponsor Air Force Flight Dynamics Laboratory (U.S.), and issuing body United States. Air Force. Systems Command (page images at HathiTrust)
• A series solution to the laminar heat transfer problem at hypersonic speeds /, by Hung-Ta Ho, Ronald F. Probstein, issuing body United States. Air Force. Air Research and Development Command, sponsor Aerospace Research Laboratories (U.S.), and sponsor Brown University. Division of Engineering (page images at HathiTrust)
• Nonlinear thermoelastic effects on hypersonic stability and control., by James R. Batt, United States. Air Force. Systems Command. issuing body, Air Force Flight Dynamics Laboratory (U.S.). sponsor, and Wright-Patterson Air Force Base. Flight Dynamics Laboratory (page images at HathiTrust)
• Nonlinear thermoelastic effects on hypersonic stability and control., by James R. Batt, Richard H. Gallagher, United States. Air Force. Systems Command. issuing body, Air Force Flight Dynamics Laboratory (U.S.). sponsor, Wright-Patterson Air Force Base. Flight Dynamics Laboratory, and Bell Aircraft Corporation. sponsor (page images at HathiTrust)
• Theoretical prediction of pressures in hypersonic flow with special reference to configurations having attached leading-edge shock. Part 2. Experimental pressure measurements at Mach 5 and 8 /, by Harold R. Mead, Frank Koch, United States. Air Force. Systems Command. Aeronautical Systems Division. issuing body, United States. Air Force. Systems Command. Aeronautical Systems Division. Directorate of Materials and Processesd States. sponsor, United States. Aerospace Medical Division. sponsor, Grumman Aircraft Engineering Corporation, and Wright-Patterson Air Force Base (Ohio) (page images at HathiTrust)
• Pressure measurements for Mach five flows over a blunt pyramidal configuration with aerodynamic controls : part of an investigation of hypersonic flow separation and control characteristics /, by Louis G. Kaufman, United States. Air Force. Systems Command. issuing body, Air Force Flight Dynamics Laboratory (U.S.). sponsor, and Grumman Aircraft Engineering Corporation. Research Department. sponsor (page images at HathiTrust)
• Low-density flow effects for hypervelocity vehicles : phase II /, by Roop N. Gupta, Sudheer N. Nayani, Inc. ViGYAN, sponsor Wright Research and Development Center, sponsor Air Force Flight Dynamics Laboratory (U.S.), and issuing body United States. Air Force. Systems Command (page images at HathiTrust)
• Hypersonic dynamic stability., by L. A. Marshall, United States. Air Force. Systems Command. issuing body, and Air Force Flight Dynamics Laboratory (U.S.). sponsor (page images at HathiTrust)
• On the hypersonic flow over a delta wing with very supersonic leading edges /, by N. Malmuth, United States. Air Force. Office of Scientific Research. issuing body, and North American Aviation. sponsor (page images at HathiTrust)
• Low-density stagnation-point heat transfer in hypersonic air flow /, by Charles F. Wittliff, Merle R. Wilson, issuing body Aerospace Research Laboratories (U.S.), and sponsor Cornell Aeronautical Laboratory (page images at HathiTrust)
• Separation ahead of controls on swept wings /, by II Kaufman Louis G., L. Michael Freeman, and issuing body Aerospace Research Laboratories (U.S.) (page images at HathiTrust)
• Three-dimensional shock wave-turbulent boundary layer interactions at Mach 6 /, by C. Herbert Law and issuing body Aerospace Research Laboratories (U.S.) (page images at HathiTrust)
• DNS studies of transitional hypersonic reacting flows over 3-D hypersonic vehicles /, by Xiaolin Zhong, Los Angeles. Mechanical University of California, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• Similitude of hypersonic flows over thin and slender bodies; an extension to real gases /, by Hsien K. Cheng, issuing body United States. Air Force. Office of Scientific Research, and sponsor Cornell Aeronautical Laboratory (page images at HathiTrust)
• Research on hypersonic stability problems /, by O. Walchner, issuing body Aerospace Research Laboratories (U.S.), and United States. Air Force. Office of Aerospace Research (page images at HathiTrust)
• A Correlation of artifically induced boundary-layer transition data from blunt slender cones at hypersonic speeds /, by A. H. Boudreau, 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)
• Some heat transfer problems in hypersonic flow /, by Antonio Ferri, issuing body United States. Air Force. Air Research and Development Command, and sponsor Polytechnic Institute of Brooklyn (page images at HathiTrust)
• Separated flow studies /, by Wilbur L. Hankey and issuing body Aerospace Research Laboratories (U.S.) (page images at HathiTrust)
• Stability derivatives of a 10° cone executing planar and nonplanar motion at Mach 14 /, by Kevin E. Yelmgren, Otto Walchner, Frank M. Sawyer, issuing body Aerospace Research Laboratories (U.S.), and sponsor Hypersonic Research Laboratory (U.S.) (page images at HathiTrust)
• Parametric study of hypersonic turbulent boundary layers with heat transfer /, by J. S. Shang, issuing body Aerospace Research Laboratories (U.S.), and sponsor Hypersonic Research Laboratory (U.S.) (page images at HathiTrust)
• Real-gas effects on the aerodynamics of blunt cones as measured in a hypervelocity range /, by C. J. Welsh, 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)

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