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Supersonic wind tunnels

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• Aerodynamics, Supersonic
• Wind tunnels

• Supersonic wind tunnels -- Bibliography
• Supersonic wind tunnels -- Data processing
• Supersonic wind tunnels -- Equipment and supplies
• Supersonic wind tunnels -- Experiments
• Supersonic wind tunnels -- Testing
• Supersonic wind tunnels -- United States

• Aeropropulsion facilities, NASA, Lewis Research Center (The Center, 1995), by Lewis Research Center (page images at HathiTrust)
• Investigations in Soviet hypervelocity testing technique; comprehensive report ([Washington], 1965), by Library of Congress. Aerospace Technology Division and Alexis Baratoff (page images at HathiTrust)
• Experimental aerodynamic characteristics at Mach numbers from 0.60 to 2.70 of two supersonic cruise fighter configurations (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by Samuel M. Dollyhigh, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Noise reduction in a Mach 5 wind tunnel with a rectangular rod-wall sound shield (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1980), by Theodore R. Creel, Ivan E. Beckwith, J. Wayne Keyes, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Effect of wing location and strakes on stability and control characteristics of a monoplanar circular missile with low-profile tail fins at supersonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by A. B. Blair, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Correlation of predicted and measured sonic boom characteristics from the reentry of STS-1 Orbiter (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Frank Garcia, Herbert R. Henderson, Jess H. Jones, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Correlations of supersonic boundary-layer transition on cones including effects of large axial variations in wind-tunnel noise (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by Fang-Jenq Chen, Theodore R. Creel, Ivan E. Beckwith, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Analysis of the performance of the drive system and diffuser of the Langley Unitary Plan Wind Tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Lowell E. Hasel, Robert L. Stallings, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
• Stability and control characteristics of a monoplanar missile configuration with two low-profile tail arrangements at Mach numbers from 1.70 to 2.86 (National Aeronautics and Space Administration ;, 1977), by A. B. Blair and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Investigation of light source and scattering medium related to vapor-screen flow visualization in a supersonic wind tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by W. L. Snow, Odell A. Morris, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Nozzle wall roughness effects on free-stream noise and transition in the pilot low-disturbance tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Theodore R. Creel, Fang-Jenq Chen, Ivan E. Beckwith, and Langley Research Center (page images at HathiTrust)
• Description and calibration of the Langley Unitary Plan Wind Tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Charlie M. Jackson, William J. Monta, William A. Corlett, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Experimental and theoretical aerodynamic characteristics of two hypersonic cruise aircraft concepts at Mach numbers of 2.96, 3.96, and 4.63 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Jimmy L. Pittman, Gregory D. Riebe, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Wind-tunnel measurements and comparison with flight of the boundary layer and heat transfer on a hollow cylinder at Mach 3 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Robert L. Stallings, Milton Lamb, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Görtler vortices and transition in wall boundary layers of two Mach 5 nozzles (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Ivan E. Beckwith, Barbara B. Holley, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
• Free-stream noise and transition measurements on a cone in a Mach 3.5 pilot low-disturbance tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Ivan E. Beckwith and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Fluid entrainment (National Aeronautics and Space Administration, 1964), by Jacques A. F. Hill, James E. Nicholson, Inc Mithras, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Reduction of acoustic disturbances in the test section of supersonic wind tunnels by laminarizing their nozzle and test section wall boundary layers by means of suction (National Aeronautics and Space Administration ;, 1974), by W. Pfenninger, J. Syberg, Langley Research Center, and Boeing Commercial Airplane Company (page images at HathiTrust)
