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Mach number

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• Aerodynamics
• Compressibility

• Mach number -- Tables
• Mach number -- Testing
• Aerodynamics, Hypersonic

• Effects of wing planform on the aerodynamic characteristics of a wing-body-tail model at Mach numbers 3.96 and 4.63 (National Aeronautics and Space Administration ;, 1966), by Maurice O. Feryn and Langley Research Center (page images at HathiTrust)
• Aerodynamic characteristics of a 0.0667-scale model of the X-15A-2 research airplane at transonic speeds (National Aeronautics and Space Administration ;, 1966), by James C. Patterson and Langley Research Center (page images at HathiTrust)
• Experimental investigation of base flow field at high altitudes for configurations of four and five clustered nozzles (National Aeronautics and Space Administration ;, 1967), by R. A. Wasko, T. L. Cover, and Lewis Research Center (page images at HathiTrust)
• Flight evaluation of splitter-plate effectiveness in reducing base drag at Mach numbers from 0.65 to 0.90 (National Aeronautics and Space Administration ;, 1967), by Edwin J. Saltzman, John Hintz, and Flight Research Center (U.S.) (page images at HathiTrust)
• Experimental evaluation of wall Mach number distributions of the octagonal test section proposed for NASA Lewis Research Center's altitude wind tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1986), by Douglas E. Harrington, Robert R. Corban, Richard R. Burley, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Flight and wind-tunnel measurements showing base drag reduction provided by a trailing disk for high Reynolds number turbulent flow for subsonic and transonic Mach numbers (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1986), by Sheryll Goecke Powers, Charles H. Fox, Jarrett K. Huffman, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Effect of Reynolds number and Mach number on flow angularity probe sensitivity (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1986), by Leigh Ann Smith, Jerry B. Adcock, and Langley Research Center (page images at HathiTrust)
• Experimental aerodynamic characteristics for slender bodies with thin wings at angles of attack from 0 ̊to 58 ̊and Mach numbers from 0.6 to 2.0 (National Aeronautics and Space Administration ;, 1976), by Leland H. Jorgensen, Michael H. Howell, and Ames Research Center (page images at HathiTrust)
• Experimental aerodynamic characteristics for slender bodies with thin wings and tail at angles of attack from 0 ̊to 58 ̊and Mach from 0.6 to 2.0 (U.S. National Aeronautics and Space Administration ;, 1976), by Leland H. Jorgensen, Edgar R. Nelson, and Ames Research Center (page images at HathiTrust)
• An investigation of several NACA 1-series inlets at Mach numbers from 0.4 to 1.29 for mass-flow ratios near 1.0 (U.S. National Aeronautics and Space Administration ;, 1976), by Richard J. Re and Langley Research Center (page images at HathiTrust)
• In-flight transition measurement on a 10⁰ cone at Mach numbers from 0.5 to 2.0 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by David F. Fisher, N. Sam Dougherty, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Dryden Flight Research Facility (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)
• Assessment of a transitional boundary layer theory at low hypersonic mach numbers (National Aeronautics and Space Administration ;, 1972), by S. J. Shamroth, H. McDonald, Langley Research Center, and United Aircraft Corporation (page images at HathiTrust)
• Numerical calculations of viscous compressible fluid flow around a stationary cylinder (National Aeronautics and Space Administration ;, 1970), by John G. Trulio, Leonard Walitt, George C. Marshall Space Flight Center, and inc Applied Theory (page images at HathiTrust)
• Design of a convective cooling system for a Mach 6 hypersonic transport airframe (National Aeronautics and Space Administration ;, 1971), by R. G. Helenbrook, F. M. Anthony, Langley Research Center, and Bell Aerospace Company (page images at HathiTrust)
• Airfoil at supersonic mach number (National Aeronautics and Space Administration, 1965), by Lucien A. Schmit, William A. Thornton, Case Institute of Technology, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• A study of the effects of Reynolds number and mach number on constant pressure coefficient jump for shock-induced trailing-edge separation (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1987), by Atlee M. Cunningham and Gregory S. Spragle (page images at HathiTrust)
• NASA TR R-82 (National Aeronautics and Space Administration ;, 1961), by Fred W. Matting, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• Effect of afterbody geometry and sting diameter on the aerodynamic characteristics of slender bodies at Mach number from 1.57 to 2.86 (National Aeronautics and Space Administration :, 1963), by Dennis E. Fuller, Victor E. Langhans, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-1979 (National Aeronautics and Space Administration, 1963), by Donald M. Kuehn, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TR R-182 (National Aeronautics and Space Administration ; [For sale by the Office of Technical Services, Department of Commerce, Washington, D.C. 20230], 1963), by Richard D. Wagner, Ralph Watson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effects of a lower surface jet on the lift-drag ratio of a 45° sweptback wing at a Mach number of 2.01 (National Aeronautics and Space Administration, 1960), by Emma Jean Landrum and Langley Research Center (page images at HathiTrust)
• An experimental investigation at a Mach number of 4.95 of flow in the vicinity of a 90 degree interior corner alined with the free-stream velocity (National Aeronautics and Space Administration, 1960), by P. Calvin Stainback and Langley Research Center (page images at HathiTrust)
