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Aerodynamic heating

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• Aerodynamics
• Aerothermodynamics
• Friction
• Heat
• Thermodynamics

• Artificial satellites -- Atmospheric entry
• Space vehicles -- Atmospheric entry

• Heat barrier
• Heating, Aerodynamic
• Thermal barrier

• Gas dynamics in space exploration ; [scientific papers] (Washington, National Aeronautics and Space Administration, Office of Scientific and Technical Information ; [for sale by the Superintendent of Documents, U.S.Govt. Print.Off.], 1962 [i.e. 1963]), by Chicago NASA-University Conference on the Science and Technology of Space Exploration (page images at HathiTrust)
• Wood-based paneling as thermal barriers. (Madison, Wis. : U.S. Dept. of Agriculture, Forest Service, Forest Products Laboratory, [1982]), by Robert H. White and Forest Products Laboratory (U.S.) (page images at HathiTrust)
• Experimental heat-transfer and friction coefficients for air flowing through stacks of parallel flat plates / (Washington, D.C. : NACA, 1954), by Eldon W. Sams, Walter F. Weiland, United States. National Advisory Committee for Aeronautics, and Lewis Research Center (page images at HathiTrust)
• Preliminary results of aerodynamic heating studies on the X-15 airplane / (Washington, D.C. : National Aeronautics and Space Administration, 1962), by Richard D. Banner, Robert D. Quinn, Albert E. Kuhl, and Flight Research Center (U.S.) (page images at HathiTrust)
• Optimization of the NiCrAl-Y/Zr0₂-Y₂O₃ / (Cleveland, Ohio : Lewis Research Center, [1985?]), by Stephan Stecura and Lewis Research Center (page images at HathiTrust)
• Elevated-temperature tests under static and aerodynamic conditions on honeycomb-core sandwich panels / (Washington [D.C.] : National Aeronautics and Space Administration, [1959]), by Joseph M. Groen, Aldie E. Johnson, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Investigation of aerodynamic effects of external combustion below flat-plate model in 10- by 10-foot wind tunnel at Mach 2.4 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Robert G. Dorsch, Murray Dryer, Harrison Allen, and Lewis Research Center (page images at HathiTrust)
• Radiative heat transfer during atmosphere entry at parabolic velocity / (Washington, [D.C.] : National Aeronautical and Space Administration, 1961), by Kenneth K. Yoshikawa, Bradford H. Wick, United States National Aeronautics and Space Administration, and Ames 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 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Jerry N. Hefner and Lanley Research Center (page images at HathiTrust)
• Surface flow and heating distributions on a cylinder in near wake of Aeroassist Flight Experiment (AFE) configuration at incidence in Mach 10 air / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1990), by William L. Wells and Langley Research Center (page images at HathiTrust)
• Elevated-temperature tests under static and aerodynamic conditions on corrugated-stiffened panels / (Washington [D.C.] : National Aeronautics and Space Administration, [1959]), by Joseph M. Groen, Richard Rosecrans, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Low-cycle fatigue evaluation for regeneratively cooled panels / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1971), by C. E. Richard, Langley Research Center, AiResearch Manufacturing Company of Los Angeles (Calif.), and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Solutions of the ionized radiating shock layer, including reabsorption and foreign species effects, and stagnation region heat transfer / ([Washington, D.C., National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1963), by John T. Howe, John R. Viegas, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Analysis of various descent trajectories for a hypersonic-cruise, cold-wall research airplane / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Pierce L. Lawing and Langley Research Center (page images at HathiTrust)
• Experiments to study strain-gage load calibrations on a wing structure at elevated temperatures / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Richard C. Monaghan, Roger A. Fields, and Flight Research Center (U.S.) (page images at HathiTrust)
• Curve fits of predicted inviscid stagnation-point radiative heating rates, cooling factors, and shock standoff distances for hyperbolic earth entry / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by John T. Suttles, Stephen B. Margolis, Edward M. Sullivan, and Langley Research Center (page images at HathiTrust)
• Tests of aerodynamically heated multiweb wing structures in a free jet at mach number 2 : five aluminum-alloy models of 20-inch chord with 0.064-inch-thick skin, 0.025-inch-thick webs, and various chordwise stiffening at 2° angle of attack / (Washington [D.C.] : National Aeronautics and Space Administration, [1960]), by Donald H. Trussell, Robert G. Thomson, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Thermal-structural combined loads design criteria study / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by V. Deriugin, Langley Research Center, and Boeing Company (page images at HathiTrust)
• Thermal and structural tests of a hydrogen cooled panel / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by C. E. Richard, Langley Research Center, and AiResearch Manufacturing Company of Los Angeles (Calif.) (page images at HathiTrust)
• Aerodynamic heating and loading within large open cavities in cone and cone-cyclinder-flare models at Mach 6.7 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by L. Roane Hunt and Langley Research Center (page images at HathiTrust)
• Aerodynamic pressure and heating-rate distributions in tile gaps around chine regions with pressure at a Mach number of 6.6 / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1990), by L. Roane Hunt, Kristopher K. Notestine, and Langley Research Center (page images at HathiTrust)
• Numerical studies of convective cooling for a locally heated skin / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1991), by Stephen J. Scotti and Langley Research Center (page images at HathiTrust)
• Investigation of aluminum phosphate coatings for thermal insulation of airframes / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by A. G. Eubanks, D. G. Moore, and United States. National Bureau of Standards (page images at HathiTrust)
• A new technique for calculating reentry base heating / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by James C. S. Meng and George C. Marshall Space Flight Center. Aero-Astrodynamics Laboratory (page images at HathiTrust)
• Safe atmosphere entry of an isotope heat source with a single stable trim attitude at hypersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by Lionel L. Levy, Raymond K. Burns, and Ames Research Center (page images at HathiTrust)
