The Online Books Page

Aerodynamics, Hypersonic -- Computer programs

See also what's at your library, or elsewhere.

• Aerodynamics, Hypersonic
• Aerodynamics, Supersonic -- Computer programs
• Sound pressure -- Computer programs
• Aerodynamics -- Computer programs
• Computer programs

• Aerodynamics, Hypersonic -- Computer programs -- Handbooks, manuals, etc.

• NSEG : a segmented mission analysis program for low and high speed aircraft (National Aeronautics and Space Administration ;, 1977), by D. S. Hague, H. L. Rozendaal, Aerophysics Research Corporation, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• The Mark IV Supersonic-Hypersonic Arbitrary-body Program. Volume II, Program formulation (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1973., 1973), by Arvel E. Gentry, Wayne R. Oliver, Douglas N. Smyth, Air Force Flight Dynamics Laboratory (U.S.), and Douglas Aircraft Company (page images at HathiTrust)
• The Mark IV Supersonic-Hypersonic Arbitrary-body Program. Volume I, User's manual (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1973., 1973), by Arvel E. Gentry, Wayne R. Oliver, Douglas N. Smyth, Air Force Flight Dynamics Laboratory (U.S.), and Douglas Aircraft Company (page images at HathiTrust)

• Computer user's guide for a chemically reacting viscous shock-layer program (National Aeronautics and Space Administration ;, 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)

Items below (if any) are from related and broader terms.

• Viscous hypersonic flow : theory of reacting and hypersonic boundary layers. (McGraw-Hill, 1962), by William H. Dorrance (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. (U.S. G.P.O., 1985), by Aviation United States. Congress. House. Committee on Science and Technology. Subcommittee on Transportation (page images at HathiTrust)
• Hypersonic dynamic stability. (Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, 1967), by General Electric Company (page images at HathiTrust)
• Hypersonic free flight research. (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 Air Development Center, Air Research and Development Command, U. S. Air Force, 1900), by Bell Aircraft Corporation (page images at HathiTrust)
• The blunt-body problem in hypersonic flow at low Reynolds number. (Cornell Aeronautical Laboratory, Inc., 1963), by Hsien Kei Cheng (page images at HathiTrust)
• Hypersonic flow with combined leading-edge bluntness and boundary-layer displacement effect. (Cornell Aeronautical Laboratory, 1960), by Hsien Kei Cheng (page images at HathiTrust)
• Expansion of gas clouds and hypersonic jets bounded by a vacuum. (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)
• 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. (Physical Research Laboratory, Space Technology Laboratories, 1960), by Richard W. Ziemer (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)
• Wave superheater hypersonic tunnel; semiannual report (Buffalo, 1959), by Cornell Aeronautical Laboratory and James E. Carpenter (page images at HathiTrust)
• Studies of microwave transmission through a hypersonic air plasma; final report ([Sandia Laboratories], 1967), by Donald Wayne Boyer, S. N. Andre, and G. P. Bein (page images at HathiTrust; US access only)
• The shock layer concept and three-dimensional hypersonic boundary layers. (Cornell Aeronautical Laboratory, 1961), by Hsien Kei Cheng (page images at HathiTrust)
• Effects of ambient nonuniformities in flow over hypersonic test bodies. (Cornell Aeronautical Laboratory, Inc., 1963), by J. Gordon Hall (page images at HathiTrust)
• Instrumentation for force and pressure measurements in a hypersonic shock tunnel (Cornell Aeronautical Laboratory, Inc., 1962), by James F. Martin, Leroy M. Stevenson, and George R. Duryea (page images at HathiTrust)
• Radiation at hypersonic speeds. (Cornell Aeronautical Laboratory, 1961), by Charles E. Treanor (page images at HathiTrust)
• Aerothermodynamic consequences of nozzle nonequilibrium (Arnold Engineering Development Center, Air Force Systems Command, 1966), by A. F. Burke and J. E. Wallace (page images at HathiTrust)
• Nonequilibrium scaling criterion for inviscid hypersonic airflows (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 (Cornell Aeronautical Laboratory, Inc., 1962), by Walter E. Gibson, Paul V. Marrone, and Cornell Aeronautical Laboratory (page images at HathiTrust)
• Theoretical analysis of the downstream influence of stagnation point mass transfer (Wright-Patterson Air Force Base, Ohio, Aeronautical Systems Division, Air Force Systems Command, U.S. Air Force, 1961., 1961), by Robert J. Cresci, United States. Air Force. Systems Command. Aeronautical Systems Division, Polytechnic Institute of Brooklyn, and United States. Wright Air Development Division (page images at HathiTrust)
• An investigation of laminar heat transfer to slender cones in the hypersonic shock tunnel (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. (Aerospace Corp., 1962), by Harold Mirels, Mullen James Francis, and Aerospace Corporation (page images at HathiTrust)
• An analysis of nonequilibrium inviscid flow (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 (Guggenheim Aeronautical Laboratory, California Institute of Technology, 1958), by Howard K. McMahon (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 (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1965., 1965), by M. O. Ryder, Cornell Aeronautical Laboratory, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• On the hypersonic flow over a delta wing with very supersonic leading edges (Los Angeles, California : North American Aviation Inc., Los Angeles Division, 1965., 1965), by N. Malmuth, United States. Air Force. Office of Scientific Research, and North American Aviation (page images at HathiTrust)
• Variational approach to problems of hypervelocity flight; final report. (Purdue University, School of Aeronautical Engineering, 1959), by Angelo Miele (page images at HathiTrust; US access only)
• Investigation of test time at undertailored conditions in a shock tunnel. (Cornell Aeronautical Laboratory, Inc., 1950), by James F. Martin and Cornell Aeronautical Laboratory Hypersonic Research Department (page images at HathiTrust)
• Summary of research results: Hypersonic Research Laboratory, 1 July 1969 - 31 December 1971. (Aerospace Research Laboratories, Air Force Systems Command, 1972), by Hypersonic Research Laboratory (U.S.) (page images at HathiTrust; US access only)
• Study of hypersonic contaminated wake by an exact numerical solution. (Missile and Space Division, General Electric, 1963), by Huon Li and Philadelphia General Electric Company. Space Sciences Laboratory (page images at HathiTrust)
• Investigation of ablation effects on hypersonic dynamic stability of a 10 cone (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1967., 1967), by Dave R. Moore, Thomas C. Pope, Charles J. Stalmach, Air Force Flight Dynamics Laboratory (U.S.), and LTV Aerospace Corporation (page images at HathiTrust)
• On local flat-plate similarity in the hypersonic boundary layer (Cornell Aeronautical Laboratory, Inc. of Cornell Laboratory, 1960), by Franklin Kingston Moore (page images at HathiTrust)
• Comparison of turbulent wake characteristics with different eddy viscosity coefficients (Missile and Space Division, General Electric, 1963), by K. S. Wan and Philadelphia General Electric Company. Space Sciences Laboratory (page images at HathiTrust)
• The Hypersonic revolution : eight case studies in the history of hypersonic technology (Special Staff Office, Aeronautical Systems Division, 1987), by John Vernon Becker, Richard Hallion, and United States. Air Force. Systems Command. Aeronautical Systems Division. Special Staff Office (page images at HathiTrust)
• Effect of Reynolds number variation on aerodynamics of a hydrogen-fueled transport concept at Mach 6 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 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 (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)
• Fluctuating pressures measured beneath a high-temperature, turbulent boundary layer on a flat plate at a Mach number of 5 (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1989), by Tony L. Parrott, Cindy W. Albertson, Michael G. Jones, and Langley Research Center (page images at HathiTrust)
• Measured and predicted aerodynamic coefficients and shock shapes for Aeroassist Flight Experiment (AFE) configuration (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by William L. Wells 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 (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by L. Roane Hunt, Kristopher K. Notestine, 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 (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 (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ;, 1991), by A. Robert Porro and Lewis 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 (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 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 (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1991), by John J. Korte and Langley Research Center (page images at HathiTrust)
• Loading tests of a wing structure for a hypersonic aircraft (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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)
• Data on effects of incident-reflecting shocks on the turbulent boundary layer (National Aeronautics and Space Administration ;, 1966), by S. Z. Pinckney and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Aerothermal test results from the first flight of the Pegasus air-launched space booster (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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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)
• An analysis of combustion studies in shock expansion tunnels and reflected shock tunnels (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)
• Experimental and analytical study of an inlet forebody for an airframe-integrated scramjet concept (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 1975), by Peter T. Bernot and Langley Research Center (page images at HathiTrust)
