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Shock tubes

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• Ballistic ranges
• Shock (Mechanics)
• Shock waves

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• Shock tunnels

• Shock tube experiments on snow / (Hanover, N.H. : U.S. Army Materiel Command, Terrestrial Sciences Center, Cold Regions Research & Engineering Laboratory, 1969), by Jim Smith (page images at HathiTrust)
• An experimental investigation of wall boundary-layer transition Reynolds numbers in an expansion tube / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by K. James Weilmuenster and Langley Research Center (page images at HathiTrust)
• The shock expansion tube and its application as a sonic boom simulator / (Washington, D.C. : National Aeronautics and Space Administration, 1968), by Hugo E. Dahlke, Langley Research Center, LTV Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• An analysis of the relaxation of laminar boundary layer on a flat plate after passage of an interface with application to expansion-tube flows / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by Roop N. Gupta and Langley Research Center (page images at HathiTrust)
• Description and initial operating performance of the Langley 6-inch expansion tube using heated helium driver gas / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by John A. Moore and Langley Research Center (page images at HathiTrust)
• A Nonlinear theory for predicting the effects of unsteady laminar, turbulent, or transitional boundary layers on the attenuation of shock waves in a shock tube with experimental comparison, (Washington, D.C. : U.S. G.P.O., 1961), by Robert L. Trimpi, Nathaniel B. Cohen, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Experimental performance of an internal resistance heater for Langley 6-inch expansion tube driver / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by Thomas R. Creel and Langley Research Center (page images at HathiTrust)
• Shock-tube study of the reaction H + O₂ + Ar [rightward-pointing arrow] HO₂ + Ar / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by Casimir J. Jachimowski, William M. Houghton, and Langley Research Center (page images at HathiTrust)
• Relaxation of an unsteady turbulent boundary layer on a flat plate in an expansion tube / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Roop N. Gupta, Robert L. Trimpi, and Langley Research Center (page images at HathiTrust)
• Program and charts for determining shock tube, expansion tube, and expansion tunnel flow quantities for real air / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Charles G. Miller, Sue E. Wilder, and Langley Research Center (page images at HathiTrust)
• Investigation of an anomalous flow condition of the Langley pilot model expansion tube / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Wilfred J. Friesen and Langley Research Center (page images at HathiTrust)
• Shock shapes on blunt bodies in hypersonic-hypervelocity helium, air, and CO₂ flows, and calibration results in Langley 6-inch expansion tube / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Charles G. Miller and Langley Research Center (page images at HathiTrust)
• A comparison of measured and predicted test flow in an expansion tube with air and oxygen test gases / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Kenneth V. Haggard, William K. Goad, and Langley Research Center (page images at HathiTrust)
• A finite-difference analysis of the nozzle starting process in an expansion tunnel / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by K. James Weilmuenster and Langley Research Center (page images at HathiTrust)
• A magnetically insulated shock tube, (Los Angeles, Physical Research Laboratory, Space Technology Laboratories, [1960?]), by Richard Gildart Fowler and Eugene B. Turner (page images at HathiTrust)
• Wave superheater hypersonic tunnel; semiannual report, (Buffalo, 1959-), by Cornell Aeronautical Laboratory and James E. Carpenter (page images at HathiTrust)
• Single-pulse shock tube studies of the kinetics of the reaction N + O [arrow right over arrow left (reversible reaction)] 2 NO between 2000-3000⁰ K, (Buffalo, Cornell Aeronautical Laboratory, Inc., 1957), by Herbert S. Glick, W. Squire, and J. J. Klein (page images at HathiTrust)
• Engineering design of a wave superheater facility for hypersonic research and development. (Buffalo, Cornell Aeronautical Laboratory, Inc., 1959), by James E. Carpenter (page images at HathiTrust)
• Test time in low pressure shock tubes. (El Segundo?], 1962), by Aerospace Corporation and Harold Mirels (page images at HathiTrust)
• Shock tube driver techniques and attenuation measurements, (Buffalo, Cornell Aeronautical Laboratory, Inc., 1957), by Charles E. Wittliff and Merle R. Wilson (page images at HathiTrust)
• 48-inch hypersonic shock tunnel; description and capabilities. (Buffalo, 1962), by Cornell Aeronautical Laboratory (page images at HathiTrust)
• Interferometric measurement in a shock tube of dissociation rates for air and its component gases. (Ithaca, N. Y., [1959?]), by Stanley Richard Byron (page images at HathiTrust)
• Theory of electron driven shock waves (Los Angeles, Physical Research Laboratory, Space Technology Laboratories, 1960), by Richard Gildart Fowler and Burton D. Fried (page images at HathiTrust)