• Apollo experience report : aerothermodynamics evaluation / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by Dorothy B. Lee and Manned Spacecraft Center (U.S.) (page images at HathiTrust)
• Flight test aerodynamic heating data for the afterbody of the Project Mercury spacecraft with comparisons to available prediction methods / ([Washington, D.C. : National Aeronautics and Space Administration] ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1967), by J. D. Murphy, Project Mercury (U.S.), Manned Spacecraft Center (U.S.), Lockheed Missiles and Space Company, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Panel flutter tests on full-scale X-15 lower vertical stabilizer at Mach number of 3.0 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1962), by Herman L. Bohon, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Flutter at very high speeds / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Harry L. Runyan, Homer G. Morgan, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• The aerothermodynamic environment of the Apollo command module during suborbital entry / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by Dorothy B. Lee, Winston D. Goodrich, and Manned Spacecraft Center (U.S.) (page images at HathiTrust)
• Analytical and experimental studies of shock interference heating in hypersonic flows (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by J. Wayne Keyes, Frank D. Hains, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Interference heating from interactions of shock waves with turbulent boundary layers at Mach 6 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Charles B. Johnson, Louis G. Kaufman, and Langley Research Center (page images at HathiTrust)
• Free-flight investigation of heat transfer to an unswept cylinder subjected to an incident shock and flow interference from an upstream body at Mach numbers up to 5.50 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1961), by Howard S. Carter, Robert E. Carr, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Analytical determination of the effect of thermal property variations on the performance of a charring ablator / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1966), by C. M. Pittman, William D. Brewer, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Range of interface thermal conductance for aircraft joints / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Martin E. Barzelay and Syracuse University (page images at HathiTrust)
• Low-cycle fatigue of thermal-barrer coatings at 982⁰ C / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Service ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Albert Kaufman, Alfred J. Nachtigall, Curt H. Liebert, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Z-function solutions for the motion and heating during atmosphere entry from equatorial orbits of a rotating planet / (Washington, DC : National Aeronautics and Space Administration, [1963]), by Frederick W. Boltz and Ames Research Center (page images at HathiTrust)
• Instrumentation for magnetoaerodynamic heat transfer. (Los Angeles, Physical Research Laboratory, Space Technology Laboratories, 1960), by Richard W. Ziemer (page images at HathiTrust)
• Thermal effects on static aeroelastic stability and control. (Wright-Patterson Air Force Base, O. : Wright Air Development Center, Air Research and Development Command, U. S. Air Force, 1959), by Bell Aircraft Corp (page images at HathiTrust)
• Preliminary analysis of the capabilities of a composite slab for an advanced heat-sink design / (Wright-Patterson Air Force Base, Ohio : Wright Air Development Division, Air Research and Development Command, U.S. Air Force, [1961]), by Paul A. Libby (page images at HathiTrust)
• A 50-megawatt arc heater: scaling parameters and performance prediction (Wright-Patterson Air Force Base, Ohio, AF Flight Dynamics Laboratory, Research and Technology Division, Air Force systems Command, 1964), by Richard T. Smith and Joseph P. Doyle (page images at HathiTrust)
• Aerodynamic heating of parachutes (Wright-Patterson Air Force Base, Ohio, Wright Air Development Center, Air Research and Development Command, U.S. Air Force, 1957), by Cornell University. Dept. of Engineering Mechanics and Materials, F. Frank, S. W. Liu, and A. L. Ruoff (page images at HathiTrust)
• Performance improvement of arc heaters for aerodynamic wind tunnels ([Wright-Patterson Air Force Base, Ohio, Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, 1965]), by R. C. Eschenbach, E. F. Stresino, and J. R. McLeod (page images at HathiTrust)
• Helium injection into the boundary layer at an axisymmetric stagnation point (Wright-Patterson Air Force Base, Ohio, Aeronautical Research Laboratory, Office of Aerospace Research, U. S. Air Force, 1961), by Herbert Fox and Paul Andrew Libby (page images at HathiTrust)
• Study of infrared emission in heated air; annual report, July 1960-June 1961, (Buffalo, Cornell Aeronautical Laboratory, 1961), by Walter H. Wurster and Paul V. Marrone (page images at HathiTrust)
• An experimental study of the effect of mass injection at the stagnation point of a blunt body, (Pasadena, Guggenheim Aeronautical Laboratory, California Institute of Technology, 1958), by Howard K. McMahon (page images at HathiTrust)
• Optimum shape for transpiration-cooled nosetip of a re-entry vehicle / (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1978), by Kevin E. Yelmgren (page images at HathiTrust)
• Preliminary analytical investigation of booster recovery by use of a hot-air balloon for both deceleration and final recovery / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia], 1966), by Stanley H. Scher, Irene G. Young, James C. Dunavant, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust; US access only)
• A study of the accuracy of a flight-heating simulation and its effect on load measurement / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by Roger A. Fields, Flight Research Center (U.S.), and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Water injection from a 9⁰ hemisphere-cone into a hypersonic airstream / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by William L. Weaver, William F. Hinson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• An integral analysis of heat transfer downstream of a rearward-facing step with small coolant injection. (Washington, National Aeronautics and Space Administration; [for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], 1970), by Keiichi Karashima (page images at HathiTrust; US access only)
