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Reynolds number

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NASA SC(2)-0714 Airfoil Data Corrected for Sidewall Boundary-Layer Effects in the Langley 0.3-Meter Transonic Cryogenic Tunnel (NASA technical paper 2890, 1989), by Renaldo V. Jenkins (page images at HathiTrust)
The effects of resonant vibrations on heat transfer at high reynolds numbers final report (Engineering Experiment Station, Georgia Institute of Technology, 1961), by Thomas Woodrow Jackson, Ian Eastwood, Calvin C. Oliver, Georgia Institute of Technology. Engineering Experiment Station, and University of California. Lawrence Radiation Laboratory (page images at HathiTrust; US access only)
The blunt-body problem in hypersonic flow at low Reynolds number. (Cornell Aeronautical Laboratory, Inc., 1963), by Hsien Kei Cheng (page images at HathiTrust)
M=3 turbulent boundary layer measurements at very high Reynolds numbers (Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1977), by Anthony W. Fiore (page images at HathiTrust)
Effects of large-scale intermittency of turbulence on scalar spectra at high wave numbers (U.S. Dept. of Commerce, National Oceanic and Atmospheric Administration, Environmental Research Laboratories, 1980), by Reginald J. Hill and Wave Propagation Laboratory (page images at HathiTrust)
Effect of Reynolds number variation on aerodynamics of a hydrogen-fueled transport concept at Mach 6 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1987), by Jim A. Penland, Don C. Marcum, and Langley Research Center (page images at HathiTrust)
Effects of yaw angle and Reynolds number on rectangular-box cavities at subsonic and transonic speeds (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ;, 1991), by Elizabeth B. Plentovich, M. B. Tracy, and Julio Chu (page images at HathiTrust)
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)
Flight Reynolds number effects on a contoured boattail nozzle at subsonic speeds (National Aeronautics and Space Administration ;, 1974), by Roger Chamberlin 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)
Measurements of fluctuating pressure in a rectangular cavity in transonic flow at high Reynolds numbers (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by M. B. Tracy, Julio Chu, Elizabeth B. Plentovich, and Langley Research Center (page images at HathiTrust)
Elliptic flow computation by low Reynolds number two-equation turbulence models (National Aeronautics and Space Administration ;, 1991), by V. Michelassi, T.-H. Shih, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Aerothermal tests of a 12.5⁰ cone at Mach 6.7 for various Reynolds numbers, angles of attack, and nose shapes (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Robert J. Nowak, L. Roane Hunt, Cindy W. Albertson, and Langley Research Center (page images at HathiTrust)
Aerodynamic characteristics of three helicopter rotor airfoil sections at Reynolds numbers from model scale to full scale at Mach numbers from 0.35 to 0.90 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Kevin W. Noonan, Gene J. Bingham, Army Research and Technology Laboratories (U.S.). Structures Laboratory, United States. Army Aviation Research and Development Command, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Longitudinal aerodynamic performance of a series of power-law and minimum-wave-drag bodies at Mach 6 and several Reynolds numbers (National Aeronautics and Space Administration ;, 1974), by George C. Ashby and Langley Research Center (page images at HathiTrust)
Aerodynamic characteristics at low Reynolds numbers of several heat-exchanger configurations for wind-tunnel use (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by William G. Johnson, William B. Igoe, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
R4 airfoil data corrected for sidewall boundary-layer effects in the Langley 0.3-meter transonic cryogenic tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1986), by Renaldo V. Jenkins and Langley Research Center (page images at HathiTrust)
Flight Reynolds number effects on a fighter-type, circular-arc - 19 ̊conic boattail nozzle at subsonic speeds (National Aeronautics and Space Administration ;, 1974), by Roger Chamberlin and Lewis Research Center (page images at HathiTrust)
Aerodynamic performance and pressure distributions for a NASA SC(2)-0714 airfoil tested in the Langley 0.3-meter transonic cryogenic tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988), by Renaldo V. Jenkins, Edward J. Ray, Acquilla S. Hill, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division (page images at HathiTrust)
Reynolds number tests of an NPL 9510 airfoil in the Langley 0.3-meter transonic cryogenic tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Renaldo V. Jenkins and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Experimental investigation to validate use of cryogenic temperatures to achieve high Reynolds numbers in boattail pressure testing (U.S. National Aeronautics and Space Administration ;, 1976), by David E. Reubush, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