• Subsonic and supersonic static aerodynamic characteristics of a family of bulbous base cones measured with a magnetic suspension and balance system (National Aeronautics and Space Administration ;, 1972), by Milan Vlajinac, Langley Research Center, and Massachusetts Institute of Technology (page images at HathiTrust)
• Acoustic and aerodynamic performance investigation of inverted velocity profile connualar plug nozzles / P.R. Knott, J.T. Blozy, and P.S. Staid. (National Aeronautic and Space Administration, Scientific and Technical Information Branch ;, 1981), by P. R. Knott, P. S. Staid, J. T. Blozy, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• NASA TR R-285 (National Aeronautics and Space Administration ;, 1968), by Ray H. Wright, Benferd L. Schilling, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5440 (National Aeronautics and Space Administration ;, 1969), by Wei J. Chyu, Richard D. Hanly, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5338 (National Aeronautics and Space Administration ;, 1969), by Joseph F. Wasserbauer, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5393 (National Aeronautics and Space Administration ;, 1969), by Bobbly Lee Berrier, Frederick H. Wood, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effect of a variable-geometry diffuser on the operating characteristics of a helium tunnel designed for a mach number in excess of 20 (National Aeronautics and Space Administration, 1960), by Patrick J. Johnston, Robert D. Witcofski, and Langley Research Center (page images at HathiTrust)
• NASA TN D-4583 (National Aeronautics and Space Administration ;, 1968), by Charles E. Shepard, John W. Vorreiter, Donald M. Ketner, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Preliminary investigation of modified blunt 13 degree half-cone re-entry configurations at subsonic speeds (National Aeronautics and Space Administration, 1961), by George C. Kenyon, George G. Edwards, and Ames Research Center (page images at HathiTrust)
• A rigidly forced oscillation system for meaasuring dynamic-stability parameters in transonic and supersonic wind tunnels (National Aeronautics and Space Administration :, 1962), by Albert L. Braslow, Cullen Q. Lee, Harleth G. Wiley, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effects of forebody length on the stability and control characteristics at a Mach number of 2.01 of a canard airplane configuration with a trapezoidal aspect-ratio-3 wing (National Aeronautics and Space Administration :, 1962), by M. Leroy Spearman, Cornelius Driver, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Aerodynamic characteristics in pitch at a Mach number of 1.97 of two variable-wing- sweep V/STOL configurations with outboard wing panels swept back 75 degree (National Aeronautics and Space Administration, 1960), by Gerald V. Foster, Odell A. Morris, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effect of diffusers, shrouds, and mass injection on the starting and operating characteristics of a Mach 5 free jet tunnel (National Aeronautics and Space Administration :, 1971), by John K. Molloy, J. Wayne Keyes, Ernest A. Mackley, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Stability and control characteristics at a Mach number of 1.97 of an airplane configuration having two types of variable- sweep wings (National Aeronautics and Space Administration, 1960), by Gerald V. Foster, Odell A. Morris, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Sideslip characteristics at various angles of attack for several hypersonic missile configurations with canard controls at a mach number of 2.01 (National Aeronautics and Space Administration, 1959), by Gerald V. Foster and Langley Research Center (page images at HathiTrust)
• Performance summary and analysis of a Mach 3.0 design axisymmetric all-external-compression double-cone inlet Mach number range 3.0 to 0.8 (National Aeronautics and Space Administration, 1960), by John L. Allen, Glenn A. Mitchell, Owen H. Davis, and Lewis Research Center (page images at HathiTrust)
• Preliminary investigation of a variable Mach number two-dimensional supersonic tunnel of fixed geometry (National Advisory Committee for Aeronautics, 1949), by William J. Nelson, Frederick Bloetscher, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• A method for the design of porous-wall wind tunnels (National Advisory Committee for Aeronautics, 1956), by George M. Stokes, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Performance of a Mach Number 3.0 design axisymmetric double-cone external-compression inlet in the mach number range 1.97 to 0.79 (National Aeronautics and Space Administration, 1960), by Owen H. Davis, Glenn A. Mitchell, and Lewis Research Center (page images at HathiTrust)
• To promote the national defense by authorizing a unitary plan for the construction of transsonic and supersonic wind-tunnel facilities and the establishment of an air engineering development center (H.R. 3434). ([U.S. G.P.O.], 1949), by United States House Committee on Armed Services, Carl Vinson, Jerome C. Hunsaker, and James Forrestal (page images at HathiTrust)