• NASA Aerodynamics Program : annual report 1990 (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)
• Measured pressure distributions, aerodynamic coefficients, and shock shapes on blunt bodies at incidence in hypersonic air and CF₄ (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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)
• Aerodynamic characteristics of two single-stage-to-orbit vehicles at Mach 20.3 (National Aeronautics and Space Administration ;, 1977), by Peter T. Bernot and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Longitudinal aerodynamic characteristics at Mach 0.60 to 2.86 of a fighter configuration with strut braced wing (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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 (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 (U.S. National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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)
• Aerodynamic characteristics at Mach number 0.2 of a wing-body concept for a hypersonic research airplane (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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)
• Real-time aerodynamic heating and surface temperature calculations for hypersonic flight simulation (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Robert D. Quinn, Leslie Gong, and Dryden Flight Research Facility (page images at HathiTrust)
• Drag and distribution measurements of single-element fuel injectors for supersonic combustors (National Aeronautics and Space Administration ;, 1974), by Louis A. Povinelli and Lewis Research Center (page images at HathiTrust)
• A method for calculating a real-gas two-dimensional nozzle contour including the effects of gamma (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Peter T. Bernot and Langley Research Center (page images at HathiTrust)
• Hypersonic characteristics of an advanced aerospace plane at Mach 20.3 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Ronald S. McCandless 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 (National Aeronautics and Space Administration, Scientific and Technical Informaion Branch;, 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)
• Longitudinal aerodynamic characteristics of a fighter model with a close-coupled canard at Mach numbers from 0.40 to 1.20 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration ;, 1969), by S. Kranc, A. B. Cambel, M. C. Yuen, and Ill.) Northwestern University (Evanston (page images at HathiTrust)
• Assessment of a transitional boundary layer theory at low hypersonic mach numbers (National Aeronautics and Space Administration ;, 1972), by S. J. Shamroth, H. McDonald, Langley Research Center, and United Aircraft Corporation (page images at HathiTrust)
• A study of boundary layer transition on outgassing cones in hypersonic flow (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)
• Stagnation point heat transfer during hypervelocity atmospheric entry (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 1969), by Lars E. Ericsson, J. Peter Reding, Lockheed Missiles and Space Company, and Langley Research Center (page images at HathiTrust)
• A supersonic/hypersonic aerodynamic investigation of the Saturn IB/Apollo upper stage (National Aeronautics and Space Administration, 1966), by David R. Carlson and William P. Walters (page images at HathiTrust; US access only)
• Airfoil at supersonic mach number (National Aeronautics and Space Administration, 1965), by Lucien A. Schmit, William A. Thornton, Case Institute of Technology, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• High performance hypersonic decelerator for planetary entry (NASA, 1965), by A. C. Kyser, Astro Research Corporation, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Coned rotating net (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)
• Analysis of hypersonic pressure and heat transfer tests on delta wings with laminar and turbulent boundary layers (National Aeronautics and Space Administration, 1966), by A. L. Nagel, L. B. Doyle, H. D. Fitzsimmons, and Langley Research Center (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 (National Aeronautics and Space Administration :, 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 (U.S. National Aeronautics and Space Administration ;, 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 (U.S. National Aeronautics and Space Administration ;, 1976), by Frank Marconi, Larry Yaeger, United States National Aeronautics and Space Administration, Langley Research Center, and Grumman Aerospace Corporation (page images at HathiTrust)
• Analytical comparison of hypersonic flight and wind tunnel viscous/inviscid flow fields (National Aeronautics and Space Administration ;, 1975), by H. J. Fivel, L. J. Mockapetris, R. V. Masek, Langley Research Center, and McDonnell Douglas Astronautics Company-East (page images at HathiTrust)
• Simulation of hypersonic scramjet exhaust (National Aeronautics and Space Administration ;, 1975), by R. A. Oman, Langley Research Center, and Grumman Aerospace Corporation (page images at HathiTrust)
• A study of surface pressure fluctuations in hypersonic turbulent boundary layers (National Aeronautics and Space Administration ;, 1974), by K. R. Raman, Ames Research Center, and Nielsen Engineering & Research (page images at HathiTrust)
• Method for obtaining aerodynamic data on hypersonic configurations with scramjet exhaust flow simulation (National Aeronautics and Space Administration ;, 1977), by William R. Hartill and United States National Aeronautics and Space Administration (page images at HathiTrust)
• High L/D concept with single pivot two position skewed wing (National Aeronautics and Space Administration ;, 1970), by B. J. Kuchta, Langley Research Center, and General Dynamics Corporation (page images at HathiTrust)
• Theoretical and experimental studies of reentry plasmas (National Aeronautics and Space Administration ;, 1973), by M. G. Dunn, Sang-Wook Kang, Langley Research Center, and Cornell Aeronautical Laboratory (page images at HathiTrust)
• Viscous computations of cold air/air flow around scramjet nozzle afterbody (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ;, 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 (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)
• Nonparallel instability of supersonic and hypersonic boundary layers (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1991), by Nabil M. El-Hady, Langley Research Center, and Inc Analytical Services & Materials (page images at HathiTrust)
• Thermal-structural design study of an airframe-integrated scramjet : summary report (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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)
• Flow separation in shock wave boundary layer interactions at hypersonic speeds (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by A. Hamed, Langley Research Center, and Joint Institute for Advancement of Flight Sciences (page images at HathiTrust)
• NASA TR R-311 (National Aeronautics and Space Administration ;, 1969), by Richard W. Barnwell, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust; US access only)
• Use of tetrafluoromethane to simulate real-gas effects on the hypersonic aerodynamics of blunt vehicles (National Aeronautics and Space Administration ;, 1969), by Robert A. Jones and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TR R-368 (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)
• Calculated radio attenuation due to plasma sheath on hypersonic blunt-nosed cone (National Aeronautics and Space Administration, 1963), by John S. Evans, Paul W. Huber, and Langley Research Center (page images at HathiTrust)
• Hypersonic viscous shock layer of nonequilibrium dissociating gas (National Aeronautics and Space Administration ;, 1961), by Paul M. Chung (page images at HathiTrust)
• NASA TN D-2019 (National Aeronautics and Space Administration, 1963), by Frank L. Clark, Charles B. Johnson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-1978 (National Aeronautics and Space Administration, 1963), by Roger A. Craig, William C. Davey, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-1979 (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)
• NASA TR R-163 (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)
• Prospects for obtaining aerodynamic heating results from analysis of meteor flight data (National Aeronautics and Space Administration :, 1964), by H. Julian Allen, Nataline A. James, and Ames Research Center (page images at HathiTrust)
• Design and performance at a local Mach number of 6 of an inlet for an integrated scramjet concept (National Aeronautics and Space Administration ;, 1975), by Carl A. Trexler, Sue W. Souders, and Langley 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 (National Aeronautics and Space Administration, 1960), by G. G. Chernyĭ (page images at HathiTrust)
• NASA TN D-2463 (National Aeronautics and Space Administration :, 1964), by Gary T. Chapman, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust; US access only)
• NASA TN D-2489 (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)
• Weak incident shock interactions with Mach 8 laminar boundary layers (National Aeronautics and Space Administration ;, 1974), by Louis G. Kaufman, Charles B. Johnson, and Langley Research Center (page images at HathiTrust)
• NASA TN D-4128 (National Aeronautics and Space Administration ;, 1967), by Frank S. Kirkham and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Transition fixing for hypersonic flow (National Aeronautics and Space Administration ;, 1967), by James R. Sterrett and Langley Research Center (page images at HathiTrust)
• Secondary flow fields embedded in hypersonic shock layers (National Aeronautics and Space Administration :, 1962), by Alvin Seiff and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Surface pressure distributions with a sonic jet normal to adjacent flat surfaces at Mach 2.92 to 6.4 (National Aeronautics and Space Administration, 1961), by Robert W. Cubbison, James J. Ward, Bernhard H. Anderson, and Lewis Research Center (page images at HathiTrust)