• Boundary-layer similar solutions and correlation equations for laminar heat-transfer distribution in equilibrium air at velocities up to 41,100 feet per second / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Supt. of Docs., U.S. G.P.O.], 1961), by Nathaniel B. Cohen and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• An analytic study of radiatively cooled delta-wing structures for hypersonic aircraft / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151], 1971), by James Campbell Robinson, George F. Klich, Robert R. McWithey, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• High temperature radome design techniques. (Buffalo, Cornell Aeronautical Laboratory, [196-?]), by Godfrey F. Buranich (page images at HathiTrust)
• Further industrial tests of ceramic thermal-barrier coatings / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1982), by Curt H. Liebert, Stanley R. Levine, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Aerothermal tests of quilted dome models on a flat plate at a Mach number of 6.5 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1988), by Christopher E. Glass, L. Roane Hunt, and Langley Research Center (page images at HathiTrust)
• A review of high-speed, convective, heat-transfer computation methods / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1989), by Michael E. Tauber and United States. National Aeronautics and Space Administration. Office of Management (page images at HathiTrust)
• Aerothermal test results from the first flight of the Pegasus air-launched space booster / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991), by Gregory Noffz and Dryden Flight Research Facility (page images at HathiTrust)
• Experimental investigation at Mach 8 of the effects of projections and cavities on heat transfer to a model of the Viking aeroshell / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Theodore R. Creel and Langley Research Center (page images at HathiTrust)
• Aerothermal tests of spherical dome protuberances on a flat plate at a Mach number of 6.5 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1986), by Christopher E. Glass, L. Roane Hunt, and Langley Research Center (page images at HathiTrust)
• Trajectory characteristics and heating of hypervelocity projectiles having large ballistic coeffients / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1986), by Michael E. Tauber and Ames Research Center (page images at HathiTrust)
• The use of interactive graphic displays for interpretation of surface design parameters / (Washington, D.C. : U.S. National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Noel A. Talcott, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Analysis of gap heating due to stepped tiles in the shuttle thermal protection system / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1983), by D. H. Petley and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Flight vehicle thermal testing with infrared lamps / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Roger A. Fields and Dryden Flight Research Facility (page images at HathiTrust)
• Analysis of metal temperature and coolant flow with a thermal-barrier coating on a full-coverage-film-cooled turbine vane / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Peter L. Meitner, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Propulsion Laboratory (U.S.) (page images at HathiTrust)
• Durability of zirconia thermal-barrier ceramic coatings on air-cooled turbine blades in cyclic jet engine operation / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by Lewis Research Center, Curt H. Liebert, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Optimum element density studies for finite-element thermal analysis of hypersonic aircraft structures / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, VA : For sale by the National Technical Information Service, 1990), by William L. Ko, Kyle M. Muramoto, Timothy Olona, and Dryden Flight Research Facility (page images at HathiTrust)
• Real-time aerodynamic heating and surface temperature calculations for hypersonic flight simulation / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1990), by Robert D. Quinn, Leslie Gong, and Dryden Flight Research Facility (page images at HathiTrust)
• Pressure and heating-rate distributions on a corrugated surface in a supersonic turbulent boundary layer / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by James Wayne Sawyer and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Surface recession characteristics of a cryogenic insulation subjected to arc-tunnel heating / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by C. M. Pittman, Ronald D. Brown, and Langley Research Center (page images at HathiTrust)
• Aerodynamic heating to the gaps and surfaces of simulated reusable-surface-insulation tile arrays in turbulent flow at Mach 6.6 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Irving Weinstein, Andrew J. Chapman, Don E. Avery, and Langley Research Center (page images at HathiTrust)
• In-flight boundary-layer measurements on a hollow cylinder at a Mach number of 3.0 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by Robert D. Quinn, Leslie Gong, Hugh L. Dryden Flight Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• An experimental investigation of base heating on typical Mars entry body shapes / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1971]), by O. L. Zappa, William G. Reinecke, Langley Research Center, and Avco Corporation. Systems Division (page images at HathiTrust)
• Rapid methods for calculating radiation transport in the entry environment / (Washington, D.C. : National Aeronautics and Space Administration, 1975), by William E. Nicolet, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Heat-transfer tests of 20-millimeter projectiles at a Mach number of 5 with an analysis by unsteady scaling laws to predict component temperature rises after firing for various free-flight conditions / (Washington : National Aeronautics and Space Administration, [1961]), by Robert L. Trimpi, Robert A. Jones, James G. Gallagher, and Langley Research Center (page images at HathiTrust)
• A study of the aerodynamic characteristics of a fixed geometry paraglider configuration and three canopies with simulated variable canopy inflation at a mach number of 6.6 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce], [1962]), by Jim A. Penland and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Methods of predicting laminar heat rates on hypersonic vehicles / (Washington : National Aeronautics and Space Administration, [1959]), by Richard J. Wisniewski and Lewis Research Center (page images at HathiTrust)
• Numerical computation of aerodynamic heating of liquid propellants / (Washington : National Aeronautics and Space Administration, [1960]), by John L. Kramer, William H. Roudebush, Herman H. Lowell, and Lewis Research Center (page images at HathiTrust)
• Aerodynamic-heating data obtained from free-flight tests between Mach numbers of 1 and 5 / (Washington : National Aeronautics and Space Administration, [1960]), by Charles B. Rumsey, Russell N. Hopko, Robert Owens Piland, and Langley Research Center (page images at HathiTrust)