Effects of Reynolds number and model support on the supersonic aerodynamic chacteristics of a 140° included-angle cone (National Aeronautics and Space Administration ;, 1974), by Charles D. Trescot, Dorothy T. Howell, Clarence A. Brown, and Langley Research Center (page images at HathiTrust)
Representation of turbulent shear stress by a product of mean velocity differences (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1977), by Willis H. Braun and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Water-tunnel study of transition flow around circular cylinders (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by D. Almosnino, Kenneth W. McAlister, 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)
Pressure distributions from high Reynolds number tests of a Boeing BAC I airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by William G. Johnson, Acquilla S. Hill, and Langley Research Center (page images at HathiTrust)
A hybridized method for computing high-reynolds-number hypersonic flow about blunt bodies (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by K. James Weilmuenster, H. Harris Hamilton, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Pressure distributions from high Reynolds number tests of a NASA SC(3)-0712(B) airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by William G. Johnson, Otto Eichmann, Acquilla S. Hill, and Langley Research Center (page images at HathiTrust)
High Reynolds number tests of a NASA SC(3)-0712(B) airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by William G. Johnson, Otto Eichmann, Acquilla S. Hill, and Langley Research Center (page images at HathiTrust)
Wall-layer eruptions in turbulent flows (National Aeronautics and Space Administration ;, 1989), by J. D. A. Walker and United States National Aeronautics and Space Administration (page images at HathiTrust)
Experimental determination of pressure drop and flow characteristics of dilute gas-solid suspensions (National Aeronautics and Space Administration ;, 1971), by Robert Pfeffer, Salvatore J. Rossetti, Lewis Research Center, and City University of New York. City College (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)
High Reynolds number flows (National Aeronautics and Space Administration ;, 1971), by David A. Russell, United States National Aeronautics and Space Administration, and University of Washington (page images at HathiTrust)
High Reynolds number tests of a C141A aircraft semispan model to investigate shock-induced separation (National Aeronautics and Space Administration ;, 1975), by W. T. Blackerby, J. F. Cahill, Ames Research Center, and Lockheed-Georgia Company (page images at HathiTrust)
High Reynolds number test of a NACA 65₁-213, a = 0.5 airfoil at transonic speeds (National Aeronautics and Space Administration ;, 1975), by Kenneth P. Burdges, Gerald A. Pounds, James A. Blackwell, Langley Research Center, and Lockheed-Georgia Company (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)
Correlation of data related to shock-induced trailing-edge separation and extrapolation to flight Reynolds number (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by J. F. Cahill, P. C. Connor, Ames Research Center, and Lockheed-Georgia Company (page images at HathiTrust)
A Review of near-wall Reynolds-stress closures (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1991), by Ronald M. C. So, Langley Research Center, and Arizona State University. College of Engineering and Applied Sciences (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)
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; US access only)
Experimental and analytical sonic nozzle discharge coefficients for Reynolds numbers up to 8x10⁶ (National Aeronautics and Space Administration ;, 1975), by Andrew J. Szaniszlo and Lewis 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)
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)
NASA TN D-4432 (National Aeronautics and Space Administration ;, 1968), by William J. Nusbaum, Milton G. Kofskey, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Performance in air of 4-inch- (10.16-cm- ) mean-diameter single-stage axial-flow turbine for Reynolds numbers from 4900 to 188,000 (National Aeronautics and Space Administration ;, 1968), by Hugh A. Klassen, Robert Y. Wong, and Lewis Research Center (page images at HathiTrust)
Aerodynamic characteristics, temperature, and noise measurements of a large-scale external-flow jet-augmented-flap model with turbojet engines operating (National Aeronautics and Space Administration, 1961), by Marvin P. Fink, 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)
NASA TN D-5761 (National Aeronautics and Space Administration :, 1970), by Laurence J. Heidelberg, Carl Weigel, Calvin L. Ball, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Correlation of full-scale helicopter rotor performance in air with model-scale freon data (National Aeronautics and Space Administration ;, 1976), by William T. Yeager, Wayne R. Mantay, and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-5766 (National Aeronautics and Space Administration :, 1970), by Michael C. Fischer, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-5753 (National Aeronautics and Space Administration ;, 1969), by Charles B. Johnson, Dennis M. Bushnell, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Effect of Reynolds number on the subsonic boattail drag of several wing-body configurations (U.S. National Aeronautics and Space Administration ;, 1976), by David E. Reubush, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