• Plasma studies in a shock tube, (Buffalo, Cornell Aeronautical Laboratory, 1961), by John W. 1935- Daiber and Herbert S. Glick (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)
• Preliminary researchon a molecular beam for the 1-10 ev range, (Buffalo, Cornell Aeronautical Laboratory, 1959), by G. T. Skinner and Charles E. Treanor (page images at HathiTrust)
• Instrumentation for force and pressure measurements in a hypersonic shock tunnel (Buffalo, Cornell Aeronautical Laboratory, Inc., 1962), by James F. Martin, Leroy M. Stevenson, and George R. Duryea (page images at HathiTrust)
• Hypersonic research in the shock tunnel. ([New York?] Institute of the Aeronautical Sciences, [1960?]), by Charles E. Wittliff (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)
• Resistance thermometer for heat transfer measurement in a shock tube, (Pasadena, Guggenheim Aeronautical Laboratory, California Institute of Technolgy, 1956), by Josef Rabinowicz, C. A. Bartsch, and M. E. Jessey (page images at HathiTrust)
• A digital computer program for calculating the performance of single-or multiple-diaphragm shock tubes for arbitrary equilibrium real gas mixtures / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1968), by William L. Grose, Jane T. Kemper, John E. Nealy, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Shock tube test time limitation due to turbulent wall boundary layer. ([El Segundo?], 1963), by Aerospace Corporation and Harold Mirels (page images at HathiTrust)
• Investigation of test time at undertailored conditions in a shock tunnel. (Buffalo, Cornell Aeronautical Laboratory, Inc., [195-?]), by James F. Martin and Cornell Aeronautical Laboratory Hypersonic Research Dept (page images at HathiTrust)
• An analysis of combustion studies in shock expansion tunnels and reflected shock tunnels / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Casimir J. Jachimowski and Langley Research Center (page images at HathiTrust)
• Description and operating performance of a parallel-rail electric-arc system with helium driver gas for the Langley 6-inch expansion tube / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by John A. Moore, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Experimental perfect-gas study of expansion-tube flow characteristics / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Judy L. Shinn, Charles G. Miller, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Comparison of convective stagnation heat transfer in air, CO₂-N₂, and CO₂-Ar gas mixtures / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1967]), by Clifford M. Akin, Joseph G. Marvin, and Ames Research Center (page images at HathiTrust)
• Contact-surface tailoring in real shock tubes / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1965]), by Theodore A. Brabbs, Frank E. Belles, and Lewis Research Center (page images at HathiTrust)
• General chemical kinetics computer program for static and flow reactions, with application to combustion and shock-tube kinetics [electronic resource] / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1972), by David A. Bittker, Vincent J. Scullin, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Application of shock tubes to transonic airfoil testing at high Reynolds numbers / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, William John Cook, and Iowa State University (page images at HathiTrust)
• Experimental and theoretical studies on the formation of detonation waves in variable geometry tubes / (Washington : National Aeronautics and Space Administration, [1963]), by Loren E. Bollinger, United States National Aeronautics and Space Administration, and Ohio State University (page images at HathiTrust)
• Evaluation of shock-tube heat-transfer experiments to measure thermal conductivity of argon from 700 ̊to 8600 ̊K / (Washington, D.C. : National Aeronautics and Space Administration : For sale by the Office of Technical Services, Dept. of Commerce, [1964]), by Milton R. Lauver and Lewis Research Center (page images at HathiTrust)
• Absolute radiometers for use in ballistic-range and shock-tube experiments / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Roger A. Craig, William C. Davy, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Shock-tube flow analysis with a dimensionless velocity number / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1969]), by N. Muniswamy Reddy, United States National Aeronautics and Space Administration, and Ames 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)
• Shock tube determination of the drag coefficient of small spherical particles / (Washington, D.C. : National Aeronautics and Space Administration, 1966), by Bruce P. Selberg (page images at HathiTrust; US access only)
• Effects of boundary layer buildup in shock tubes upon chemical rate measurements / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1968), by Marvin Warshay, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• The shock tube as an instrument for the investigation of transonic and supersonic flow patterns : a report on work done under Office of Naval Research contract N6-ONR-232 between April, 1947 and June, 1949 / (Washington, [1949]), by Frederick William Geiger, Charles William Mautz, and University of Michigan. Office of Research Administration (page images at HathiTrust)