• Experimental boundary-layer edge Mach numbers for two space shuttle orbiters at hypersonic speeds / (Washington, DC : National Aeronautics and Space Administration, 1972), by George C. Ashby, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Preliminary studies of manned satellites wingless configuration : nonlifting / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, 1962]), by Maxime A. Faget, James J. Buglia, Benjamine J. Garland, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Calculated effective thermal conductivities of honeycomb sandwich panels / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce], [1959]), by Robert T. Swann and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Spectrographic temperature measurements in a carbon-arc-powered air jet / (Washington : National Aeronautics and Space Administration, [1959]), by David H. Greenshields and Langley Research Center (page images at HathiTrust)
• Inviscid hypersonic flow over a blunt body with high rates of mass and heat transfer / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1968]), by E. Dale Martin and Ames Research Center (page images at HathiTrust)
• An investigation of heat transfer within regions of separated flow at a Mach number of 6.0 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1965]), by Paul F. Holloway, Helen S. Creekmore, James R. Sterrett, and Langley Research Center (page images at HathiTrust)
• Interference heating on a swept cylinder in region of intersection with a wedge at Mach number 8 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1965]), by Dennis M. Bushnell and Langley Research Center (page images at HathiTrust)
• Isentropic flow solutions for reacting gas mixtures in thermochemical equilibrium / (Washington, D. C. : National Aeronautics and Space Administration ; Springfield, Va. : for sale by the Clearinghouse for Federal Scientific and Technical Information, 1967), by Ernest V. Zoby, Casimir J. Jachimowski, Jane T. Kemper, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Performance of laser glazed ZrO2 TBCs in cyclic oxidation and corrosion burner test rigs / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1982), by I. Zaplatynsky, American Vacuum Society, and Lewis Research Center (page images at HathiTrust)
• Aerodynamic heating tests of missile stabilizers in a free jet at Mach number 2 / (Washington, D.C. : National Aeronautics and Space Administration, 1960), by Louis F. Vosteen and Langley Research Center (page images at HathiTrust)
• Investigation of the loading characteristics of the lifting surfaces and the speed brakes of a 0.067-scale model of the north american x-15 airplane (configuration 3) at Mach numbers of 2.29, 2.98, and 4.65 / (Washington, D.C. : National Aeronautics and Space Administration, 1960), by Norman H. Silvers, Jane S. Wills, Julia A. Lancaster, and Langley Research Center (page images at HathiTrust)
• A simplified method for thermal analysis of a cowl leading edge subject to intense local shock-wave-interference heating / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by David M. McGowan, Stephen J. Scotti, Charles J. Camarda, and Langley Research Center (page images at HathiTrust)
• Experimental aerodynamic heating of simulated space shuttle tiles in laminar and turbulent boundary layers with variable flow angles at a nominal Mach number of 7 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1985), by Don E. Avery and Langley Research Center (page images at HathiTrust)
• A device for rapid determination of thermophysical properties of phase-change wind-tunnel models / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by Theodore R. Creel and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Heat-transfer distributions on a 0.013-scale shuttle solid rocket booster at Mach 3.70 and angles of attack from 0 ̊to 180 ̊ / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by Milton Lamb, Robert L. Stallings, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• The use of computer-generated color graphic images for transient thermal analysis / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by C. L. W. Edwards, James B. Hall, Frances T. Meissner, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Industry tests of NASA ceramic thermal barrier coating / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by Curt H. Liebert, Francis S. Stepka, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Exploratory investigation of two resin-matrix composites subjected to arc-tunnel heating / (Washington : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1979), by C. M. Pittman, Ronald D. Brown, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• CAVE : a computer code for two-dimensional transient heating analysis of conceptual thermal protection systems for hypersonic vehicles / ([Washington] : National Aeronautics and Space Administration : Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Kenneth A. Rathjen and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Actively cooled plate fin sandwich structural panels for hypersonic aircraft / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by L. M. Smith, C. S. Beuyukian, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Effects of mach number and wall-temperature ratio on turbulent heat transfer at mach numbers from 3 to 5, ([Washington, U.S. G.P.O.], 1959), by Thorval Tendeland (page images at HathiTrust)
• Analysis of turbulent flow and heat transfer on a flat plate at high mach numbers with variable fluid properties, ([Washington, U.S. G.P.O.], 1959), by R. G. Deissler (page images at HathiTrust)
• Prospects for obtaining aerodynamic heating results from analysis of meteor flight data / (Washington, D.C. : National Aeronautics and Space Administration : For sale by the Office of Technical Services, Dept. of Commerce, [1964]), by H. Julian Allen, Nataline A. James, and Ames Research Center (page images at HathiTrust)
• Exploratory investigation of several coated and uncoated metal, refractory, and graphite models in a 3800° F stagnation temperature air jet / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Otto F. Trout and Langley Research Center (page images at HathiTrust)
• The leading-edge effects on the laminar flat-plate boundary layer and the aerodynamic heating at Mach 10.4 / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Howard W. Stone, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Heat-transfer and temperature distribution of a conical porous membrane during planetary entry / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1967]), by Latif M. Jiji and Ames Research Center (page images at HathiTrust)
• Shielding stagnation surfaces of finite catalytic activity by air injection in hypersonic flight / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Paul M. Chung and Ames Research Center (page images at HathiTrust)