An experimental and analytical investigation of the effect on isolated boattail drag of varying Reynolds number up to 130 x 106 (National Aeronautics and Space Administration ;, 1976), by David E. Reubush, Lawrence E. Putnam, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
NASA TN D-5903 (National Aeronautics and Space Administration :, 1970), by Joseph W. Cleary, Charles E. Duller, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
NASA TN D-4961 (National Aeronautics and Space Administration ;, 1969), by P. Calvin Stainback, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
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)
Analytical investigation of effect of spin entry technique on spin and recovery characteristics for a 60 degree delta-wing airplane (National Aeronautics and Space Administration, 1959), by Stanley H. Scher, George F. Lawrence, Ernie L. Anglin, and Langley Research Center (page images at HathiTrust)
Effect of Reynolds number on the lateral-stability derivatives at low speed of swept-back and delta-wing-fuselage combinations oscillating in yaw (National Aeronautics and Space Administration :, 1960), by Charles P. Llewellyn and Walter D. Wolhart (page images at HathiTrust)
Pressure distributions and aerodynamic characteristics of several spoiler controls on a 40 degree sweptback wing at a Mach number of 1.61 (National Aeronautics and Space Administration, 1960), by Emma Jean Landrum, K. R. Czarnecki, 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)
Investigation by Schlieren technique of methods of fixing fully turbulent flow on models at supersonic speeds (National Aeronautics and Space Administration, 1960), by Mary W. Jackson, K. R. Czarnecki, 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)
Longitudinal aerodynamic characteristics of two blunted cone reentry configurations at Mach numbers from 17.6 to 22.2 including some Reynolds number effects (National Aeronautics and Space Administration ;, 1966), by Dal V. Maddalon and Langley Research Center (page images at HathiTrust)
Experimental results of heat transfer and pressure drop of argon flowing through single tube with internal interrupted fins (National Aeronautics and Space Administration, 1967), by David Namkoong, Michael P. Lynch, and Lewis Research Center (page images at HathiTrust)
Investigation of variation in base pressure over the Reynolds number range in which wake transition occurs for two-dimensional bodies at Mach numbers from 1.95 to 2.92 (National Aeronautics and Space Administration, 1959), by Vernon Van Hise and Langley Research Center (page images at HathiTrust)
NASA TN D-3950 (National Aeronautics and Space Administration :, 1967), by Richard E. Schwirian and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-3932 (National Aeronautics and Space Administration ;, 1967), by Vernard E. Lockwood, Langley Research Center, and United States National Aeronautics and Space Administration (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)
Investigation of double slotted flaps on a swept-wing transport model (National Aeronautics and Space Administration, 1959), by Rodger L. Naeseth, Edwin E. Davenport, and Langley Research Center (page images at HathiTrust)
On series expansions in magnetic Reynolds number (National Aeronautics and Space Administration, 1959), by Vernon J. Rossow and Ames Research Center (page images at HathiTrust)
Effect of Reynolds number and engine nacelles on the stalling characteristics of a model of a twin-engine light airplane (National Aeronautics and Space Administration ;, 1972), by Vernard E. Lockwood and Langley Research Center (page images at HathiTrust)
An experimental investigation of wall boundary-layer transition Reynolds numbers in an expansion tube (National Aeronautics and Space Administration ;, 1974), by K. James Weilmuenster and Langley Research Center (page images at HathiTrust)
Comparison of measured and calculated velocity profiles of a laminar incompressible free jet at low Reynolds numbers (National Aeronautics and Space Administration ;, 1974), by George C. Greene and Langley Research Center (page images at HathiTrust)
NASA TN D-6392 (National Aeronautics and Space Administration:, 1971), by Norman D. Wong (page images at HathiTrust; US access only)
Investigation of some effects of flexibility on the lift and pitching-moment characteristics of a series of low-aspect- ratio wing-body combinations at transonic speeds (National Aeronautics and Space Administration, 1960), by Robert V. Doggett, A. Gerald Rainey, and Langley Research Center (page images at HathiTrust)
Wind-tunnel investigation of effects of variations in Reynolds number and leading-edge treatment on the aerodynamic characteristics of an externally blown jet-flap configuration (National Aeronautics and Space Administration ;, 1973), by Lysle P. Parlett, James L. Megrail, Charles Christian Smith, and Langley Research Center (page images at HathiTrust)