• The interpretation of nonlinear pitching moments in relation to the pitch-up problem (National Aeronautics and Space Administration, 1959), by George S. Campbell, Joseph Weil, and Langley Research Center (page images at HathiTrust)
• NASA TN D-2340 (National Aeronautics and Space Administration :, 1964), by Earl A. Price, Robert L. Stallings, Paul W. Howard, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-2483 (National Aeronautics and Space Administration ; [For sale by the Office of Technical Services, Department of Commerce, Washington, D.C. 20230], 1964), by Lawrence W. Brown, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-3734 (National Aeronautics and Space Administration [for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia], 1966), by Joseph W. Bursik, George C. Marshall Space Flight Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Blowoff of propane and hydrogen diffusion flames at high Mach number, ramjet conditions (National Aeronautics and Space Administration, 1959), by Robert J. Bacigalupi, Erwin A. Lezberg, and Lewis Research Center (page images at HathiTrust)
• Transonic wind-tunnel tests of an error-compensated static-pressure probe (National Aeronautics and Space Administration, 1961), by Francis J. Capone, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Effectiveness of an all-movable horizontal tail on an unswept-wing and body combination for Mach numbers from 0.60 to 1.40 (National Aeronautics and Space Administration, 1959), by Louis S. Stivers and Ames Research Center (page images at HathiTrust)
• Wing-on and wing-off longitudinal characteristics of an airplane configuration having a thin unswept wing of aspect ratio 3, as obtained from rocket-propelled models at Mach numbers from 0.8 to 1.4 (National Aeronautics and Space Administration, 1959), by Clarence L. Gillis, A. James Vitale, and Langley Research Center (page images at HathiTrust)
• Panel flutter tests on full-scale X-15 lower vertical stabilizer at Mach number of 3.0 (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)
• Experimental investigation of the effects of compressive stress on the flutter of a curved panel and a flat panel at supersonic Mach numbers (National Aeronautics and Space Administration, 1962), by R. W. Hess, Frederick W. Gibson, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• NASA TN D-5121 (National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by James C. Ellison, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-5297 (National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Lana M. Couch, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Flutter at very high speeds (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)
• Static longitudinal stability of a rocket vehicle having a rear-facing step ahead of the stabilizing fins (National Aeronautics and Space Administration, 1961), by Robert J. Keynton, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Static longitudinal characteristics at high subsonic speeds of a complete airplane model with a highly tapered wing having the 0.80 chord line unswept and with several tail configurations (National Aeronautics and Space Administration, 1961), by Kenneth W. Goodson, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Investigation of the aerodynamic characteristics of a hypersonic transport model at Mach numbers to 6 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1971), by James C. Ellison, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• NASA TN D-6060 (National Aeronautics and Space Administration :, 1971), by James M. Cubbage, F. S. Kirkham, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5754 (National Aeronautics and Space Administration, 1970), by W. Frank Staylor, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Sonic-boom characteristics in the extreme near field of a complex airplane model at mach numbers of 1.5, 1.8, and 2.5 (National Aeronautics and Space Administration, 1970), by Odell A. Morris, Harry W. Carlson, Milton Lamb, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5861 (National Aeronautics and Space Administration :, 1970), by William F. Hinson, Dennis M. Bushnell, Paul B. Gooderum, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-4796 (National Aeronautics and Space Administration :, 1968), by Emma Jean Landrum, Barrett L. Shrout, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Aerodynamics of a model of the HL-10 flight-test vehicle at Mach 0.35 to 1.80 (National Aeronautics and Space Administration, 1971), by Charles L. Ladson, Acquilla S. Hill, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5030 (National Aeronautics and Space Administration ;, 1969), by Robert J. McGhee, James A. Martin, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-5885 (National Aeronautics and Space Administration :, 1970), by William J. Small, David E. Fetterman, Frank S. Kirkham, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Effect of speed brakes on the supersonic aerodynamic characteristics of a variable-sweep tactical fighter model at Mach numbers from 1.60 to 2.50 (National Aeronautics and Space Administration, 1968), by Celia S. Richardson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5952 (National Aeronautics and Space Administration :, 1970), by George E. Kaattari, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-5901 (National Aeronautics and Space Administration :, 1970), by Charles G. Miller, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-4843 (National Aeronautics and Space Administration :, 1968), by Bobby L. Berrier, Odis C. Pendergraft, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-5379 (National Aeronautics and Space Administration ;, 1969), by John P. Decker, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5713 (National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by Howard Tashjian, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-5717 (National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by Martin Hersch, Frederick P. Povinelli, Louis A. Povinelli, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Effects of Reynolds number and body corner radius on aerodynamic characteristics of a space shuttle-type vehicle at subsonic Mach numbers (National Aeronautics and Space Administration, 1972), by Leland H. Jorgenson, Jack J. Brownson, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• Comparison of hinge moments for a simple delta wing and a delta-wing orbiter concept at mach 6 (National Aeronautics and Space Administration, 1972), by George C. Ashby, Langley Research Center, 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 (National Aeronautics and Space Administration, 1960), by Robert G. Dorsch, Murray Dryer, Harrison Allen, and Lewis Research Center (page images at HathiTrust)
• Effects of jet billowing on stability of missile-type bodies at Mach 3.85 (National Aeronautics and Space Administration, 1960), by Reino J. Salmi and Lewis Research Center (page images at HathiTrust)
• Compressibility effects on the hovering performance of a two-blade 10-foot-diameter helicopter rotor operating at tip Mach numbers up to 0.98 (National Aeronautics and Space Administration, 1960), by Joesph W. Jewel 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 (National Aeronautics and Space Administration, 1960), by Patrick J. Johnston, Robert D. Witcofski, and Langley Research Center (page images at HathiTrust)
• Combined operations with and without afterburning for minimum fuel consumption in level flight (National Aeronautics and Space Administration, 1959), by Angelo Miele, Carlos R. Cavoti, and Purdue University (page images at HathiTrust)
• Measurement of flow angularity at supersonic and hypersonic speeds with the use of a conical probe (National Aeronautics and Space Administration, 1961), by Frank E. Swalley, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Experimental investigation at a Mach number of 3.11 of the lift, drag, and pitching-moment characteristics of five blunt lifting bodies (National Aeronautics and Space Administration, 1960), by William Letko and Langley Research Center (page images at HathiTrust)
• Experimental investigation of the effect of aspect ratio and Mach number on the flutter of cantilever wings (National Aeronautics and Space Administration, 1960), by E. Widmayer, S. A. Clevenston, W. T. Lauten, and Langley Research Center (page images at HathiTrust)
• Ground measurements of airplane shock-wave noise at Mach numbers to 2.0 and at altitudes to 60,000 feet (National Aeronautics and Space Administration, 1960), by Lindsay J. Lina, Domenic J. Maglieri, and Langley Research Center (page images at HathiTrust)
• NASA TN D-4679 (National Aeronautics and Space Administration ;, 1968), by Walter A. Vahl, Robert L. Weirich, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Free-flight investigation at Mach numbers between 0.5 and 1.7 of the zero-lift rolling effectiveness and drag of various surface, spoiler, and jet controls on an 80° delta-wing missile (National Aeronautics and Space Administration, 1960), by Eugene D. Schult and Langley Research Center (page images at HathiTrust)
• An exploratory investigation of a transport configuration designed for supersonic cruise flight near a Mach number of 3 (National Aeronautics and Space Administration, 1960), by Ausley B. Carraway, Melvin M. Carmel, Donald T. Gregory, and Langley Research Center (page images at HathiTrust)
• Span loadings and aerodynamic characteristics for a series of tip and trailing-edge controls on a 60 degree delta wing at Mach numbers of 1.61 and 2.01 (National Aeronautics and Space Administration, 1959), by K. R. Czarnecki, Douglas R. Lord, and Langley Research Center (page images at HathiTrust)
• Flight test of a 31.2-foot-diameter modified ringsail parachute deployed at a Mach number of 1.39 and a dynamic pressure of 11.0 pounds per square foot (National Aeronautics and Space Administration, 1967), by John S. Preisser, Harold N. Murrow, Clinton V. Eckstrom, and Langley Research Center (page images at HathiTrust)
• Lift and drag characteristics at subsonic speeds and at a Mach number of 1.9 of a lifting circular cylinder with a fineness ratio of 10 (National Aeronautics and Space Administration, 1959), by Vernard E. Lockwood, Linwood W. McKinney, and Langley Research Center (page images at HathiTrust)
• NASA TN D-1823 (National Aeronautics and Space Administration, 1963), by Odell A. Morris, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-6280 (National Aeronautics and Space Administration ;, 1971), by Theodore J. Goldberg, Jerry N. Hefner, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Longitudinal aerodynamic characteristics of several high-drag bodies at Mach numbers from 1.50 to 4.63 (National Aeronautics and Space Administration :, 1967), by James F. Campbell and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Ground measurements of the shock-wave noise from airplanes in level flight at Mach numbers to 1.4 and at altitudes to 45,000 feet (National Aeronautics and Space Administration, 1959), by Domenic J. Maglieri, Donald L. Lansing, Harvey H. Hubbard, and Langley Research Center (page images at HathiTrust)
• Method for predicting off-design performance of axial-flow compressor blade rows (National Aeronautics and Space Administration, 1959), by G. K. Serovy, E. W. Anderson, and Iowa State College (page images at HathiTrust)