• Heat-transfer measurements on the rotor blade of a rotor entry vehicle model / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1967), by Ronald C. Smith, Alan D. Levin, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effect of two-dimensional multiple sine-wave protrusions on the pressure and heat-transfer distributions for a flat plate at Mach 6 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1968]), by Aubrey M. Cary, E. Leon Morrisette, and Langley Research Center (page images at HathiTrust)
• A flight measurement of optical radiation from shock-heated air by using a Trailblazer II vehicle (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1968]), by Lloyd S. Keafer, Ernest E. Burcher, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Low-perigee aerodynamic heating during orbital flight of an Atmospheric Explorer / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by Paul S. Caruso, Charles R. Naegeli, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Aerodynamic heating in large cavities in an array of RSI [reusable surface insulation] tiles / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by L. Roane Hunt, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Downstream influence of swept slot injection in hypersonic turbulent flow / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Jerry N. Hefner, Dennis M. Bushnell, Aubrey M. Carey, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Convective heat-transfer rates on large-scale conical bodies at hypersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1969]), by David A. Stewart, Joseph G. Marvin, and Ames Research Center (page images at HathiTrust)
• Data-reduction technique for determining rapidly rising heating rates to thermally thick walls / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1969]), by James L. Dillon, G. Louis Smith, Robert L. Wright, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• A simplified method for calculating laminar heat transfer over bodies at an angle of attack / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1968), by Fred R. DeJarnette, Ruby M. Davis, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Evaluation of an infrared heating simulation of a Mach 4.63 flight on an X-15 horizontal stabilizer / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1969]), by Roger A. Fields, Andrew Vano, United States National Aeronautics and Space Administration, and Flight Research Center (U.S.) (page images at HathiTrust)
• Pressures and heat transfer on a 75 ̊swept delta wing with trailing-edge flap at Mach 6 and angles of attack to 90 (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by J. Wayne Keyes, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Calculation of laminar heat transfer to the windward surfaces of straight wing shuttle vehicles at high angle of attack and with yaw / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by C. C. Pappas, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• The use of energy thickness in prediction of throat heat transfer in rocket nozzles / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Robert W. Graham, Donald R. Boldman, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Experimental heat-transfer distributions on a blunt lifting body at Mach 3.71 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1970]), by Robert L. Stallings, Ida K. Collins, Robert L. Wright, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Preliminary surveys of the wall boundary layer in a Mach 6 axisymmetric tunnel / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1970]), by Robert A. Jones, William V. Feller, and Langley Research Center (page images at HathiTrust)
• Experimental investigation of Mach 3 cruise heating simulations on a representative wing structure for flight-loads measurement / (Washington, DC : National Aeronautics and Space Administration, 1972), by Roger A. Fields, Richard C. Monaghan, Frank V. Olinger, United States National Aeronautics and Space Administration, and NASA Dryden Flight Research Center (page images at HathiTrust)
• Shock-tube heat-transfer measurements on inner surface of a cylinder (simulating a flat plate) for stagnation-temperature range 4,100 ̊to 8,300 ̊R / (Washington : National Aeronautics and Space Administration, [1959]), by Jim J. Jones and Langley Research Center (page images at HathiTrust)
• Investigation of the flow over a spiked-nose hemisphere-cylinder at a Mach number of 6.8 / (Washington : National Aeronautics and Space Administration, [1959]), by Davis H. Crawford and Langley Research Center (page images at HathiTrust)
• Optimum design of insulated tension members subjected to aerodynamic heating / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by John R. Davidson and Langley Research Center (page images at HathiTrust)
• Unsteady stagnation-point heat transfer / (Washington : National Aeronautics and Space Administration, [1959]), by E. M. Sparrow and Lewis Research Center (page images at HathiTrust)
• A study of methods for simulating the atmosphere entry of vehicles with small-scale models / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Byron L. Swenson and Ames Research Center (page images at HathiTrust)
• An approximate analysis of unsteady vaporization near the stagnation point of blunt bodies / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Leonard Roberts and Langley Research Center (page images at HathiTrust)
• Theoretical analysis of the creep collapse of columns / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Floyd R. Schlechte and Langley Research Center (page images at HathiTrust)
• Effect of chordwise heat conduction on the torsional stiffness of a diamond-shaped wing subjected to a constant heat input / (Washington, [D.C.] : National Aeronautics and Space Administration, 1959), by Robert G. Thomson, J. Lyell Sanders, and Langley Research Center (page images at HathiTrust)
• An experimental and theoretical investigation of the pressure distribution and flow fields of blunted cones at hypersonic Mach number / (Washington, D.C. : National Aeronautics and Space Administration, 1965), by Joseph W. Cleary and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Laminar heat-transfer distributions for a blunted-cone, cone-frustum reentry configuration at Mach 10 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1969]), by J. David Dearing and Langley Research Center (page images at HathiTrust)
• Laminar skin-friction and heat-transfer parameters for a flat plate at hypersonic speeds in terms of free-stream flow properties / (Washington : National Aeronautics and Space Administration, [1959]), by James F. Schmidt and Lewis Research Center (page images at HathiTrust)