NASA TN D-6378 (National Aeronautics and Space Administration ;, 1971), by Enrique J. Klein, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
The Cryogenic wind-tunnel concept for high Reynolds number testing (National Aeronautics and Space Administration ;, 1974), by Robert A. Kilgore and Langley Research Center (page images at HathiTrust)
Effects of wing leading-edge radius and Reynolds number on longitudinal aerodynamic characteristics of highly swept wing-body configurations at subsonic speeds (National Aeronautics and Space Administration ;, 1976), by William P. Henderson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Location of separation on a circular cylinder in crossflow as a function of Reynolds Number (Naval Ship Research and Development Center, 1971), by David W. Coder and Naval Ship Research and Development Center (page images at HathiTrust)
Static aerodynamic characteristics of a typical single-engine low-wing general aviation design for an angle-of-attack range of - 8 ̊to 90 ̊ (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by William Bihrle, Paul Pantason, Billy Barnhart, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Investigation of effects of reynolds number on large double-entry centrifugal compressor (National Advisory Committee for Aeronautics, 1952), by Karl Kovach, Joseph R. Withee, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
Downwash, sidewash, and wave survey behind a 42⁰ sweptback wing at a Reynolds number of 6.8 x 10⁶ with and without a simulated ground (National Advisory Committee for Aeronautics, 1948), by G. Chester Furlong, Thomas V. Bollech, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Comparison of semispan data obtained in the Langley two-dimensional low-turbulence pressure tunnel and full-span data obtained in the Langley 19-foot pressure tunnel for a wing with a 40⁰ sweepback of the 0.27-chord line (National Advisory Committee for Aeronautics, 1949), by Jones F. Cahill, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Investigation of the variation with Reynolds number of the base, wave, and skin-friction drag of a parabolic body of revolution (NACA RM-10) at Mach numbers of 1.62, 1.93, and 2.41 in the Langley 9-inch supersonic tunnel (National Advisory Committee for Aeronautics, 1952), by Eugene S. Love, August F. Bromm, Donald E. Coletti, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
NACA 65-series compressor rotor performance with varying annulus-area ratio, solidity, blade angle, and Reynolds number and comparison with cascade results (National Advisory Committee for Aeronautics, 1953), by Wallace M. Schulze, George C. Ashby, John R. Erwin, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Investigation of the effects of model scale and stream Reynolds number on the aerodynamic characteristics of two rectangular wings at supersonic speeds on the Langley 9-inch supersonic tunnel (National Advisory Committee for Aeronautics, 1955), by Donald E. Coletti, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Effects of twist and camber on the low-speed longitudinal stability characteristics of a 45©� swept-back wing of aspect ratio 8 at Reynolds numbers from 1.5 x 10⁶ to 4.8 x 10 as determined by pressure distributions, force tests, and calculations (National Advisory Committee for Aeronautics, 1952), by George L. Pratt, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Drag due to lift at Mach numbers up to 2.0 (National Advisory Committee for Aeronautics, 1953), by Edward C. Polhamus, Langley Aeronautical Laboratory, and United States. National Adviosry 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)
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)
Investigation of the lift, center of pressure, and drag of a projectile at Mach number of 8.6 and a Reynolds number of 17 million (National Advisory Committee for Aeronautics, 1954), by Thomas N. Canning, Ames Research Center, and United States. National Adviosry 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)
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)
Compilation of experimental forced-convection, quality burnout data with calculated Reynolds numbers (Washington, D.C. : Department of Commerce, Office of Technical Services, 1960., 1960), by H. Firstenberg, G. Rabinowitz, S. Preiser, L. LoBianco, K. Goldmann, Nuclear Development Corporation of America, and U.S. Atomic Energy Commission (page images at HathiTrust)
Determination of profile drag of airplane wing in flight at high Reynolds numbers. (1940), by Joseph Bicknell and Langley Aeronautical Laboratory (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)
Incompressible friction factor, transition and hydrodynamic entrance length studies of ducts with triangular and rectangular cross-sections (Wright Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1957., 1957), by E. R. G. Eckert, T. F. Irvine, United States. Air Force. Air Research and Development Command, and Wright Air Development Center (page images at HathiTrust)