• The effects of an inverse-taper leading-edge flap on the aerodynamic loading characteristics of a 45° sweptback wing at Mach numbers to 0.90 (National Aeronautics and Space Administration, 1959), by Fred A. Demele and Ames Research Center (page images at HathiTrust)
• Aerodynamic damping at Mach numbers of 1.3 and 1.6 of a control surface on a two-dimensional wing by the free-oscillation method (National Aeronautics and Space Administration, 1960), by W. J. Tuovila, R. W. Hess, and Langley Research Center (page images at HathiTrust)
• An analysis of incremental horizontal-tail loads measured on a swept-wing bomber airplane in sideslip maneuvers (National Aeronautics and Space Administration, 1959), by William A. McGowan and Langley Research Center (page images at HathiTrust)
• Measured and theoretical flow fields behind a rectangular and a triangular wing up to high angles of attack at a Mach number of 2.46 (National Aeronautics and Space Administration, 1959), by Frank J. Centolanzi and Ames Research Center (page images at HathiTrust)
• Rough-water ditching investigation of a model of a jet transport with the landing gear extended and with various ditching aids (National Aeronautics and Space Administration, 1959), by William C. Thompson and Langley Research Center (page images at HathiTrust)
• Vibration and near-field sound of thin-walled cylinders caused by internal turbulent flow (National Aeronautics and Space Administration, 1960), by Paul F. R. Weyers and California Institute of Technology (page images at HathiTrust)
• Investigation at transonic speeds to determine lateral control effectiveness of blowing laterally over surfaces of 30° and 45° swept wings (National Aeronautics and Space Administration, 1959), by Alexander D. Hammond, Linwood W. McKinney, and Langley Research Center (page images at HathiTrust)
• Effects of body and fin deflections on the aerodynamic characteristics in pitch of a 0.065-scale model of a four-stage rocket configuration at Mach numbers of 1.41 and 1.82 (National Aeronautics and Space Administration, 1959), by Ross B. Robinson and Langley Research Center (page images at HathiTrust)
• Base heat transfer, pressure ratios, and configuration effects obtained on a 1/27 scall saturn (C-1) model at mach numbers from 0.1 to 2.0 (National Aeronautics and Space Administration, 1963), by John L. Allen, Robert A. Wasko, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-2900 (National Aeronautics and Space Administration :, 1965), by James M. Cubbage and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Experimental operating performance of a single-stage annular air ejector (National Aeronautics and Space Administration, 1959), by Robert R. Howell and Langley Research Center (page images at HathiTrust)
• Flight investigation of the lift and drag characteristics of a swept-wing, multijet, transport-type airplane (National Aeronautics and Space Administration, 1960), by Ronald Tambor and Flight Research Center (U.S.) (page images at HathiTrust)
• Experimental investigation of air film cooling applied to an adiabatic wall by means of an axially discharging slot (National Aeronautics and Space Administration, 1959), by S. Stephen Papell, Arthur M. Trout, and Lewis Research Center (page images at HathiTrust)
• Measured and predicted section wave drag coefficients at a Mach number of 1.6 for a delta wing with two airfoil sections (National Aeronautics and Space Administration, 1959), by Frederick C. Grant and Langley Research Center (page images at HathiTrust)
• NASA TN D-1769 (National Aeronautics and Space Administration, 1963), by Charles E. Duller, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Wind-tunnel investigation of sonic-boom characteristics of two simple wing models at Mach numbers from 2.3 to 4.63 (National Aeronautics and Space Administration, 1971), by Davis S. Miller, Odell A. Morris, Harry W. Carlson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Pressure distributions on blunt-delta wings at angles of attack up to 90 degrees and Mach number of 6.85 (National Aeronautics and Space Administration :, 1963), by Peter T. Bernot and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Stability and control characteristics at mach numbers of 2.50, 3.00, and 3.71 of a variable- wing-sweep configuration with outboard wing panels swept back 75 degree (National Aeronautics and Space Administration, 1960), by Gerald V. Foster, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effects of wing planform on the aerodynamic characteristics of a wing-body-tail model at Mach numbers 1.57, 2.16, and 2.87 (National Aeronautics and Space Administration :, 1965), by Royce L. McKinney, Lloyd S. Jernell, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Stability and control characteristics at a mach number of 2.01 of a variable-wing-sweep configuration with outboard wing panels swept back 75° (National Aeronautics and Space Administration, 1959), by M. Leroy Spearman, Gerald V. Foster, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-6392 (National Aeronautics and Space Administration:, 1971), by Norman D. Wong (page images at HathiTrust)
• Wind-tunnel investigation at Mach numbers from 3.0 to 6.8 of the static aerodynamic characteristics of modified Mercury exit and escape capsule configurations (National Aeronautics and Space Administration, 1960), by Albin O. Pearson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effects of wing height on the stability and control characteristics at a mach number of 2.01 of a canard airplane configuration with a 70 degree delta wing (National Aeronautics and Space Administration, 1960), by Cornelius Driver, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Measurements of the Mach number and pressure on the afterbody of a blunt-nosed model in free flight at Mach numbers from 6.5 to 14 (National Aeronautics and Space Administration, 1960), by 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 variable-wing-sweep STOL configuration (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)