• Heat-transfer and pressure distributions on hemisphere-cylinders in methane-air combustion products at Mach 7 [electronic resource] / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Irving Weinstein, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Effect of wing sweep, angle of attack, Reynolds number, and wing root fillet on the interference heating to the wing windward surface of an entry vehicle configuration [electronic resource] / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by Louis E. Clark, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Effect of roughness on heat transfer to hemisphere cylinders at Mach numbers 10.4 and 11.4 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1967), by James C. Dunavant, Howard W. Stone, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Supersonic aerodynamic heating tests on a lightweight external insulation system for liquid-hydrogen tanks of boost vehicles / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1966), by Reeves P. Cochran, Robert W. Cubbison, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• FREE-FLIGHT AERODYNAMIC-HEATING DATA TO MACH NUMBER 10.4 FOR A MODIFIED VON KARMAN NOSE SHAPE. (Ft. Belvoir Defense Technical Information Center, MAY 1961), by COLLIE,KATHERINE A, BLAND,WILLIAM M JR, and NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C. (page images at HathiTrust; US access only)
• Procedures for including temperature effects in structural analyses of elastic wings - part I an equivalent plate method of structural analysis for elevated temperature structures /, by William R. Mills, United States. Air Force. Air Research and Development Command. sponsor, Wright Air Development Center issuing body, and Wright Air Development Center (page images at HathiTrust)
• Heat transfer and frictional effects in laminar boundary layers :, by Arthur N. Tifford, sponsor United States. Air Force. Air Research and Development Command., issuing body Wright Air Development Center, and sponsor Ohio State University. Research Foundation. (page images at HathiTrust)
• A comparative analysis of the performance of long-range hypervelocity vehicles / (Washington : National Advisory Committee for Aeronautics, [1957]), by Alfred J. Eggers, Stanford E. Neice, H. Julian Allen, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Measurements of aerodynamic heat transfer in turbulent separated regions at a Mach number of 1.8 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1958), by Benjamine J. Garland, J. R. Hall, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• The effect of nonuniform temperature distributions on the stresses and distortions of stiffened-shell structures / (Washington, D.C. : National Advisory Committee for Aeronautics, 1950), by Richard R. Heldenfels and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Experimental investigation of the simulation of atmospheric entry of ballistic missiles / (Washington, D.C. : National Advisory Committee for Aeronautics, [1957]), by Stanford E. Neice, Bernard E. Cunningham, James A. Carson, Ames Laboratory, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• an Integral approach to transient heat-conduction problems with phase transition /, by Tse-Fou Zien and Naval Surface Weapons Center. White Oak Laboratory (page images at HathiTrust)
• Heat transfer from high-temperature surfaces to fluids. (Washington, [D.C.] : National Advisory Committee for Aeronautics, [1949]), by Warren H. Lowdermilk, Milton D. Grele, United States. National Advisory Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Heat transfer from high-temperature surfaces to fluids. (Washington, [D.C.] : National Advisory Committee for Aeronautics, [1948]), by Leroy V. Humble, Milton Grele, Warren H. Lowdermilk, United States. National Advisory Committee for Aeronautics. NACA research memorandum, United States. National Advisory Committee for Aeronautics, and Flight Propulsion Research Laboratory (page images at HathiTrust)
• Measurements of aerodynamic heating obtained during demonstration flight tests of the Douglas D-558-II airplane / (Washington, D.C. : National Advisory Committee for Aeronautics, 1952), by Ira P. Jones, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Preliminary results of supersonic-jet tests of simplified wing structures / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by Richard R. Heldenfels, Richard Rosecrans, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Transient temperature distribution in an aerodynamically heated multiweb wing / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by George E. Griffith, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Aerodynamic-heating data obtained from free-flight tests between Mach numbers of 1 and 5 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1955), by Charles B. Rumsey, Russell N. Hopko, Robert O. Piland, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Free-flight measurements of aerodynamic heat transfer to Mach number 3.9 and of drag to Mach number 6.9 of a fin-stabilized cone-cylinder configuration / (Washington, D.C. : National Advisory Committee for Aeronautics, 1955), by Charles B. Rumsey, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Flutter at very high speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1957), by Harry L. Runyan, Homer G. Morgan, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Local heat transfer to blunt noses at high supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1957), by William E. Stoney, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Preliminary investigation of lithium hydride as a high-temperature internal coolant / (Washington, D.C. : National Advisory Committee for Aeronautics, 1957), by Jerry L. Modisette, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Aerodynamic heating and the deflection of drops by an obstacle in an air stream in relation to aircraft icing / (Washington D.C. : National Advisory Committee for Aeronautics ;, 1940), by Arthur Kantrowitz and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Analysis of turbulent heat transfer, mass transfer, and friction in smooth tubes at high Prandtl and Schmidt numbers / (Washington, D.C. : National Advisory Committee for Aeronautics, [1954]), by Robert G. Deissler and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• The compressible laminar boundary layer with fluid injection / (Washington, D.C. : National Advisory Committee for Aeronautics, [1955]), by George M. Low and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Estimates from satellites of weather erosion parameters for reentry systems /, by John H. Conover, James T. Bunting, and U.S. Air Force Geophysics Laboratory. Meteorology Division (page images at HathiTrust)
• Measurements of atmospheric density at Kwajalein Atoll, 18 May 1977 /, by C. R. Philbrick, D. H. Fryklund, A. C. Faire, and U.S. Air Force Geophysics Laboratory (page images at HathiTrust)
• Horizontal scale variations in satellite estimates of weather erosion parameters for reentry systems /, by James T. Bunting, C. N. Touart, and U.S. Air Force Geophysics Laboratory (page images at HathiTrust)
