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Supersonic wind tunnels

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• Aerodynamics, Supersonic
• Wind tunnels

• Low-speed effects of high-lift devices on the aerodynamic characteristics of a supersonic transport model with outboard tails / (Washington, D.C. : National Aeronautics and Space Administration, 1963), by William C. Sleeman, Paul G. Fournier, Edward J. Ray, and Langley Research Center (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 / (Washington, D.C. : 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 / (Washington, D.C. : National Aeronautics and Space Administration, 1960), by John L. Allen, Glenn A. Mitchell, Owen H. Davis, and Lewis Research Center (page images at HathiTrust)
• Low-speed longitudinal stability characteristics of a supersonic transport configuration with variable-sweep wings employing a double inboard pivot / (Washington, D.C. : National Aeronautics and Space Administration, [1961?]), by William P. Henderson and Langley Research Center (page images at HathiTrust)
• Wind-tunnel investigation at Mach numbers from 1.60 to 2.86 of the static aerodynamic characteristics of a supersonic transport configuration with variable-sweep wings employing a double inboard pivot / (Washington, D.C. : National Aeronautics and Space Administration, [1962?]), by David S. Shaw, William P. Henderson, and Langley Research Center (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 / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Patrick J. Johnston, Robert D. Witcofski, and Langley Research Center (page images at HathiTrust)
• Compressibility effects on fluid entrainment by turbulent mixing layers / ([Washington] : 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)
• Subsonic and supersonic static aerodynamic characteristics of a family of bulbous base cones measured with a magnetic suspension and balance system / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1972), by Milan Vlajinac, Langley Research Center, and Massachusetts Institute of Technology (page images at HathiTrust)
• Effect of diffusers, shrouds, and mass injection on the starting and operating characteristics of a Mach 5 free jet tunnel / (Washington : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], 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)
• Performance of a Mach Number 3.0 design axisymmetric double-cone external-compression inlet in the mach number range 1.97 to 0.79 / (Washington, D.C. : National Aeronautics and Space Administration, 1960), by Owen H. Davis, Glenn A. Mitchell, and Lewis Research Center (page images at HathiTrust)
• Spanwise loadings and aerodynamic characteristics for a series of trailing-edge controls on a 40° sweptback wing at Mach numbers of 1.61 and 2.01/ (Washington, D.C. : National Aeronautics and Space Administration, 1962), by Emma Jean Landrum, K. R. Czarnecki, and Langley Research Center (page images at HathiTrust)
• Wind-tunnel studies at subsonic and transonic speeds of a multiple-mission variable-wing- sweep airplane configuration / (Washington, D.C. : National Aeronautics and Space Administration, 1959), by William J. Alford, William P. Handerson, Arvo A. Luoma, and Langley 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). ([Washington, D.C.] : [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)
• Full committee hearing on H.R. 9612 and S. 3889 / ([Washington, D.C.] : [U.S. G.P.O.], [1950]), by United States House Committee on Armed Services (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 / ([Washington, D.C.] : [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 / ([Washington, D.C.] : [U.S. G.P.O.], [1949]), by United States House Committee on Armed Services (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)
• Effect of jet velocity and axial location of nozzle exit on the performance of a twin-jet afterbody model at Mach numbers up to 2.2 / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 20230], 1969), by Bobbly Lee Berrier, Frederick H. Wood, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Approximation of the spanwise distribution of wind-tunnel-boundary interference on lift of wings in rectangular perforated-wall test sections / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1968), by Ray H. Wright, Benferd L. Schilling, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Power- and cross-spectra and space-time correlations of surface fluctuating pressures at Mach numbers between 1.6 and 2.5 / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va. 22151], 1969), by Wei J. Chyu, Richard D. Hanly, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• A high enthalpy plasma generator for entry heating simulation / (Washington, D. C. : National Aeronautics and Space Administration ; Springfield, Va. : for sale by the Clearinghouse for Federal Scientific and Technical Information, 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)
• Effect of wing location and strakes on stability and control characteristics of a monoplanar circular missile with low-profile tail fins at supersonic speeds / (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 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 / (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 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 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 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 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 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)
• Gust generator for a supersonic wind tunnel / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Bobby W. Sanders, John A. Webb, Allan R. Bishop, and Lewis Research Center (page images at HathiTrust)
• Investigation of light source and scattering medium related to vapor-screen flow visualization in a supersonic wind tunnel / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 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 / (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 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 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 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 / ([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 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 / (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 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 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 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 / (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 Ivan E. Beckwith and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (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 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by W. Pfenninger, J. Syberg, Langley Research Center, and Boeing Commercial Airplane Company (page images at HathiTrust)
• Supersonic wind tunnel nozzles : a selected, annotated bibliography to aid in the development of quiet wind tunnel technology / (Washington, D.C. : National Aeronautics and Space Administration, 1990), by Stephen W. D. Wolf and Ames Research Center. Fluid Dynamics Research Branch (page images at HathiTrust)
• Static longitudinal stability and control characteristics at a mach number of 2.01 of a hypersonic missile configuration having all-movable wing and tail surfaces / (Washington, D.C. : National Aeronautics and Space Administration, 1961), by Ross B. Robinson, Gerald V. Foster, and Langley Research Center (page images at HathiTrust)
• A preliminary investigation of modified blunt 13° half-cone re-entry configurations at subsonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, 1961), by George C. Kenyon, George G. Edwards, and Ames Research Center (page images at HathiTrust)