• NASA TN D-6397 (National Aeronautics and Space Administration:, 1971), by Robert J. Keynton (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)
• Aerodynamic and acoustic performance of high Mach number inlets (National Aeronautics and Space Administration ;, 1977), by Edward Lumsdaine and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Static longitudinal aerodynamic characteristics of close-coupled wing-canard configurations at Mach numbers from 1.60 to 2.86. (National Aeronautics and Space Administration :, 1971), by Samuel M. Dollyhigh, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1945), by Harold F. Kleckner, United States. National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by John A. Zalovcik, Fred L. Daum, United States. National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1945), by Antonio Ferri, United States. National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by Carl Kaplan, United States. National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by E. O. Pearson, United States. National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1946), by John A. Zalovcik, Fred L. Daum, United States. National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Two-dimensional motion of a gas at large supersonic velocities (National Advisory Committee for Aeronautics, 1949), by S. V. Falkovich and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• K voprosu o povedenii bystrodvizhushchegosya potoka szhimaemogo gaza v pryamoi tsilindricheskoi trube pri nalichii okhlazhdenia (National Advisory Committee for Aeronautics, 1951), by G. A. Varshavsky and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by Jerry Goodman, United States. National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• A comparison of the performance of four side-mounted inlets over a Mach number range of 0.88 to 2.2 and angles of attack to 14 degrees (National Aeronautics and Space Administration, 1960), by Leroy L. Presley, William P. Peterson, and Ames Research Center (page images at HathiTrust)
• Force, moment, and flow-field characteristics of two wing-body-nacelle combinations at Mach numbers 2 and 3 (National Aeronautics and Space Administration, 1960), by Jr. Hill and Ames Research Center (page images at HathiTrust)
• Effect of forebody strakes on the aerodynamic characteristics in pitch and sideslip of a hypersonic airplane configuration at Mach numbers of 1.41, 2.01, and 6.86 (National Aeronautics and Space Administration, 1959), by Cornelius Driver and Langley Research Center (page images at HathiTrust)
• Transonic flutter investigation of models of proposed horizontal tails for the X-15 airplane (National Aeronautics and Space Administration, 1961), by Lou S. Young and Langley Research Center (page images at HathiTrust)
• Transonic flutter investigation of models of the X-15 airplane horizontal tail (National Aeronautics and Space Administration, 1961), by Lou S. Young, Samuel R. Bland, and Langley Research Center (page images at HathiTrust)
• Wind-tunnel investigation at a Mach number of 2.91 of stability and control characteristics of three lifting reentry configurations at angles of attack up to 90 degrees (National Aeronautics and Space Administration, 1961), by John E. Grimaud and Langley Research Center (page images at HathiTrust)
• Measurements of the surface flows, heat transfer, pressure distribution, and longitudinal stability of a mercury capsule model at Mach numbers of 6.9 and 9.6 (National Aeronautics and Space Administration, 1961), by Philip E. Everhart, Peter T. Bernot, and Langley Research Center (page images at HathiTrust)
• Wind-tunnel calibration of a combined pitot-static tube and vane-type flow-angularity indicator at Mach numbers of 1.61 and 2.01 (National Advisory Committee for Aeronautics, 1956), by Archibald R. Sinclair, William D. Mace, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation of axially symmetric and two-dimensional multinozzles for producing supersonic streams (National Advisory Committee for Aeronautics, 1952), by Eli Reshotko, Rudolph C. Haefeli, United States. National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Investigation of three types of supersonic diffuser over a range of Mach numbers from 1.75 to 2.74 (National Advisory Committee for Aeronautics, 1951), by L. Eugene Baughman, Larence I. Gould, United States. National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Tests of a small-scale NACA submerged inlet at transonic Mach numbers (National Advisory Committee for Aeronautics, 1950), by L. Stewart Rolls, George A. Rathert, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Supplementary note on modified-impact-theory calculations for bodies of revolution having minimum drag at hypersonic speeds (National Advisory Committee for Aeronautics, 1952), by Meyer M. Resnikoff, United States. National Advisory Committee for Aeronautics, and Ames Research Center (page images at HathiTrust)
• A comparison at mach numbers up to 0.92 of the calculated and experimental downwash and wake characteristics at various horizonatl tail heights behind a wing with 45 degrees of sweepback (National Advisory Committee for Aeronautics, 1955), by Jack D. Stephenson, Angelo Bandettini, Ralph Selan, United States. National Advisory Committee for Aeronautics, and Ames Research Center (page images at HathiTrust)