• A parametric study of the aerodynamic characteristics of nose-cylinder-flare bodies at a Mach number of 6.0 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 1968), by Aubrey M. Cary, E. Leon Morrisette, and Langley Research Center (page images at HathiTrust)
• NASA TN D-4367 (National Aeronautics and Space Administration ;, 1968), by Davis H. Crawford, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• NASA TN D-4079 (National Aeronautics and Space Administration ;, 1967), by Bernard Spencer, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Real-gas correction factors for hypersonic flow parameters in helium. (National Aeronautics and Space Administration :, 1960), by Wayne D. Erickson and United States National Aeronautics and Space Administration (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 (National Aeronautics and Space Administration ;, 1975), by Charles G. Miller and Langley Research Center (page images at HathiTrust)
• Experimental investigation of a Mach 6 fixed-geometry inlet featuring a swept external-internal compression flow field (National Aeronautics and Space Administration ;, 1975), by Marvin G. Torrence 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 1975), by William D. Harvey, William W. Hunter, 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 (National Aeronautics and Space Administration ;, 1975), by Charles G. Miller and Langley Research Center (page images at HathiTrust)
• Investigation of the aerodynamic characteristics of a hypersonic transport model at Mach numbers to 6 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1971), by James C. Ellison, 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 (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)
• NASA TN D-5768 (National Aeronautics and Space Administration :, 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)
• NASA TN D-5788 (National Aeronautics and Space Administration :, 1970), by Joseph H. Kemp, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-5861 (National Aeronautics and Space Administration :, 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)
• Exploratory study of transient unstart phenomena in a three-dimensional fixed-geometry scramjet engine (U.S. National Aeronautics and Space Administration ;, 1976), by Allan R. Wieting and Langley Research Center (page images at HathiTrust)
• NASA TN D-6005 (National Aeronautics and Space Administration :, 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)
• NASA TN D-6017 (National Aeronautics and Space Administration :, 1970), by Roger M. Winebarger, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-5433 (National Aeronautics and Space Administration ;, 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)
• NASA TN D-5948 (National Aeronautics and Space Administration :, 1970), by Gerard E. Woodbury, W. Douglas Morris, 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 (National Aeronautics and Space Administration ;, 1965), by Chester H. Wolowicz, Terrence D. Gossett, and Flight Research Center (U.S.) (page images at HathiTrust)
• NASA TN D-5885 (National Aeronautics and Space Administration :, 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)
• NASA TN D-5893 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 1977), by Langley Research Center and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5438 (National Aeronautics and Space Administration ;, 1969), by Waldo I. Oehman, Sylvia A. Wallace, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5937 (National Aeronautics and Space Administration ;, 1970), by Leonard M. Weinstein, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-5638 (National Aeronautics and Space Administration :, 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)
• NASA TN D-5496 (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)
• NASA TN D-5498 (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)
• NASA TN D-5555 (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)
• NASA TN D-5346 (National Aeronautics and Space Administration ;, 1969), by John B. McDevitt, Jack A. Mellenthin, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5454 (National Aeronautics and Space Administration ;, 1969), by Allen H. Whitehead, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-4961 (National Aeronautics and Space Administration ;, 1969), by P. Calvin Stainback, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Discrete sonic jets used as boundary-layer trips at Mach numbers of 6 and 8.5 (National Aeronautics and Space Administration ;, 1972), by David R. Stone, Aubrey M. Cary, United States National Aeronautics and Space Administration, and Langley Research Center (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 (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 (National Aeronautics and Space Administration, 1960), by Ruth N. Weltmann, Perry W. Kuhns, and Lewis Research Center (page images at HathiTrust)
• Preliminary surveys of the wall boundary layer in a Mach 6 axisymmetric tunnel (National Aeronautics and Space Administration ;, 1970), by Robert A. Jones, William V. Feller, and Langley Research Center (page images at HathiTrust)
• Hypersonic and transonic buzz measurements on the lower pitch flap of M2-F2 lifting entry configuration (National Aeronautics and Space Administration ;, 1972), by Robert W. Warner, Phillip R. Wilcox, United States National Aeronautics and Space Administration, 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration, 1962), by James R. Sterrett, James C. Emery, and Langley Research Center (page images at HathiTrust)
• Effect of geometry variations on lee-surface vortex-induced heating for flat-bottom three-dimensional bodies at Mach 6 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 1974), by P. Calvin Stainback and Langley Research Center (page images at HathiTrust)
• Hot-wire anemometry in hypersonic helium flow (National Aeronautics and Space Administration ;, 1974), by Richard D. Wagner, Leonard M. Weinstein, and Langley Research Center (page images at HathiTrust)
• NASA TN D-7002 (National Aeronautics and Space Administration ; [For sale for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1971), by Sherwood Hoffman, Joseph J. Janos, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-5721 (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)
• 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 (National Aeronautics and Space Administration, 1961), by Frank A. Pfyl, Leroy L. Presley, and Ames Research Center (page images at HathiTrust)
• Investigation of flow fields within large-scale hypersonic inlet models (National Aeronautics and Space Administration ;, 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)
• Hypersonic aerodynamics and entry-maneuver--aerothermodynamic interactions for two lifting entry vehicles (National Aeronautics and Space Administration ;, 1972), by James P. Arrington, William C. Woods, 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 (National Aeronautics and Space Administration :, 1971), by Walter P. Nelms, Charles L. Thomas, Ames Research Center, and United States National Aeronautics and Space Administration (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 (National Aeronautics and Space Administration ;, 1974), by David R. Stone, Bernard Spencer, 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 (National Aeronautics and Space Administration ;, 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. (National Aeronautics and Space Administration :, 1962), by John V. Becker, Peter F. Korycinski, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Interference heating from interactions of shock waves with turbulent boundary layers at Mach 6 (National Aeronautics and Space Administration ;, 1974), by Charles B. Johnson, Louis G. Kaufman, and Langley Research Center (page images at HathiTrust)
• Experimental study of sharp- and blunt-nose streamwise corners at Mach 20 (National Aeronautics and Space Administration ;, 1974), by Ralph D. Watson and Langley Research Center (page images at HathiTrust)
• A theoretical and experimental study of hypersonic flow over flared bodies at incidence (National Aeronautics and Space Administration ;, 1966), by John V. Rakich, Gene P. Menees, and Ames Research Center (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 (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)
• Comparisons of two-dimensional shock-expansion theory with experimental aerodynamic data for delta-planform wings at high supersonic speeds (National Aeronautics and Space Administration ;, 1974), by Lloyd S. Jernell and Langley Research Center (page images at HathiTrust)
• NASA TN D-6280 (National Aeronautics and Space Administration ;, 1971), by Theodore J. Goldberg, Jerry N. Hefner, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Studies of optimum body shapes at hypersonic speeds (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)
• 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 (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 (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 (National Aeronautics and Space Administration :, 1965), by Donald M. Kuehn 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 (National Aeronautics and Space Administration ;, 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 (National Aeronautics and Space Administration ;, 1965), by Dennis M. Bushnell and Langley Research Center (page images at HathiTrust)
• Analysis of nonequilibrium air streams in the Ames 1-foot shock tunnel (National Aeronautics and Space Administration ;, 1969), by Robert Smith Hiers, John O. Reller, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• NASA TN D-1632 (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)
• NASA TN D-1638 (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)