• Evaluation of expansion chambers in shock tubes /, by Horst P. Richter, Lawrence Radiation Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Evaluation of expansion chambers in shock-tube experiments with mass addition /, by Horst P. Richter and U.S. Atomic Energy Commission (page images at HathiTrust)
• Shock tube pulse shaper /, by R. J. Herrmann, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Measurement of frequency response of pressure gauges by a high-pressure shock tube technique /, by S. P. Pfaff, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Wind tunnel simulation of head-on bow wave-blast wave interactions /, by David L. Merritt, P. M. Aronson, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• The tolerance of guinea pigs to air blast when mounted in shallow, deep, and deep-with-offset chambers on a shock tube /, by Donald R. Richmond, Clayton S. White, Victor R. Clare, Lovelace Foundation for Medical Education and Research, and United States. Defense Atomic Support Agency (page images at HathiTrust)
• The effect of wall friction on the strength of shock waves in tubes and hydraulic jumps in channels / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by Coleman duP. Donaldson, Roger D. Sullivan, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Experimental studies of shock-shock interactions on a 9° cone /, by David L. Merritt, Philip M Aronson, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• An electromagnetic shock tube for aerodynamic research /, by Richard W. Ziemer and inc. Space Technology Laboratories (page images at HathiTrust)
• Mortality in small animals exposed in a shock tube to "sharp"-rising overpressures of 3-4 MSEC duration /, by Donald R. Richmond, Clayton S. White, C. C. Fischer, R. T. Sanchez, F. Sherping, D. R. Pratt, Victor R. Clare, V. C. Goldizen, Lovelace Foundation for Medical Education and Research, and United States. Defense Atomic Support Agency (page images at HathiTrust)
• The effects of shock tube generated, step-rising overpressures on guinea pigs located in shallow chambers oriented side-on and end-on to the incident shock /, by Victor R. Clare, Clayton S. White, C. S. Gaylord, D. R. Pratt, C. C. Fischer, V. C. Goldizen, Donald R. Richmond, Lovelace Foundation for Medical Education and Research, and United States. Defense Atomic Support Agency (page images at HathiTrust)
• Orbital "blow-out" fractures in dogs produced by air blast /, by Donald R. Richmond, Clayton S. White, D. R. Pratt, Lovelace Foundation for Medical Education and Research, and United States. Defense Atomic Support Agency (page images at HathiTrust)
• Photoionization of N₂ and O₂ ahead of strong shock waves in a shock tube /, by A. J. Mulac, Sandia Corporation, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Shock-tube diagnostics utilizing laser raman spectroscopy /, by Anthony A Boiarski and Naval Surface Weapons Center. : White Oak Laboratory (page images at HathiTrust)
• Kinetics of reactions in shock tubes /, by S. H. Bauer, sponsor Cornell University, sponsor United States. Wright Air Development Division, and United States. Air Force. Air Research and Development Command. issuing body (page images at HathiTrust)
• Shock tube studies of the effects of sharp-rising, long-duration overpressures on biological systems /, by V. C. Goldizen, C. S. White, M. B. Wetherbe, R. V. Taborelli, F. Sherping, R. T. Sanchez, D. R. Richmond, U.S. Atomic Energy Commission, Air Force Special Weapons Center (U.S.), and Va.) International Shock Tube Symposium (3rd : 1959 : Fort Monroed (page images at HathiTrust)
• Shock tubes : a bibliography / Arnold M. Melnick. (Miamisburg, Ohio. : Mound Laboratory, Monsanto Research Corp., 1964), by Arnold M. Melnick, U.S. Atomic Energy Commission, and Mound Laboratory (page images at HathiTrust)
• Development of an aeroacoustic methodology to evaluate heatshield material performance /, by A. L. Laganelli, sponsor Air Force Flight Dynamics Laboratory (U.S.), sponsor Air Force Wright Aeronautical Laboratories, and inc. Science Applications (page images at HathiTrust)
• Development of a miniature pressure transducer for application to airfoil studies in the shock tube /, by J. Ray Ruetenik, United States. Air Force. Air Research and Development Command. issuing body, Wright Air Development Center sponsor, and sponsor Massachusetts Institute of Technology. Aeroelastic and Structures Research Laboratory (page images at HathiTrust)
• Investigations into shock-induced enhancement of mixing and combustion in supersonic burners /, by Frank E. Marble, California Institute of Technology. sponsor, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• High altitude shock wave structure : Part 1 and Part 2 /, by S. M. Scala, B. B. Cary, Lawrence Talbot, United States. Air Force. Office of Scientific Research. issuing body, and General Electric Company. Space Sciences Laboratory. sponsor (page images at HathiTrust)
• Optimization of a low heat load turbine inlet vane /, by Jamie J. Johnson, Ryan P. Lemaire, Michael J. Flanagan, John P. Clark, Paul I. King, United States. Air Force. Material Command. sponsor, and Ohio). |b Propulsion Directorate. issuing body Air Force Research Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)

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