• Methods for conducting short-time tensile, creep, and creep-rupture tests under conditions of rapid heating /, by Donald P. Moon, Ward F. Simmons, Defense Metals Information Center (U.S.) issuing body, and United States. Office of the Director of Defense Research and Engineering (page images at HathiTrust)
• Selected short-time tensile and creep data obtained under conditions of rapid hearting /, by Donald P. Moon, Ward F. Simmons, Defense Metals Information Center (U.S.) issuing body, and United States. Office of the Director of Defense Research and Engineering (page images at HathiTrust)
• Charts of equilibrium real-gas stagnation point conditions on a sphere for altitudes to 200,000 feet and velocities to 15,000 feet per second /, by P. D. Fisher and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Use of phase-change paints to study fin-body interference heating /, by Jr. Gillerlain and Naval Surface Weapons Center. : White Oak Laboratory (page images at HathiTrust)
• Normal impingement of a supersonic jet on a plane : a basic study of shock-interference heating /, by Kuei-Yuan Chien and Naval Surface Weapons Center. White Oak Laboratory (page images at HathiTrust)
• Interacting supersonic turbulent boundary layers over a two-dimensional protuberance. /, by Arnold Polak and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Experimental investigation of a fin-cone interference flow field at Mach 5 /, by Jr. Gillerlain and Naval Surface Weapons Center. White Oak Laboratory (page images at HathiTrust)
• Boundary-layer transition experiments on pre-ablated graphite nosetips in a hyperballistics range /, by Daniel C Reda, Robert A. Leverance, and Naval Surface Weapons Center. White Oak Laboratory (page images at HathiTrust)
• Motion and heating during atmosphere reentry of space vehicles / (Washington : National Aeronautics and Space Administration, 1960), by Thomas J. Wong, Robert E. Slye, Glen Goodwin, and Ames Research Center (page images at HathiTrust; US access only)
• Elasto-plastic analysis of structures under load and two-dimensional temperature distributions., by P. C. Huang, R. J. Edwards, issuing body United States. Air Force. Systems Command. Aeronautical Systems Division, Air Force Flight Dynamics Laboratory (U.S.) sponsor, and sponsor Martin Marietta Corporation. Baltimore Division (page images at HathiTrust)
• Induction heating and theory in the solution of transient problems of aircraft structures /, by N. J. Hoff, Burton Erickson, V. Wagle, S. Lederman, I. Mirsky, Irwin Berman, Frederick Pohle, sponsor United States. Air Force. Air Research and Development Command, Wright Air Development Center issuing body, and Polytechnic Institute of Brooklyn. Department of Aeronautical Engineering and Applied Mechanics (page images at HathiTrust)
• Investigation of numerical techniques for predicting aerodynamic heating to flight vehicles /, by Arthur B. Lewis, Neil J. Sliski, and sponsor Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Aerodynamic heating and heat transfer for airfoils at Mach numbers of 2.74 through 5.7 /, by A. E. Abramson, J. A. Zdrazil, W. L. Torgeson, sponsor United States. Air Force. Air Research and Development Command, Wright Air Development Center issuing body, and Inc. Research (page images at HathiTrust)
• Theory and experiment in the solution of structural problems of supersonic aircraft /, by Nicholas J. Hoff, Lederman,S., MacLean,William R., Alexander Chwick, William I. Berks, I. Mirsky, Henry Oliver, Frederick V. Pohle, Martin Bloom, sponsor Wright Air Development Center, and sponsor Polytechnic Institute of Brooklyn (page images at HathiTrust)
• Elasto-plastic analysis of structures under load and two-dimensional temperature distributions., by P. C. Huang, R. J. Edwards, issuing body United States. Air Force. Systems Command. Aeronautical Systems Division, Air Force Flight Dynamics Laboratory (U.S.) sponsor, and sponsor Martin Marietta Corporation. Baltimore Division (page images at HathiTrust)
• An experimental study of the distribution of convective heat transfer to a large-scale model of parachute cloth /, by E. R. G. Eckert, K. M. Krall, C. J. Scott, M. Ruiz-Urbieta, J. E. Anderson, sponsor Wright-Patterson Air Force Base (Ohio), sponsor University of Minnesota, and sponsor Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Thermal effects on static aeroelastic stability and control : description and results of tests conducted to determine the thermally affected deflectional behavior of corrugated multiweb wing structures /, by James F. Quinn, Richard H. Gallagher, Donald Turrentine, sponsor Bell Aircraft Corporation, sponsor United States. Wright Air Development Division, and United States. Air Force. Air Research and Development Command. issuing body (page images at HathiTrust)
• Calculation of laminar separation with free interaction by the method of integral relations., by Jack Norman Nielsen, Frederick K. Goodwin, Larry L. Lynes, sponsor Wright-Patterson Air Force Base (Ohio), sponsor Itek Corporation, and sponsor Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• The analytical determination of the thermal response of a typical aircraft structure subjected to transient external heating and cooling /, by Thomas N. Bernstein, Robert M. Engle, Gene E. Maddux, and sponsor Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• A discussion of methods for reducing aerodynamic heating in supersonic flight / (Washington, D.C. : National Advisory Committee for Aeronautics, [1955]), by A. J. Jr Eggers, United States. National Advisory Committee for Aeronautics. NACA research memorandum, and Ames Research Center (page images at HathiTrust)
• Calculation of surface temperatures in steady supersonic flight / (Washington D.C. : National Advisory Committee for Aeronautics ;, 1946), by George P. Wood and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Test of 61S-T6 aluminum sheet under short-duration, high rate of rise, heating / ([Albuquerque, N.M.] : Sandia Corporation ; Washington, D.C. : Available from the Office of Technical Services, Department of Commerce, [1958]), by J. A. Barber and Sandia Corporation (page images at HathiTrust; US access only)
• A comparison of stagnation-point heating in a rocket exhaust to that of actual flight / ([Albuquerque, N.M.], [Sandia Corp.], 1961), by Frank L. Paris (page images at HathiTrust; US access only)
• Distribution of ROBIN sensed wind shears at 30 to 70 kilometers /, by Henry A. Salmela, Norman Sissenwine, and Air Force Cambridge Research Laboratories (U.S.) (page images at HathiTrust)