• NASA TN D-2900 (National Aeronautics and Space Administration :, 1965), by James M. Cubbage and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-1963 (National Aeronautics and Space Administration, 1963), by Bernard Spencer, W. Pelham Phillips, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Pilot model expansion tunnel test flow properties obtained from velocity, pressure, and probe measurements (National Aeronautics and Space Administration ;, 1973), by Wilfred J. Friesen, John A. Moore, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Engineering prediction of turbulent skin friction and heat transfer in high-speed flow (National Aeronautics and Space Administration ;, 1974), by Aubrey M. Cary, Mitchel H. Bertram, 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 (National Aeronautics and Space Administration ;, 1972), by Lionel L. Levy, Raymond K. Burns, and Ames Research Center (page images at HathiTrust)
• Analytical and experimental studies of shock interference heating in hypersonic flows (National Aeronautics and Space Administration ;, 1973), by J. Wayne Keyes, Frank D. Hains, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• NASA TN D-6689 (National Aeronautics and Space Administration :, 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)
• Aerodynamic heating and loading within large open cavities in cone and cone-cyclinder-flare models at Mach 6.7 (National Aeronautics and Space Administration ;, 1974), by L. Roane Hunt and Langley Research Center (page images at HathiTrust)
• Heat-transfer and pressure distributions on hemisphere-cylinders in methane-air combustion products at Mach 7 (National Aeronautics and Space Administration ;, 1973), by Irving Weinstein, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Evaluation of compressible-flow Preston tube calibrations (National Aeronautics and Space Administration ;, 1973), by Jerry M. Allen and Langley Research Center (page images at HathiTrust)
• Investigation of an anomalous flow condition of the Langley pilot model expansion tube (National Aeronautics and Space Administration ;, 1974), by Wilfred J. Friesen and Langley Research Center (page images at HathiTrust)
• A parametric study of effect of forebody shape on flow angularity at Mach 8 (National Aeronautics and Space Administration ;, 1974), by Charles B. Johnson, Don C. Marcum, and Langley Research Center (page images at HathiTrust)
• Aerodynamic drag and fuel spreading measurements in a simulated scramjet combustion module (National Aeronautics and Space Administration ;, 1974), by Louis A. Povinelli and Lewis Research Center (page images at HathiTrust)
• 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 (National Aeronautics and Space Administration, 1961), by Philip E. Everhart, Peter T. Bernot, and Langley Research Center (page images at HathiTrust)
• Pressure measurements on a hypersonic glide configuration having 79.5 degree sweepback and 45 degree dihedral at a Mach number of 4.95 (National Aeronautics and Space Administration, 1959), by Morton Cooper, Charles R. Gunn, 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 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 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)
• Supplementary note on modified-impact-theory calculations for bodies of revolution having minimum drag at hypersonic speeds (National Advisory Committee for Aeronautics, 1952), by Meyer M. Resnikoff and Ames Research Center (page images at HathiTrust)
• Flutter at very high speeds (National Advisory Committee for Aeronautics, 1957), by Harry L. Runyan, Homer G. Morgan, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Telemeter transmission at 219.5 megacycles from two rocket-powered models at Mach number up to 15.7 (National Advisory Committee for Aeronautics, 1958), by George B. Graves, J. Thomas Markley, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Preliminary studies of manned satellites wingless configuration : nonlifting (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 (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 (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)
• A study of hypersonic small-disturbance theory (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 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)
• Hypersonic longitudinal trim, stability, and control characteristics of a delta-wing configuration at high angles of attack (National Aeronautics and Space Administration, 1960), by William H. Close and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Static stability characteristics of three thick wing models with parabolic plan forms at mach number of 3.11 (National Aeronautics and Space Administration, 1959), by M. J. Queijo and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Investigation of the rolling stability derivatives of two hypersonic gliders of parabolic plan form at high subsonic speeds (National Aeronautics and Space Administration, 1960), by Donald D. Arabian and United States National Aeronautics and Space Administration (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 (National Advisory Committee for Aeronautics, 1954), by Thomas N. Canning, Ames Research Center, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Kinetic study of the hypersonic flow past the leading edge of a flat plate. (Dept. of Computer Science ;, 1968), by Rateb Jaber El Assar (page images at HathiTrust)
• Mach tables for real gas equilibrium flow of air in hypervelocity test facilities with total temperatures to 10,000°K (Sandia Corporation, Technical Information Division ;, 1961), by Kennith L. Goin, U.S. Atomic Energy Commission, and Sandia Corporation (page images at HathiTrust)
• Gas dynamics in space exploration ; [scientific papers] (National Aeronautics and Space Administration, Office of Scientific and Technical Information ; [for sale by the Superintendent of Documents, U.S.Govt. Print.Off.], 1963), by Chicago NASA-University Conference on the Science and Technology of Space Exploration (page images at HathiTrust)
• Measurements of hypersonic turbulent heat transfer on a highly cooled cone (White Oak, Maryland : United States Naval Ordnance Laboratory, 1967., 1967), 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 (White Oak, Maryland : United States Naval Ordnance Laboratory, 1967., 1967), by John D. Anderson and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Hypersonic pitch-damping support using water-cooled ball bearings (White Oak, Maryland : United States Naval Ordnance Laboratory, 1968., 1968), by Frank J. Regan, Eugene V. Horanoff, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• A hot-wire stagnation temperature probe (White Oak, Maryland : United States Naval Ordnance Laboratory, 1968., 1968), 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 (White Oak, Maryland : United States Naval Ordnance Laboratory, 1968., 1968), 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 (White Oak, Maryland : United States Naval Ordnance Laboratory, 1969., 1969), 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 (White Oak, Maryland : United States Naval Ordnance Laboratory, 1970., 1970), 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 (Los Angeles : Physical Research Laboratory, Space Technology Laboratories, 1958., 1958), by Richard W. Ziemer and inc Space Technology Laboratories (page images at HathiTrust)
• A Program for computing steady inviscid three-dimensional supersonic flow on reentry vehicles : volume I : analysis and programming (Silver Spring, Maryland : Naval Surface Weapons Center, White Oak Laboratory, 1977., 1977), 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)
• The downstream influence of mass transfer at the nose of a slender cone (Wright-Patterson Air Force Base, Ohio : Aeronautical Systems Division, Air Force Systems Command, U.S. Air Force, 1961., 1962), by Robert J. Cresci, Paul A. Libby, United States. Air Force. Air Research and Development Command, Wright Air Development Division, and United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• Supersonic flutter trends as revealed by piston theory calculations (Wright Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1958., 1958), by Holt Ashley, Garabed Zartarian, United States. Air Force. Air Research and Development Command, and Wright Air Development Center (page images at HathiTrust)
• Review of hypersonic research (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1958., 1958), by Seymour M. Bogdonoff, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Princeton University. Gas Dynamics Laboratory (page images at HathiTrust)
• An investigation of laminar, transitional and turbulent heat transfer on blunt-nosed bodies in hypersonic flow (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1959., 1959), by Robert J. Cresci, Paul A. Libby, Donald A. MacKenzie, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Polytechnic Institute of Brooklyn. |b Department of Aerospace Engineering and Applied Mechanics (page images at HathiTrust)
• Turbulent heat transfer on blunt-nosed bodies in two-dimensional and general three-dimensional hypersonic flow (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1958., 1958), by Roberto Vaglio-Laurin, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Polytechnic Institute of Brooklyn. Department of Aeronautical Engineering and Applied Mechanics (page images at HathiTrust)
• Tabulation of coordinates for hypersonic axisymmetric nozzles : Part 1, Analysis and coordinates for test section Mach numbers of 8, 12 and 20 (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1958., 1958), by Robert J. Cresci, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Polytechnic Institute of Brooklyn. Department of Aeronautical Engineering and Applied Mechanics (page images at HathiTrust)
• Thermal protection of structural, propulsion, and temperature-sensitive materials for hypersonic and space flight (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1960., 1960), by William P. Manos, Anthony J. Tuzzolino, Donald E. Taylor, Wright Air Development Center, and United States. Air Force. Air Research and Development Command (page images at HathiTrust)
• Preliminary design and experimental investigation of the FDL-5A unmanned high L/D spacecraft. Part III, Aerodynamics (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1968., 1968), by C. F. Ehrlich, C. M. Onspaugh, R. S. Peyton, J. J. Rising, Air Force Flight Dynamics Laboratory (U.S.), and Lockheed-California Company (page images at HathiTrust)