• An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability below the Mach Number of Lift Divergence (National Advisory Committee for Aeronautics, 1948), by John A. Axelson, J. Conrad Crown, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation of a three-blade propeller in combination with two different spinners and an NACA D-type cowl at mach numbers up to 0.80 (National Advisory Committee for Aeronautics, 1954), by George C. Kenyon, Robert M. Reynolds, United States. National Advisory Committee for Aeronautics, and Ames Research Center (page images at HathiTrust)
• Development of flow distortions in a full-scale nacelle inlet at mach numbers 0.63 and 1.6 to 2.0 (National Advisory Committee for Aeronautics, 1956), by Thomas G. Piercy, Bruce G. Chiccine, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation of the NACA-4-(3)(08)-03 two-blade propeller at forward Mach numbers to 0.925 (National Advisory Committee for Aeronautics, 1949), by James B. Delano, Francis G. Morgan, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation of the NACA 4-(0)(03)-45 two-blade propeller at forward Mach numbers to 0.925 (National Advisory Committee for Aeronautics, 1950), by Melvin M. Carmel, Joseph R. Milillo, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Flight investigation at Mach numbers from 0.6 to 1.7 to determine drag and base pressures on a blunt-trailing-edge airfoil and drag of diamond and circular-arc airfoils at zero lift (National Advisory Committee for Aeronautics, 1950), by John D. Morrow, Ellis Katz, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• The aerodynamic design and calibration of an asymmetric variable Mach number nozzle with sliding block for the Mach number range 1.27 to 2.75 (National Advisory Committee for Aeronautics, 1951), by Paige B. Burbank, Robert W. Byrne, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Effect of thickness, camber, and thickness distribution on airfoil characteristics at Mach numbers up to 1.0 (National Advisory Committee for Aeronautics, 1952), by Bernard N. Daley, Richard S. Dick, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Some measurements of aerodynamic forces and moments at subsonic speeds on a rectangular wing of aspect ratio 2 oscillating about the midchord (National Advisory Committee for Aeronautics, 1953), by Edward Widmayer, Sumner A. Leadbetter, Sherman A. Clevenson, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Investigation of the aerodynamic characteristics at high supersonic Mach numbers of a family of delta wings having double-wedge sections with the maximum thickness at 0.18 chord (National Advisory Committee for Aeronautics, 1954), by Mitchel H. Bertram, William D. McCauley, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation of the aerodynamic characteristics in pitch and sideslip of a 45©� swept-wing airplane configuration with various vertical locations of the wing and horizontal tail. Static lateral and directional stability; Mach numbers of 1.41 and 2.01 (National Advisory Committee for Aeronautics, 1957), by M. Leroy Spearman, Ross B. Robinson, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Flight calibration of four airspeed systems on a swept-wing airplane at Mach numbers up to 1.04 by the NACA radar-phototheodolite method (National Advisory Committee for Aeronautics, 1950), by Jim Rogers Thompson, George E. Cooper, Richard S. Bray, Ames Research Center, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Some effects of density and Mach number on the flutter speed of two uniform wings (National Advisory Committee for Aeronautics, 1949), by George E. Castile, Robert W. Herr, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Data on shape and location of detached shock waves on cones and spheres (National Advisory Committee for Aeronautics, 1949), by Juergen W. Heberle, Paul B. Gooderum, George P. Wood, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Effects of Mach number up to 0.34 and Reynolds number up to 8,000,000 on the maximum lift coefficient of a wing of NACA 66-series airfoil sections (National Advisory Committee for Aeronautics, 1950), by G. Chester Furlong, James E. Fitzpatrick, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Turbulent boundary-layer temperature recovery factors in two-dimensional supersonic flow (National Advisory Committee for Aeronautics, 1951), by Maurice Tucker, Stephen H. Maslen, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Experimental investigation of base pressure on blunt-trailing-edge wings at supersonic velocities (National Advisory Committee for Aeronautics, 1952), by Dean R. Chapman, Robert H. Kester, William R. Wimbrow, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Aerodynamic characteristics of 0.187-scale model of a target missile at Mach 1.80 to 2.16 (National Aeronautics and Space Administration ;, 1966), by William A. Corlett and Langley Research Center (page images at HathiTrust)
• Longitudinal aerodynamic characteristics at Mach numbers from 0.50 to 1.19 of a supersonic transport model with a modified M wing (National Aeronautics and Space Administration ;, 1967), by Edward J. Ray, Robert T. Taylor, and Langley Research Center (page images at HathiTrust)
• Investigation of the static longitudinal stability characteristics of an air-to-surface canard missile configuration in the transonic mach number range (National Aeronautics and Space Administration, 1960), by Gerald L. Hunt and Langley Research Center (page images at HathiTrust)
• Flight test of a 30-foot nominal diameter disk-gap-band parachute deployed at a Mach number of 1.56 and a dynamic pressure of 11.4 pounds per square foot (National Aeronautics and Space Administration ;, 1967), by Clinton V. Eckstrom, John S. Preisser, and Langley Research Center (page images at HathiTrust)
• Heat transfer to blunt axially symmetric bodies (National Aeronautics and Space Administration, 1960), by John O. Reller and Ames Research Center (page images at HathiTrust)