• Proceedings of Symposium on Aerothermoelasticity ; 30-31 October and 1 November 1961 /, by David M. Jones and sponsor United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• Pressure and heat transfer measurements for hypersonic flows over expansion corners and ahead of ramps / (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, 1963-1964), by Louis G. Kaufman, sponsor Air Force Flight Dynamics Laboratory (U.S.), issuing agency United States. Air Force. Systems Command. Aeronautical Systems Division, and sponsor Grumman Aircraft Engineering Corporation. Research Department (page images at HathiTrust)
• Heat barrier coatings /, by Buford A. Macklin, Elihu A. Schatz, James C. Withers, issuing agency United States. Air Force. Systems Command. Aeronautical Systems Division, and United States. Air Force. Systems Command. Aeronautical Systems Division. Directorate of Materials and Processesd States. sponsor (page images at HathiTrust)
• High speed flow and aerodynamic heating behavior of porous fibrous structures /, by Myron J. Coplan, sponsor United States. Air Force. Systems Command, and issuing agency United States. Air Force. Systems Command. Aeronautical Systems Division. Directorate of Materials and Processes (page images at HathiTrust)
• Aerodynamic applications of plasma wind tunnels /, by Jackson R. Stalder, Boris Ragent, Charles E. Noble, Frederick K. Goodwin, United States. Air Force. Air Research and Development Command. issuing agency, and United States. Wright Air Development Center. sponsor (page images at HathiTrust)
• Evaluation of several hypersonic turbulent heat transfer analyses by comparison with experimental data, by Paul A. Libby, Robert J. Cresci, sponsor United States. Air Force. Air Research and Development Command, issuing body Wright Air Development Center, and Polytechnic Institute of Brooklyn. |b Department of Aerospace Engineering and Applied Mechanics. sponsor (page images at HathiTrust)
• A study of the overall problems of the true-temperature, hypersonic wind tunnel having semi-continuous operation and the preferred methods of solution. ([Lafayette, Ind., Purdue University, School of Aeronautical Engineering, 1959]), by George M. Palmer (page images at HathiTrust)
• Recent developments connected with the hypersonic facility of the Polytechnic Institute of Brooklyn. Pt. I: Tests of the compression heater. Pt. II: Aspects of the design, construction and installation of a multiple-outlet collector for the convection heater /, by Sergio R. Panunzio, Aerospace Medical Laboratory. sponsor, sponsor United States. Wright Air Development Division, United States. Air Force. Air Research and Development Command. issuing body, and sponsor Polytechnic Institute of Brooklyn (page images at HathiTrust)
• An investigation of the half-model reflection-plane technique for dynamic stability testing at transonic Mach numbers /, by T. O. Shadow, United States. Air Force. Systems Command. issuing body, sponsor Arnold Engineering Development Center, and Inc. ARO (page images at HathiTrust)
• Ablation modeling for dynamic simulation of reentry vehicles : preprint /, by David B. Doman, William B. Blake, and Ohio). Air Vehicles Directorate Air Force Research Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
• Analytical and experimental thermal analysis of a guided bomb /, by W. K. Crain, R. K. Matthews, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Aerodynamic heating and heat transfer phenomena at Mach numbers 3 to 4 /, by K. G. Anderson, J. M. Durben, H. B. Merrell, Wright Air Development Center. issuing body, and United States. Air Force. Air Research and Development Command. sponsor (page images at HathiTrust)
• Applied heat transfer course lecture notes on interference flows /, by Gerald L. Burke and Air Force Flight Dynamics Laboratory (U.S.). issuing body (page images at HathiTrust)
• Laminar, transitional, and turbulent heat transfer measurements on a yawed blunt conical nosetip /, by George F. Widhopf, issuing body United States. Air Force. Systems Command, sponsor Space and Missile Systems Organization (U.S.), and sponsor Aerospace Corporation (page images at HathiTrust)
• Theoretical analysis of the downstream influence of stagnation point mass transfer /, by Robert J. Cresci, issuing body United States. Air Force. Systems Command. Aeronautical Systems Division, sponsor Polytechnic Institute of Brooklyn, and sponsor United States. Wright Air Development Division (page images at HathiTrust)
• Laminar heat transfer on sharp and blunt ten-degree cones in conical and parallel low-density flow /, by David E. Boylan, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Development of test facilities for studies in hypersonic range., by Henry Halle, Channon F. Price, issuing body United States. Air Force. Air Research and Development Command, sponsor United States. Wright Air Development Division, and sponsor University of Chicago (page images at HathiTrust)
• Thermo-structural analysis manual., by H. Switzky, M. Newman, Marvin J. Forray, issuing body United States. Air Force. Systems Command. Aeronautical Systems Division. Directorate of Materials and Processes, and sponsor Republic Aviation Corporation (page images at HathiTrust)
• Development of test facilities for studies in hypersonic range., by Henry Halle, Channon F. Price, issuing body United States. Air Force. Air Research and Development Command, sponsor United States. Wright Air Development Division, and sponsor University of Chicago (page images at HathiTrust)
• Shock wave - turbulent boundary layer interaction in high speed flow /, by Michael S. Holden, issuing body Aerospace Research Laboratories (U.S.), and sponsor Calspan Corporation (page images at HathiTrust)
• Free flight hypersonic heat transfer and boundary layer transition studies: HTV flights A-40 and A-41 /, by James E. Brunk, Warren N. White, issuing body Aerospace Research Laboratories (U.S.), and sponsor Curtiss-Wright Corporation (page images at HathiTrust)
• An Analytical study of the use of air-equivalent hot gaseous mixtures for aerodynamic test purposes /, by Kenneth E. Tempelmeyer, Inc. sponsor ARO, Arnold Engineering Development Center. issuing body, and United States. Air Force. Air Research and Development Command. sponsor (page images at HathiTrust)
• A design manual for determining the thermal characteristics of high speed aircraft /, by H. A. Johnson, L. Possner, E. G. Slack, F. M. Sauer, Morris W. Rubesin, Berkeley. Department of Mechanical Engineering University of California, and issuing agency United States. Army Air Forces. Air Matériel Command (page images at HathiTrust)
• Low-density stagnation-point heat transfer in hypersonic air flow /, by Charles F. Wittliff, Merle R. Wilson, issuing body Aerospace Research Laboratories (U.S.), and sponsor Cornell Aeronautical Laboratory (page images at HathiTrust)
• Three-dimensional shock wave-turbulent boundary layer interactions at Mach 6 /, by C. Herbert Law and issuing body Aerospace Research Laboratories (U.S.) (page images at HathiTrust)

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