• Preliminary design and experimental investigation of the FDL-5A unmanned high L/D spacecraft.. Part IV, Aerothermodynamics (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1968., 1968), by F. L. Guard, H. D. Schultz, Air Force Flight Dynamics Laboratory (U.S.), and Lockheed-California Company (page images at HathiTrust)
• Heat transfer to surfaces in the neighborhood of protuberances in hypersonic flow (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1957., 1957), by M. H. Bloom, Adrian Pallone, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Polytechnic Institute of Brooklyn (page images at HathiTrust)
• Further studies on high-speed unsteady flow (Wright-Patterson Air Force Systems Base, Ohio : Flight Dynamics Laboratory, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1962., 1962), by Garabed Zartarian, Harry Sauerwein, United States. Air Force. Systems Command. Aeronautical Systems Division, and Massachusetts Institute of Technology. Aeroelastic and Structures Research Laboratory (page images at HathiTrust)
• Pressure and heat transfer measurements for hypersonic flows over expansion corners and ahead of ramps (Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, 1963), by Louis G. Kaufman, Air Force Flight Dynamics Laboratory (U.S.), United States. Air Force. Systems Command. Aeronautical Systems Division, and Grumman Aircraft Engineering Corporation. Research Department (page images at HathiTrust)
• Pressure and laminar heat transfer results in three-dimensional hypersonic flow (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1958., 1958), by Victor Zakkay, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Polytechnic Institute of Brooklyn. Department of Aeronautical Engineering and Applied Mechanics (page images at HathiTrust)
• Conditions near a sonic line in rotational flow (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research Development and Command, United States Air Force, 1956., 1956), by Maurice Holt, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Brown University. Division of Engineering (page images at HathiTrust)
• Development design methods for predicting hypersonic aerodynamic control characteristics (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1966., 1966), by Z. Popinski, C. F. Ehrlich, Lockheed-California Company, and Air Force Flight Dynamics Laboratory (U.S.) (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 (Wright-Patterson Air Force Base, Ohio : Flight Control Division, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1963., 1963), by Stavros A. Hartofilis, United States. Air Force. Systems Command. Aeronautical Systems Division, and 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 (Wright-Patterson Air Force Base, Ohio : Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1963., 1963), by Paul H. Kutschenreuter, United States. Air Force. Systems Command. Research and Technology Division, and United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• Similarity studies for dissociating gases in hypersonic, low density flow (Wright Patterson Air Force Base, Ohio : Wright Air Development Division, Air Research and Development Command, United States Air Force, 1960., 1960), by K. Pearce, R. J. Whalen, S. Samet, Air Force Flight Dynamics Laboratory (U.S.), United States. Wright Air Development Division, and United States. Air Force. Air Research and Development Command (page images at HathiTrust)
• Wave propagation and the method of characteristics in reacting gas mixtures with applications to hypersonic flow (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research Development and Command, United States Air Force, 1957., 1957), by Boa-Teh Chu, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Brown University. Division of Engineering (page images at HathiTrust)
• Theoretical and experimental studies on airloads related to hypersonic aeroelastic problems of general slender pointed configurations (Wright-Patterson Air Force Base, Ohio : Aeronautical Systems Division, Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1961., 1961), by Garabed Zartarian, Pao Tan Hsu, United States. Air Force. Systems Command. Aeronautical Systems Division, Air Force Flight Dynamics Laboratory (U.S.), and Massachusetts Institute of Technology. Aeroelastic and Structures Research Laboratory (page images at HathiTrust)
• Flow regimes for hypervelocity vehicles (Wright-Patterson Air Force Base, Ohio : Directorate of Aeromechanics, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1962., 1962), by Anthony Casaccio, Edgar Bendor, Republic Aviation Corporation, and United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• A theoretical investigation on the use of combustion products for the simulation of hypersonic flow (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1959., 1959), by Vito D. Agosta, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Polytechnic Institute of Brooklyn. |b Department of Aeronautical Engineering and Applied Mechanics (page images at HathiTrust)
• Feasibility study of hypersonic parachute free flight test capability : phase I (Wright-Patterson Air Force Base, Ohio : Flight Accessories Laboratory, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1962., 1962), by B. A. Engstrom, W. M. Gran, Cook Electric Company. Cook Research Laboratories, and United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• A study of hypersonic aerodynamic drag devices : final technical report (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1960., 1960), by W. B. Champney, Wright Air Development Center, and United States. Air Force. Air Research and Development Command (page images at HathiTrust)
• Relationship between flutter parameters and generalized aerodynamic forces for wings of low aspect ratio (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1962., 1962), by Bernard Mazelsky, Harry B. Amey, United States. Air Force. Systems Command. Aeronautical Systems Division, and Aerojet-General Corporation (page images at HathiTrust)
• Tests to determine subsonic aerodynamic characteristics of hypersonic re-entry configurations (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1963., 1963), by K. Mantz, R. Ross, D. B. Seager, Aeronautical Systems Center (U.S.), United States. Air Force. Systems Command. Aeronautical Systems Division, and Lockheed-California Company (page images at HathiTrust)
• Note on the flow fields on the rear part of blunt bodies in hypersonic flow (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1956., 1956), by Antonio Ferri, Adrian Pallone, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Polytechnic Institute of Brooklyn (page images at HathiTrust)
• Design, calibration and simulation capability of the Rosemount aeronautical laboratories high temperature hypersonic facility (Wright-Patterson Air Force Base, Ohio : Aeronautical Research Laboratories, Air Force Research Division, Air Research and Development Command, United States Air Force, 1960., 1960), by Rudolph Hermann, United States. Air Force. Air Research and Development Command, United States. Wright Air Development Center, Aerospace Research Laboratories (U.S.), University of Minnesota, and Rosemount Aeronautical Laboratories (page images at HathiTrust)
• An experimental investigation of the surface pressure and the laminar boundary layer on a blunt flat plate in hypersonic flow (Wright-Patterson Air Force Base, Ohio : Fluid Dynamics Laboratory, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1963., 1963), by G. M. Gregorek, J. D. Lee, Theodore C. Nark, United States. Air Force. Systems Command. Aeronautical Systems Division, and Ohio State University (page images at HathiTrust)
• Results of ablation tests on several plastic models in a hypersonic wind tunnel (Wright-Patterson Air Force Base, Ohio : Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1961., 1961), by Constantino Economos, United States. Air Force. Air Research and Development Command, United States. Wright Air Development Center, and Polytechnic Institute of Brooklyn (page images at HathiTrust)
• The blunt body viscous layer problem with and without an applied magnetic field (Wright-Patterson Air Force Base, Ohio : Wright Air Development Division, Air Research and Development Command, United States Air Force, 1960., 1960), by Hakurō Oguchi, United States. Air Force. Air Research and Development Command, United States. Wright Air Development Center, and Brown University. Division of Engineering (page images at HathiTrust)
• Determination of factors governing selection and application of materials for ablation cooling of hypervelocity vehicles (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1959., 1959), by John H. Bonin, Donald E. Taylor, Channon F. Price, Wright Air Development Center, and United States. Air Force. Air Research and Development Command (page images at HathiTrust; US access only)
• A review of the hypersonic research carried out at Princeton University from 1949-1955 (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1956., 1956), by Seymour M. Bogdonoff, Wright Air Development Center, United States. Air Force. Air Research and Development Command, and Princeton University (page images at HathiTrust)
• Inversion of the Prandtl-Meyer relation for specific heat ratios of 5/3 and 5/4 (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research Development and Command, United States Air Force, 1956., 1956), by Ronald F. Probstein, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Brown University. Division of Engineering (page images at HathiTrust)
• Shock wave - turbulent boundary layer interaction in high speed flow (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, United States Air Force, 1975., 1975), by Michael S. Holden, Aerospace Research Laboratories (U.S.), and Calspan Corporation (page images at HathiTrust)