• Lateral directional stability characteristics at mach 2.3 to 3.5 of a supersonic transport model with various outboard vertical-tail locations (National Aeronautics and Space Administration ;, 1965), by William A. Corlett and Langley Research Center (page images at HathiTrust)
• Static aerodynamic characteristics of a model of a typical subsonic jet-transport airplane at Mach numbers from 0.40 to 1.20 (National Aeronautics and Space Administration ;, 1967), by Eugene N. Brooks, James A. Blackwell, John P. Decker, 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 (National Aeronautics and Space Administration, 1960), by Owen H. Davis, Glenn A. Mitchell, and Lewis Research Center (page images at HathiTrust)
• Effects of wing inboard plan-form modifications on lift, drag, and longitudinal stability at Mach numbers from 1.0 to 2.3 of a rocket-propelled free-flight model with a 52.5 degree sweptback wing of aspect ratio 3 (National Advisory Committee for Aeronautics, 1957), by Allen B. Henning and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Summary of drag coefficients of various shaped cylinders (General Electric, Aircraft Nuclear Propulsion Dept., Atomic Products Division, Technical Publications Sub-Section ;, 1957), by C. F. Heddleson, General Electric Company. Aircraft Nuclear Propulsion Department. Atomic Products Division, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Mach tables for real gas equilibrium flow of air in hypervelocity test facilities with total temperatures to 10,000°K (Sandia Corporation, Technical Information Division ;, 1961), by Kennith L. Goin, U.S. Atomic Energy Commission, and Sandia Corporation (page images at HathiTrust)
• Standard nomenclature for airspeeds with tables and charts for use in calculation of airspeed (National Advisory Committee for Aeronautics ;, 1946), by William J. Aiken and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Free-flight measurements of the rolling effectiveness and drag of trailing-edge spoilers on a tapered sweptback wing at Mach numbers between 0.6 and 1.4 (Washington, D.C. : National Advisory Committee for Aeronautics, 1954., 1954), by Eugene D. Schult, E. M. Fields, Langley Aeronautical Laboratory, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Mach number table (₋gc=1.4) with correction factors for real air (General Dynamics Pomona Division, 1963), by Ernest Carlton Kennedy and H. C. Kerr (page images at HathiTrust; US access only)
• Handbook of inviscid sphere-cone flow fields and pressure distributions (White Oak, Silver Spring, Marlyand : Naval Surface Weapons Center, White Oak Laboratory, 1975., 1975), by A. M. Morrison, Naval Surface Weapons Center. White Oak Laboratory, R. E. Ferguson, M. Ciment, and J. M. Solomon (page images at HathiTrust)
• An Investigation of the damping in pitch characteristics of a ten degree cone (Silver Spring, Maryland : Naval Surface Weapons Center, White Oak Laboratory, 1975., 1975), by A. M. Morrison, W. R. Lawrence, J. E. Holmes, and Naval Surface Weapons Center. White Oak Laboratory (page images at HathiTrust)
• Handbook of blunt-body aerodynamics: volume 1 - static stability. (Silver Spring, Maryland : Naval Ordnance Laboratory, White Oak, 1973., 1973), by John A. Darling and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Flight text investigation of transonic shock-boundary layer phenomena (Wright-Patterson Air Force Base, Ohio : Air Force Systems Command, Air Force Flight Dynamics Laboratory, 1968., 1968), by Jones F. Cahill, Bill L. Copper, Air Force Flight Dynamics Laboratory (U.S.), and Lockheed-Georgia Company (page images at HathiTrust)
• Force balance determination of inlet performance for advanced vehicle applications to orbital velocities using internal drag measurements (Wright-Patterson Air Force Base, Ohio : Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1963., 1963), by Paul H. Kutschenreuter, United States. Air Force. Systems Command. Research and Technology Division, and United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• Experimental and theoretical panel flutter studies in the mach number range of 1.0 to 5.0 : supplement 1 (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1965., 1965), by E. H. Dowell, Air Force Flight Dynamics Laboratory (U.S.), United States. Air Force. Systems Command. Aeronautical Systems Division, and Boeing Company (page images at HathiTrust)
• Evaluation of USSAERO and HABP computer codes for aerodynamic predictions for slender bodies (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1981., 1981), by Jack I. Flaherty, Air Force Wright Aeronautical Laboratories, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Experimental and theoretical panel flutter studies in the mach number range of 1.0 to 5.0 (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1963., 1963), by E. H. Dowell, H. M. Voss, Air Force Flight Dynamics Laboratory (U.S.), and Boeing Company (page images at HathiTrust)
• External store airloads prediction technique. Volume I. Technical summary (Eglin Air Force Base, Florida : Air Force Armament Laboratory, Armament Configuration Division, Air Force Systems Command, United States Air Force, 1975., 1975), by A. R. Rudnicki, R. D. Gallagher, C. T. Alexander, E. G. Waggoner, United States. Air Force. Systems Command, Air Force Armament Laboratory, and LTV Aerospace Corporation (page images at HathiTrust)
• An Investigation of three-dimensional wall interference in a variable porosity transonice wind tunnel (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1974., 1974), by Travis W. Binion, United States. Air Force. Arnold Air Force Base, United States. Air Force. Systems Command. Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