• Subcommittee hearings on H.R. 3434, to promote the national defense by authorizing a unitary plan for the construction of transonic and supersonic wind-tunnel facilities and the establishment of an air engineering development center ([U.S. G.P.O.], 1949), by United States. Congress. House. Committee on Armed Services. Subcommittee No. 3 (page images at HathiTrust)
• Full committee hearings on H.R. 2895, S. 509, S. 1267, S. 2382, S. 2380, S. 1560, H.R. 5876 ([U.S. G.P.O.], 1949), by United States House Committee on Armed Services (page images at HathiTrust)
• An electric resistance air heater for a low density wind tunnel (1961), by Velvin R. Watson (page images at HathiTrust)
• The high-speed flexible-throat supersonic wind tunnel. (Aberdeen Proving Ground, Maryland : Ballistic Research Laboratories, [1948?], 1948), by U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• The design and performance of a regenerative-type heater for an intermittent supersonic wind tunnel (Wright-Patterson Air Force Base, Ohio, Wright Air Development Center, Air Research and Development Command, United States Air Force, 1957., 1957), by Tung-Sheng Liu, Robert K. Knutson, Ernst J. C. Sun, Wright Air Development Center, and Rosemount Aeronautical Laboratories (page images at HathiTrust)
• Supersonic wind tunnel tests of the IDS 6208 rocket sled (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 Leroy M. Jenke, United States. Air Force. Arnold Air Force Base, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
• An investigation of separated flows on two-dimensional models at Mach numbers 5 and 8 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1963., 1963), by A. L. Baer, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Investigation of drag reduction by boundary-layer suction on a body of revolution at Mach numbers 2.5, 3, and 3.5 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Von Kármán Gas Dynamics Facility, Air Research and Development Command, United States Air Force, 1965., 1965), by S. R. Pate, Inc ARO, Air Force Flight Dynamics Laboratory (U.S.), and Arnold Engineering Development Center (page images at HathiTrust)
• Calibration and performance of the AEDC/VKF Tunnel C, Mach Number 4, Aerothermal Wind Tunnel (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1982., 1982), by W. T. Strike, Calspan Field Services, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Pressure tests on the standard hypervelocity ballistic model HB-2 at Mach 1.5 to 5 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1964., 1964), by Jerry H. Jones, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Phenomena in supersonic diffusers (Wright Field, Dayton, Ohio : Headquarters Air Materiel Command, 1947., 1947), by Heinrich Ramm and United States. Army Air Forces. Air Matériel Command (page images at HathiTrust)
• Flow characteristics of a 12-in. intermittent supersonic tunnel (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1963., 1963), by A. Anderson, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Sting interference effects as determined by measurements of dynamic stability derivatives, surface pressure, and base pressure for Mach numbers 2 through 8 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1980., 1980), by Bob L. Uselton, Frederick B. Cyran, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Support interference on an ogive-cylinder model at high angle of attack in transonic flow (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnet Facility, Air Force Systems Command, United States Air Force, 1978., 1978), by M. C. Altstatt, W. E. Dietz, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
• Critical sting length as determined by the measurement of pitch-damping derivatives for laminar, transitional, and turbulent boundary layers at Mach number 3 for reduced frequencies of 0.0033 and 0.0056 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Von Karman Gas Dynaqmics Facility, Air Force Systems Command, United States Air Force, 1977., 1977), by Bob L. Uselton, Fred B. Cyran, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
• Boundary-layer characteristics at Mach numbers 2 through 5 in the test section of the 12-inch supersonic tunnel (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1963., 1963), by D. R. Bell, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Captive trajectory system for AEDC supersonic wind tunnel (A) and hypersonic wind tunnels (B) and (C) (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1983., 1983), by T. D. Buchanan, W. A. Crosby, United States. Air Force. Arnold Air Force Base, Arnold Engineering Development Center, and Calspan Field Services (page images at HathiTrust)

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