• Panel flutter studies of boost-vehicle full-scale flight insulation panels / (Washington, D.C. : National Aeronautics and Space Administration, 1967), by Michael L. Nacht, Richard L. Greene, and Lewis Research Center (page images at HathiTrust)
• Some measurements of the dynamic and static stability of two blunt-nosed, low-fineness-ratio bodies of revolution in free flight at M=4 / (Washington, D.C. : National Aeronautics and Space Administration, 1959), by Barbara J. Sort, Simon C. Sommer, and Ames Research Center (page images at HathiTrust)
• Static longitudinal and lateral aerodynamic characteristics at a Mach number of 2.20 of a V/STOL airplane configuration with a variable-sweep wing and with a skewed wing design / (Washington, D.C. : National Aeronautics and Space Administration, 1961), by Odell A. Morris, Gerald V. Foster, and Langley Research Center (page images at HathiTrust)
• Effectiveness of several control arrangements on a Mercury-type capsule / (Washington, D.C. : National Aeronautics and Space Administration, 1961), by Robert I. Sammonds, Robert R. Dickey, and Ames Research Center (page images at HathiTrust)
• A rigidly forced oscillation system for meaasuring dynamic-stability parameters in transonic and supersonic wind tunnels / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce], [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 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce], [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° / (Washington, [D.C.] : 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)
• Stability and control characteristics at a Mach number of 1.97 of an airplane configuration having two types of variable- sweep wings / (Washington, [D.C.] : 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)
• Experimental aerodynamic characteristics at Mach numbers from 0.60 to 2.70 of two supersonic cruise fighter configurations / (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 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 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 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)
• Stability and control characteristics of a monoplanar missile configuration with two low-profile tail arrangements at Mach numbers from 1.70 to 2.86 / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by A. B. Blair and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Wind-tunnel investigation of the validity of a sonic-boom-minimization concept / (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 Robert J. Mack, Christine M. Darden, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• An experimental investigation of a large [Delta]P settling chamber for a supersonic pilot quiet tunnel / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Michael J. Piatt, Systems and Applied Sciences Corporation, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (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. (Washington, D.C. : National Aeronautic and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 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)
• Dynamic response of a Mach 2.5 axisymmetric inlet with engine or cold pipe and utilizing 60 percent supersonic internal area contraction / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Joseph F. Wasserbauer, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Boundary-layer velocity profiles downstream of three-dimensional transition trips on a flat plate at Mach 3 and 4 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1969]), by John B. Peterson, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• An electric resistance air heater for a low density wind tunnel / (1961), by Velvin R. Watson (page images at HathiTrust; US access only)
• Flow-field properties near an arrow-wing : body model at Mach numbers of 1.60, 2.36, and 2.96 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1968), by Robert L. Weirich, Walter A. Vahl, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Aeropropulsion facilities at the NASA Lewis Research Center (Cleveland, Ohio : The Center, [1995]), by Lewis Research Center (page images at HathiTrust)
• Luminescent gas flow visualization in a low-density supersonic wind tunnel /, by Wulf B. Kunkel, United States. Air Force. Air Research and Development Command. sponsor, and Wright Air Development Center issuing body (page images at HathiTrust)
• Preliminary investigation of a variable Mach number two-dimensional supersonic tunnel of fixed geometry / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by William J. Nelson, Frederick Bloetscher, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• A method for the design of porous-wall wind tunnels / (Washington, D.C. : National Advisory Committee for Aeronautics, 1956), by George M. Stokes, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• The high-speed flexible-throat supersonic wind tunnel., 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 /, by Tung-Sheng Liu, Robert K. Knutson, Ernst J. C. Sun, sponsor Wright Air Development Center, and sponsor Rosemount Aeronautical Laboratories (page images at HathiTrust)
• Supersonic wind tunnel tests of the IDS 6208 rocket sled /, by Leroy M. Jenke, United States. Air Force. Arnold Air Force Base. sponsor, Arnold Engineering Development Center. issuing body, and Inc. ARO (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 /, by S. R. Pate, Inc. sponsor ARO, Air Force Flight Dynamics Laboratory (U.S.). sponsor, and Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• Support interference on an ogive-cylinder model at high angle of attack in transonic flow /, by M. C. Altstatt, W. E. Dietz, United States. Air Force. Systems Command. issuing body, sponsor 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 /, by Bob L. Uselton, Fred B. Cyran, United States. Air Force. Systems Command. issuing body, sponsor Arnold Engineering Development Center, and Inc. ARO (page images at HathiTrust)
• Captive trajectory system for AEDC supersonic wind tunnel (A) and hypersonic wind tunnels (B) and (C) /, by T. D. Buchanan, W. A. Crosby, United States. Air Force. Arnold Air Force Base. sponsor, Arnold Engineering Development Center. issuing body, and Calspan Field Services. sponsor (page images at HathiTrust)
• An investigation of separated flows on two-dimensional models at Mach numbers 5 and 8 /, by A. L. Baer, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Calibration and performance of the AEDC/VKF Tunnel C, Mach Number 4, Aerothermal Wind Tunnel /, by W. T. Strike, sponsor Calspan Field Services, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Pressure tests on the standard hypervelocity ballistic model HB-2 at Mach 1.5 to 5 /, by Jerry H. Jones, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Flow characteristics of a 12-in. intermittent supersonic tunnel /, by A. Anderson, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (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 /, by Bob L. Uselton, Frederick B. Cyran, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Boundary-layer characteristics at Mach numbers 2 through 5 in the test section of the 12-inch supersonic tunnel /, by D. R. Bell, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Supersonic flow measurements in the body vortex wake of an ogive nose cylinder /, by William L. Oberkampf, T. J. Bartel, United States. Air Force. Systems Command. sponsor, and Air Force Armament Laboratory. issuing body (page images at HathiTrust)
• Phenomena in supersonic diffusers /, by Heinrich Ramm and issuing agency United States. Army Air Forces. Air Matériel Command (page images at HathiTrust)

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