• Investigation of combined low-angle jets and variable wall geometry for hypersonic aerodynamic control (Arlington, Virginia : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 2004., 2004), by Rodney D. W. Bowersox, University of Alabama. Department of Aerospace Engineering, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Low-density stagnation-point heat transfer in hypersonic air flow (Wright-Patterson Air Force Base, Ohio : Aeronautical Research Laboratory, Air Force Research Division, Air Research and Development Command, United States Air Force, 1961., 1961), by Charles F. Wittliff, Merle R. Wilson, Aerospace Research Laboratories (U.S.), and Cornell Aeronautical Laboratory (page images at HathiTrust)
• Force and pressure tests on cones with simulated ablated noses at Mach numbers 8 and 16 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1972., 1972), by J. S. Hahn, H. R. Little, Arnold Engineering Development Center, United States. Air Force. Systems Command, and Inc ARO (page images at HathiTrust)
• Dominance of radiated aerodynamic noise on boundary-layer transition in supersonic-hypersonic wind tunnels : theory and application (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Von Karman Gas Dynamics Facility, Air Force Systems Command, United States Air Force, 1978., 1978), by Samuel R. Pate, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
• Effect of contact surface bluntness on massive blowing from a wedge in hypersonic flow (Los Angeles, California : Space Systems and Ballistic Systems Divisions, Los Angeles Air Force Station, Air Force Systems Command, United States Air Force, 1966., 1966), by George Emanuel, United States. Air Force. Systems Command. Space Systems Division, and Aerospace Corporation (page images at HathiTrust)
• Stability and transition analysis for reentry tool, STAR (Arlington, Virginia. : Air Force Office of Scientific Research, 2006., 2006), by Helen L. Reed, Texas A & M University. Aerospace Engineering Department, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Axisymmetric hypersonic flow with strong viscous interaction (Los Angeles, California : Space Systems and Ballistic Systems Divisions, Los Angeles Air Force Station, Air Force Systems Command, United States Air Force, 1967., 1967), by John Webster Ellinwood, Harold Mirels, United States. Air Force. Systems Command. Space Systems Division, and Aerospace Corporation (page images at HathiTrust)
• Research on the effects of collisions of small particles with bodies moving at hypersonic speed. PART II Erosion and heat transfer effects (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1959., 1959), by G. Whitnah, D. Rosenberg, W. Torgeson, Arie Gaalswyk, J. Upton, G. Wehner, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Inc General Mills (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 (Arnold Air Force Base, Tennessee : Von Kármán Gas Dynamics Facility, Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1973., 1973), by Arloe W. Mayne, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Hypersonic maneuvering vehicle simulations using real-aas, unstructured Navier-Stokes software (Arlington, Virginia. : Air Force Office of Scientific Research, 2001., 2001), by William D. McGrory, Inc AeroSoft, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Hypersonic dynamic stability Part II. Conical body experimental program (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1967., 1967), by R. B. Hobbs, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and General Electric Company (page images at HathiTrust)
• Nonlinear thermoelastic effects on hypersonic stability and control. Part 1, Volume 1. Aerodynamics (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1964., 1964), by James R. Batt, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), Wright-Patterson Air Force Base. Flight Dynamics Laboratory, and Bell Aircraft Corporation (page images at HathiTrust)
• Study to determine aerodynamic characteristics on hypersonic re-entry configurations. Part II--Analytical Phase, Volume 2--Design Charts (Wright-Patterson Air Force Base, Ohio : Aeronautical Systems Division, Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1962., 1962), by Frank S. Malvestuto, Vivan E. Huggins, Jules A. Larrivee, Herbert A. Mortzschky, William L. Marcy, Phillip J. Sullivan, Lockheed Aircraft Corporation, United States. Air Force. Systems Command. Aeronautical Systems Division, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• A study of flow separation in regions of shock wave-boundary layer interaction in hypersonic flow (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, 1975., 1975), by Michael S. Holden, Aerospace Research Laboratories (U.S.), and New York University. Aerospace and Energetics Laboratory (page images at HathiTrust)
• Separation ahead of controls on swept wings (Wright-Patterson Air Force Base, Ohio : Aeronautical Research Laboratories, Air Force Systems Command, 1975., 1975), by II Kaufman Louis G., L. Michael Freeman, and Aerospace Research Laboratories (U.S.) (page images at HathiTrust)
• Three-dimensional shock wave-turbulent boundary layer interactions at Mach 6 (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, United States Air Force, 1975., 1975), by C. Herbert Law and Aerospace Research Laboratories (U.S.) (page images at HathiTrust)
• Development of test facilities for studies in hypersonic range. Part II (Wright-Patterson Air Force Base, Ohio : Wright Air Development Division, Air Research and Development Command, United States Air Force, 1960., 1960), by Henry Halle, Channon F. Price, United States. Air Force. Air Research and Development Command, United States. Wright Air Development Division, and University of Chicago (page images at HathiTrust)
• Flat-plate boundary-layer transition at hypersonic speeds (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1964., 1964), by R. E. Deem, J. S. Murphy, C. R. Erickson, Air Force Flight Dynamics Laboratory (U.S.), North American Aviation, and United States. Air Force. Systems Command (page images at HathiTrust)
• Hypersonic lifting body windward surface flow-field analysis for high angles of incidence (Arnold Air Force Base, Tennessee : Von Kármán Gas Dynamics Facility, Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1973., 1973), by John C. Adams, William R. Martindale, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• The shock shape and shock detachment distance for spheres and flat-faced bodies in low-density, hypervelocity, argon flow (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1963., 1963), by A. B. Bailey, W. H. Sims, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• DNS studies of transitional hypersonic reacting flows over 3-D hypersonic vehicles (Arlington, Virginia : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 2003., 2003), by Xiaolin Zhong, Los Angeles. Mechanical University of California, and United States. Air Force. Office of Scientific Research (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 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1975., 1975), by B. J. Griffith, B. M. Majors, W. T. Strike, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• An experimental study of passive control of hypersonic cavity flow oscillations (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, Aerospace Sciences, 1998., 1998), by D. S. Dolling, Y. L. Leu, S. W. Perng, University of Texas at Austin. Department of Aerospace Engineering and Engineering Mechanics, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Experimental determination of aerodynamic drag on a blunted 10-deg cone at angles of attack in hypersonic, rarefied flow (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1964., 1964), by David E. Boylan, William H. Sims, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Comments on hypersonic boundary-layer transition (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Wright Research and Development Center, Air Force Systems Command, United States Air Force, 1990., 1990), by Kenneth F. Stetson, Wright Research and Development Center, Air Force Flight Dynamics Laboratory (U.S.), and United States. Air Force. Systems Command (page images at HathiTrust)
• Development of test facilities for studies in hypersonic range. Part I (Wright-Patterson Air Force Base, Ohio : Wright Air Development Division, Air Research and Development Command, United States Air Force, 1960., 1960), by Henry Halle, Channon F. Price, United States. Air Force. Air Research and Development Command, United States. Wright Air Development Division, and University of Chicago (page images at HathiTrust)
• Restricted variational principle method for the mixing of parallel low-density streams (Los Angeles, California : Space Systems and Ballistic Systems Divisions, Los Angeles Air Force Station, Air Force Systems Command, United States Air Force, 1967., 1967), by Charles R. Ortloff, United States. Air Force. Systems Command. Space Systems Division, and Aerospace Corporation (page images at HathiTrust)
• Similitude of hypersonic flows over thin and slender bodies; an extension to real gases (Buffalo, New York : Cornell Aeronautical Laboratory, 1958., 1958), by Hsien K. Cheng, United States. Air Force. Office of Scientific Research, and Cornell Aeronautical Laboratory (page images at HathiTrust)
• A series solution to the laminar heat transfer problem at hypersonic speeds (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1958., 1958), by Hung-Ta Ho, Ronald F. Probstein, United States. Air Force. Air Research and Development Command, Aerospace Research Laboratories (U.S.), and Brown University. Division of Engineering (page images at HathiTrust)
• Research on hypersonic stability problems (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, United States Air Force, 1974., 1974), by O. Walchner, Aerospace Research Laboratories (U.S.), and United States. Air Force. Office of Aerospace Research (page images at HathiTrust)
• Analysis of laminar boundary layers on right circular cones at angle of attack, including streamline-swallowing effects (Arnold Air Force Station, Tennessee : Von Kármán Gas Dynamics Facility, Arnold Engineering Development Center, Air Force Systems Command, 1972., 1972), by Arloe Wesley Mayne, Inc ARO, and Arnold Engineering Development Center (page images at HathiTrust)