• Documentation of the Phase III 0.192-scale Northrop/McDonnell-Douglas F-18 inlet performance test at mach numbers 0 to 1.55 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1978., 1978), by Jimmy Walker, Sverdrup Corporation, United States. Naval Air Systems Command, and United States. Air Force. Systems Command. Arnold Engineering Development Center (page images at HathiTrust)
• Investigation of suction controlled boundary layer on a Northrop model at Mach numbers of 2, 5, 3, and 3.5 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Research and Development Command, United States Air Force, 1959., 1959), by W. T. Strike, J. C. Donaldson, Inc ARO, and Arnold Engineering Development Center (page images at HathiTrust)
• External store airloads prediction technique. Volume II. Detailed Data. Book 5 : MER carriage axial force and rolling moment predictions and TER carriage predictions (Eglin Air Force Base, Florida : Air Force Armament Laboratory, Armament Configuration Division, Air Force Systems Command, United States Air Force, 1975., 1975), by A. R. Rudnicki, R. D. Gallagher, C. T. Alexander, E. G. Waggoner, United States. Air Force. Systems Command, Air Force Armament Laboratory, and LTV Aerospace Corporation (page images at HathiTrust)
• Aerodynamics of missiles wih offset fin configurations (Eglin Air Force Base, Florida : Air Force Armament Laboratory, Aeromechanics Division, Air Force Systems Command, United States Air Force, 1989., 1989), by Gregg L. Abate, United States. Air Force. Systems Command, and Air Force Armament Laboratory (page images at HathiTrust)
• Skin friction measurements at transonic mach numbers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1979., 1979), by Charles L. Smith, Inc. ARO, and United States. Air Force. Systems Command. Arnold Engineering Development Center (page images at HathiTrust)
• CFD wing/pylon/finned store mutual interference wind tunnel experiment (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1991., 1991), by E. Rolland Heim, Calspan Corporation, and United States. Air Force. Systems Command. Arnold Engineering Development Center (page images at HathiTrust)
• External store airloads prediction technique. Volume II. Detailed Data. Book 2 : single carriage airloads predictions (Eglin Air Force Base, Florida : Air Force Armament Laboratory, Armament Configuration Division, Air Force Systems Command, United States Air Force, 1975., 1975), by A. R. Rudnicki, R. D. Gallagher, C. T. Alexander, E. G. Waggoner, United States. Air Force. Systems Command, Air Force Armament Laboratory, and LTV Aerospace Corporation (page images at HathiTrust)
• External store airloads prediction technique. Volume II. Detailed Data. Book 1 : initial airloads prediction (Eglin Air Force Base, Florida : Air Force Armament Laboratory, Armament Configuration Division, Air Force Systems Command, United States Air Force, 1975., 1975), by A. R. Rudnicki, R. D. Gallagher, C. T. Alexander, E. G. Waggoner, United States. Air Force. Systems Command, Air Force Armament Laboratory, and LTV Aerospace Corporation (page images at HathiTrust)
• A study of flow fields about some typical blunt-nosed slender bodies (Brooklyn, New York : Polytechnic Institute of Brooklyn, Department of Aerospace Engineering and Applied Mechanics, 1960., 1960), by Roberto Vaglio-Laurin, Massimo Trella, United States. Air Force. Office of Scientific Research, and Polytechnic Institute of Brooklyn. Department of Aerospace Engineering and Applied Mechanics (page images at HathiTrust)
• Static force and moment test of the Holloman narrow-gage rocket slet at Mach numbers from 3.5 to 5.5 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1987., 1987), by C. L. Ratliff, Calspan Corporation, and United States. Air Force. Systems Command. Arnold Engineering Development Center (page images at HathiTrust)
• High altitude supersonic target (HAST) : phase III (Eglin Air Force Base, Florida : Air Force Armament Laboratory, Armament Development and Test Center, Air Force Systems Command, United States Air Force, 1977., 1977), by D. E. Wells, W. M. Byrne, United States. Air Force. Systems Command, Air Force Armament Laboratory, and Beech Aircraft Corporation (page images at HathiTrust)
• On the Mach number independence principle for a hypersonic boundary layer ([Princeton, New Jersey] : Princeton University, Department of Aeronautical Engineering, [1959], 1959), by N. C. Freeman, Sau-hai Lam, United States. Air Force. Office of Scientific Research, United States. Air Force. Air Research and Development Command, and Princeton University. Department of Aeronautical Engineering (page images at HathiTrust)
• The Use of boundary-layer suction for maintaining laminar flow downstream of a reflected incidence shock wave on a flat plate at free-stream 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)
• External store airloads prediction technique. Volume II. Detailed Data. Book 4 : MER carriage normal force and pitching moment predictions (Eglin Air Force Base, Florida : Air Force Armament Laboratory, Armament Configuration Division, Air Force Systems Command, United States Air Force, 1975., 1975), by A. R. Rudnicki, R. D. Gallagher, C. T. Alexander, E. G. Waggoner, United States. Air Force. Systems Command, Air Force Armament Laboratory, and LTV Aerospace Corporation (page images at HathiTrust)
• External store airloads prediction technique. Volume III. Detailed Data. Book 3 : MER carriage side force and yawing moment predictions (Eglin Air Force Base, Florida : Air Force Armament Laboratory, Armament Configuration Division, Air Force Systems Command, United States Air Force, 1975., 1975), by A. R. Rudnicki, R. D. Gallagher, C. T. Alexander, E. G. Waggoner, United States. Air Force. Systems Command, Air Force Armament Laboratory, and LTV Aerospace Corporation (page images at HathiTrust)

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