• Dynamic stability characteristics of a10-deg cone at Mach number 10 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1964., 1964), by A. E. Hodapp, G. E. Burt, B. L. Uselton, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Force and pressure tests of an AGARD Calibration Model B at a Mach number of 10 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1964., 1964), by R. K. Matthews, L. L Trimmer, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• A Method of calculating turbulent-boundary-layer growth at hypersonic Mach numbers (Arnold Air Force Base, Tennessee, Arnold Engineering Development Center, Air Research and Development Command, United States Air Force, 1959., 1959), by James C. Sivells, Robert G. Payne, Inc ARO, United States. Air Force. Arnold Air Force Base, and Arnold Engineering Development Center (page images at HathiTrust)
• A Correlation of artifically induced boundary-layer transition data from blunt slender cones at hypersonic speeds (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Von Kármán Gas Dynamics Facility, Air Force Systems Command, United States Air Force, 1979., 1979), by A. H. Boudreau, Inc ARO, United States. Air Force. Arnold Air Force Base, and Arnold Engineering Development Center (page images at HathiTrust)
• Vortex calculations using extended potential flow theory (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, United States Air Force, 1989, 1989), by Robert W. Guyton, Wright Research and Development Center, Air Force Flight Dynamics Laboratory (U.S.), and United States. Air Force. Systems Command (page images at HathiTrust)
• Problems underlying the numerical integration of the chemical and vibrational rate equations in a near-equilibrium flow (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1963., 1963), by George Emanuel, Stanford University. Department of Aeronautics and Astronautics, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Some heat transfer problems in hypersonic flow ([Brooklyn, New York] : Polytechnic Institute of Brooklyn, Department of Aeronautical Engineering and Applied Mechanics, [1959], 1959), by Antonio Ferri, United States. Air Force. Air Research and Development Command, and Polytechnic Institute of Brooklyn (page images at HathiTrust)
• Artificially induced boundary-layer transition on blunt-slender cones using distributed roughness and spherical-type tripping devices at hypersonic speeds (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Von Karman Gas Dynamics Facility, Air Force Systems Command, United States Air Force, 1978., 1978), by A. H. Boudreau, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
• Nonlinear thermoelastic effects on hypersonic stability and control. Part III. Simulation, measurement and analysis of nonlinear static aerothermoelastic behavior of a 45 degrees delta wing (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1965., 1965), by James R. Batt, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Wright-Patterson Air Force Base. Flight Dynamics Laboratory (page images at HathiTrust)
• Fluctuating pressure loads for hypersonic vehicle structures : phase I (Wright-Patterson Air Force Base, Ohio : Fliight Dynamics Directorate, Wright Laboratory, Air Force Systems Command, 1991, 1991), by Henry G. Lew, Anthony L. Laganelli, Ohio) Wright Laboratory (Wright-Patterson Air Force Base, and Science Applications International Corporation (page images at HathiTrust)
• Method for calculation of the one-dimensional nonequilibrium flow of a general gas mixture through a hypersonic nozzle (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1962., 1962), by George Emanuel, Walter G. Vincenti, Stanford University. Department of Aeronautics and Astronautics, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• A computer study of hypersonic laminar boundary-layer/shock-wave interaction using the time-dependent compressible Navier-Stokes equations (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Von Darman Gas Dynamics Facility, Air Force Systems Command, United States Air Force, 1976., 1976), by B. K. Hodge, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
• Nonlinear thermoelastic effects on hypersonic stability and control. Part II. Analytical and experimental static aerothermoelasticity (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1964., 1964), by James R. Batt, Richard H. Gallagher, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), Wright-Patterson Air Force Base. Flight Dynamics Laboratory, and Bell Aircraft Corporation (page images at HathiTrust)
• Analysis of the three-dimensional compressible turbulent boundary layer on a sharp cone at incidence in supersonic and hypersonic flow (Arnold Air Force Base, Tennessee : Von Kármán Gas Dynamics Facility, Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1972., 1972), by John C. Adams, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• A study of flow fields about some typical blunt-nosed slender bodies (Brooklyn, New York : Polytechnic Institute of Brooklyn, Department of Aerospace Engineering and Applied Mechanics, 1960., 1960), by Roberto Vaglio-Laurin, Massimo Trella, United States. Air Force. Office of Scientific Research, and Polytechnic Institute of Brooklyn. Department of Aerospace Engineering and Applied Mechanics (page images at HathiTrust)
• Code validation studies of high-enthalpy flows (Arlington, Virginia. : Air Force Office of Scientific Research, 2006., 2006), by Graham V. Candler, Ioannis Nompelis, University of Minnesota. Department of Aerospace Engineering and Mechanics, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Nonequilibrium inviscid flow about blunt bodies (Inglewood, California : Space Systems Division, Air Force Systems Command, United States Air Force, 1964., 1964), by R. H. Lee, S. T. Chu, United States. Air Force. Systems Command. Space Systems Division, and Aerospace Corporation (page images at HathiTrust)
• Longitudinal force charactristics of two AFFDL MDF-4 high lift-to-drag configurations at Mach number 19 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1964., 1964), by A. R. Wallace, L. G. Siler, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Nonequilibrium hypersonic stagnation flow at low reynolds numbers (Los Angeles, California : Ballistic Systems and Space Systems Divisions, Los Angeles Air Force Station, Air Force Systems Command, United States Air Force, 1964., 1964), by G. I. Inger, United States. Air Force. Systems Command. Space Systems Division, and Aerospace Corporation. Laboratory Operations (page images at HathiTrust)
• An efficient numerical method for three-dimensional hypersonic flow (Wright-Patterson Air Force Base, Ohio : Fliight Dynamics Directorate, Wright Laboratory, Air Force Materiel Command, 1993., 1993), by R. W. MacCormack, Ohio) Wright Laboratory (Wright-Patterson Air Force Base, and Stanford University. Department of Aeronautics and Astronautics (page images at HathiTrust)
• Separated flow studies (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, 1975., 1975), by Wilbur L. Hankey and Aerospace Research Laboratories (U.S.) (page images at HathiTrust)
• Magneto-aerodynamic hypersonics (Wright Patterson Air Force Base, Ohio : Air Vehicles Directorte, Air Force Research Laboratory, Air Force Materiel Command, 2003., 2003), 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 (Arlington, Virginia. : Air Force Office of Scientific Research, 2006., 2006), by Clarence W. Rowley, David R. Williams, Illinois Institute of Technology. Department of Mechanical and Aerospace Engineering, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Computation of viscous shock/shock hypersonic interactions with an implicit flux split scheme (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Wright Laboratory, Air Force Systems Command, United States Air Force, 1990., 1990), by Datta V. Gaitonde, Inc Universal Energy Systems, Ohio) Wright Laboratory (Wright-Patterson Air Force Base, Air Force Flight Dynamics Laboratory (U.S.), and United States. Air Force. Systems Command (page images at HathiTrust)
• Highly nonequilibrium boundary layer flows of a multicomponent dissociated gas mixture (Inglewood, California : Space Systems Division, Air Force Systems Command, United States Air Force, 1963., 1963), by G. I. Inger, United States. Air Force. Systems Command. Space Systems Division, and Aerospace Corporation (page images at HathiTrust)
• The influence of slight leading-edge bluntness on boundary-layer transition at a Mach number of eight (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1964., 1964), by Jack D. Whitfield, J. Leith Potter, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Stability derivatives of a 10° cone executing planar and nonplanar motion at Mach 14 (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Hypersonic Research Laboratory, Air Force Systems Commany, 1974., 1974), by Kevin E. Yelmgren, Otto Walchner, Frank M. Sawyer, Aerospace Research Laboratories (U.S.), and Hypersonic Research Laboratory (U.S.) (page images at HathiTrust)
• Calibration tests of a Litton conical air data probe at Mach numbers of 2 to 8 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1962., 1962), by Scott R. Mallard, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Three-dimensional laminar boundary-layer analysis of upwash patterns and entrained vortex formation on sharp cones at angle of attack (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1971., 1971), by John C. Adams, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Parametric study of hypersonic turbulent boundary layers with heat transfer (Wright-Patterson Air Force Base, Ohio : Aeronautical Research Laboratories, Hypersonic Research Laboratory, Air Force Systems Command, United States Air Force, 1974., 1974), by J. S. Shang, Aerospace Research Laboratories (U.S.), and Hypersonic Research Laboratory (U.S.) (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 (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1964., 1964), by Louis G. Kaufman, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Grumman Aircraft Engineering Corporation. Research Department (page images at HathiTrust)
• The effect of pressure gradients on transition zone length in hypersonic boundary layers (Wright Patterson Air Force Base, Ohio : Flight Dynamics Directorate , Wright Laboratory, Air Force Materiel Command, United States Air Force, 1993., 1993), by Roger L. Kimmel and Ohio) Wright Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
• Control of boundary layer instability in hypervelocity flow (Bolling Air Force Base, DC. : Air Force Office of Scientific Research, 2002., 2002), by H. G. Hornung, California Institute of Technology, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Low-density flow effects for hypervelocity vehicles : phase II (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Wright Research Development Center, United States Air Force Systems Command, 1990., 1990), by Roop N. Gupta, Sudheer N. Nayani, Inc ViGYAN, Wright Research and Development Center, Air Force Flight Dynamics Laboratory (U.S.), and United States. Air Force. Systems Command (page images at HathiTrust)
• Hypersonic dynamic stability. Part I. Summary (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1967., 1967), by L. A. Marshall, United States. Air Force. Systems Command, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Simulation of turbulent hypersonic flows : subgrid-scale model for the temperature fluctuations in reacting turbulence (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, 1997., 1997), by Graham V. Candler, M. Pino Martin, University of Minnesota. Department of Aerospace Engineering and Mechanics, and 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 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1963., 1963), by David B. Wilkinson, Shelby A. Harrington, Cornell Aeronautical Laboratory, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Direct numerical simulation and experimental validation of hypersonic boundary-layer receptivity and instability (Arlington, Virginia. : Air Force Office of Scientific Research, 2007., 2007), by Xiaolin Zhong, Los Angeles. Mechanical University of California, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Automated design optimization for hypersonic plasma-aerodynamics (Arlington, Virginia. : Air Force Office of Scientific Research, 2005., 2005), by Ramakanth Munipalli, Jennifer D. Goss, Donald R Wilson, Shashi Aithal, Kamesh Subbarao, and 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 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1964., 1964), by J. Don Gray, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Pre-flight ground testing of the full-scale HIFiRE-1 at fully duplicated flight conditions (Arlington, Virginia. : Air Force Office of Scientific Research, 2008., 2008), by Tim P. Wadhams, Erik Mundy, Michael S. Holden, Matthew G. MacLean, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Further experiments on impact-pressure probes in a low-density, hypervelocity flow (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1962., 1962), by A. B. Bailey, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• An automated design optimization tool for electromagnetic control of hypersonic flows (Arlington, Virginia. : Air Force Office of Scientific Research, 2005., 2005), by Lei Tang, John Schmisseur, K. Xu, Andre C. Marta, Juan J. Alonso, Danny D. Liu, Yun Zheng, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Real-gas effects on the aerodynamics of blunt cones as measured in a hypervelocity range (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1979., 1979), by C. J. Welsh, Inc ARO, United States. Air Force. Arnold Air Force Base, and Arnold Engineering Development Center (page images at HathiTrust)
• An investigation of the effects of shock impingement on a blunt leading edge (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Von Kármán Gas Dynamics Facility, Air Force Systems Command, United States Air Force, 1965., 1965), by A. D. Ray, R. L. Palko, Inc ARO, United States. Air Force. Arnold Air Force Base, and Arnold Engineering Development Center (page images at HathiTrust)
• Interaction of chemistry, turbulence, and shock waves in hypervelocity flow (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, 1999., 1999), by Graham V. Candler, B. Sturtevant, D. I. Pullin, B. V. McKoy, Daniel I. Meiron, Anthony Leonard, H. G. Hornung, Paul E. Dimotakis, Daniel Guggenheim Aeronautical Laboratory, California Institute of Technology. Graduate Aeronautical Laboratories, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Pressure distribution and flow visualization tests of a 1.5 elliptic cone at Mach 10 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1963., 1963), by R. L. Palko, A. D. Ray, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Heat transfer and temperature distribution in a hemispherical nose cone in hypersonic flow (Polytechnic Institute of Brooklyn, Department of Aerospace Engineering and Applied Mechanics, 1962), by S. V. Nardo, Ronald W. Sadler, and Polytechnic Institute of Brooklyn. Dept. of Aerospace Engineering and Applied Mechanics (page images at HathiTrust; US access only)
• Pressure measurements for Mach 8 flows over expansion corners and ramps on an internally cooled model. Part 2. Flows over a flat plate with and without a partial span ramp : part of an investigation of hypersonic flow separation and control characteristics (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1964., 1964), by Louis G. Kaufman, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Grumman Aircraft Engineering Corporation. Research Department (page images at HathiTrust)
• Pressure measurements for Mach 8 flows over expansion corners and ramps on an internally cooled model. Part 3 Flows over full span ramps mounted on a flat plate (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1964., 1964), by Louis G. Kaufman, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Grumman Aircraft Engineering Corporation. Research Department (page images at HathiTrust)
• Investigation of hypersonic inlet shock-wave boundary layer interaction. Part I (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1965., 1965), by Paul H Kutschenreuter, Paul H. Nettleton, James A. Weil, James S. Keith, United States. Air Force. Systems Command. Research and Technology Division, Air Force Flight Dynamics Laboratory (U.S.), and General Electric Company (page images at HathiTrust)
• Hypersonic aerodynamics (Wright-Patterson Air Force Base, Ohio, Flight Control Laboratory, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, [1962]-1963., 1962), by Vincent W. Donato, Joseph Padlog, James F. Quinn, Rolland D. Huff, Richard H. Gallagher, James R. Batt, United States. Air Force. Systems Command. Aeronautical Systems Division, Bell Aerospace Corporation, and Wright-Patterson Air Force Base (Ohio) (page images at HathiTrust)
• Aerodynamic characteristics and flap loads for a blunt pyramidal configuration at Mach 5 and 8 : part of an investigation of hypersonic flow separation and control characteristics (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1964., 1964), by William J. Evans, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Grumman Aircraft Engineering Corporation. Research Department (page images at HathiTrust)
• Pressure and heat transfer measurements for Mach 8 flows over a blunt pyramidal configuration with aerodynamic controls (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1964., 1964), by Louis G. Kaufman, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Grumman Aircraft Engineering Corporation. Research Department (page images at HathiTrust)
• Tests to determine subsonic pressures, forces and moments acting on a hypersonic re-entry configurations (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1963., 1963), by K. Mantz, R. Ross, D. B. Seager, United States. Air Force. Systems Command. Aeronautical Systems Division, Air Force Flight Dynamics Laboratory (U.S.), and Lockheed-California Company (page images at HathiTrust)
• Heat transfer measurements at Mach 8 on an aerodynamically controllable winged re-entry configuration : part of an investigation of hypersonic flow separation and control characteristics (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1964., 1964), by Lawrence Meckler, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Grumman Aircraft Engineering Corporation. Research Department (page images at HathiTrust)
• Pressure measurements at Mach 8 on an aerodynamically controllable winged re-entry configuration : part of an investigation of hypersonic flow separation and control characteristics (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1965., 1965), by Lawrence Meckler, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Grumman Aircraft Engineering Corporation. Research Department (page images at HathiTrust)
• An investigation of hypersonic flow separation and control characteristics (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1965., 1965), by Louis G. Kaufman, Daniel Weiss, Stravos Hartofilis, Lawrence Meckler, United States. Air Force. Systems Command. Research and Technology Division, Air Force Flight Dynamics Laboratory (U.S.), and Grumman Aircraft Engineering Corporation (page images at HathiTrust)
• Surface measurements on sharp flat plates and wedges in low-density hypersonic flow / repared by by Robert J. Vidal and John A. Bartz. (Cornell Aeronautical Laboratory of Cornell University, 1968), by Robert J. Vidal, John A. Bartz, United States. Air Force. Office of Scientific Research, and Cornell Aeronautical Laboratory (page images at HathiTrust)
• Flowfield surveys in the hypersonic viscous shock layer on a sharp flat plate (Cornell Aeronautical Laboratory of Cornell University, 1970), by Robert J. Vidal, Gordon E. Merritt, John A. Bartz, United States. Air Force. Office of Scientific Research, and Cornell Aeronautical Laboratory (page images at HathiTrust)
• Flowfield surveys in the leading edge region of a sharp flat plate (Cornell Aeronautical Laboratory of Cornell University, 1971), by Robert J. Vidal, John A. Bartz, Gordon E. Merritt, United States. Air Force. Office of Scientific Research, and Cornell Aeronautical Laboratory (page images at HathiTrust)

More items available under broader and related terms at left.