Afterglow investigations of shock detachment distances at low Reynolds numbers (Wright-Patterson Air Force Base, Ohio : Wright Air Development Division, Air Research and Development Command, United States Air Force, 1958., 1958), by E. S. Moulic, United States. Air Force. Air Research and Development Command, Armour Research Foundation (U.S.), and Wright Air Development Center (page images at HathiTrust)
Pressure and heat transfer measurements for hypersonic flows over expansion corners and ahead of ramps (Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, 1963), by Louis G. Kaufman, Air Force Flight Dynamics Laboratory (U.S.), United States. Air Force. Systems Command. Aeronautical Systems Division, and Grumman Aircraft Engineering Corporation. Research Department (page images at HathiTrust)
Skin friction measurements at a Mach number of three and momentum thickness Reynolds numbers up to a half million (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1980., 1980), by Anthony W. Fiore and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
Boundary-layer transition under hypersonic conditions (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1965., 1965), by J. Leith Potter, Jack D. Whitfield, United States. Air Force. Arnold Air Force Base, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
Final report : studies in hypersonic flow theory (Stanford, California : Stanford University, Department of Aeronautics and Astronautics, 1963., 1963), by Milton Van Dyke, Stanford University. Department of Aeronautics and Astronautics, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Fundamental studies of subsonic and transonic flow separation. Part II. Second phase summary report (Tullahoma, Tennessee : University of Tennessee Space Institute, 1977., 1977), by Zhengming Wu, Arnold Engineering Development Center, and University of Tennessee (System). Space Institute (page images at HathiTrust)
Model study of the exhaust flow noise of the proposed AEDC high Reynolds number tunnel (Arnold Air Force Base, Tennessee : Von Karman Gas Dynamics Facility, Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1971., 1971), by J. E. Robertson, Wyle Laboratories, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Numerical study of unsteady low-reynolds number wing performance (Arlington, Virginia. : Air Force Office of Scientific Research, 2008., 2008), by Ashok Gopalarathnam, Gregory Z. McGowan, North Carolina State University. Department of Mechanical and Aerospace Engineering, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Turbulence structure associated with intercomponent and interscale energy transfer, and modification by forcing (University Park, Pennsylvania : Pennsylvania State University, Department of Mechanical Engineering, 1994., 1993), by James G. Brasseur, Pennsylvania State University. Department of Mechanical Engineering, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Unsteady stall penetration experiments at high Reynolds number (Bolling Air Force Base, D. C. : Air Force Office of Scientific Research, United States Air Force, 1987., 1987), by Peter F. Lorber, F. O. Carta, United Technologies Research Center, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Dynamic stability characteristics of a 10-deg cone at Mach number 20 (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 R. H. Urban, R. J. Shanahan, Inc ARO, Aerospace Research Laboratories (U.S.), and Arnold Engineering Development Center (page images at HathiTrust)
Low Reynolds number aerodynamics of flapped airfoils at supersonic speeds (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1958., 1958), by James L. Amick, Gerard F. Carvalho, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and University of Michigan (page images at HathiTrust)
Structure and dynamics of turbulent wall layers (Urbana, Illinois : University of Illinois at Urbana-Champaign, Department of Theoretical and Applied Mechanics, 1994., 1994), by R. J. Adrian, University of Illinois at Urbana-Champaign. Department of Theoretical and Applied Mechanics, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
The effect of pressure pulsations and vibrations on fully developed pipe flow (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1981., 1981), by Donald O. Barnett, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Analytical, numerical, and experimental results on turbulent boundary layers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1976., 1976), by David L. Whitfield, Arnold Engineering Development Center, United States. Air Force. Systems Command, and Inc ARO (page images at HathiTrust)
Numerical simulation of turbulent combustion using vortex methods (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 1990., 1990), by Ahmed F. Ghoniem, Massachusetts Institute of Technology. Department of Mechanical Engineering, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
The Structure of high Reynolds Number turbulent boundary layers (Princeton, New Jersey : Princeton University, Department of Mechanical and Aerospace Engineering, 1993., 1993), by Alexander J. Smits, Princeton University. Department of Mechanical and Aerospace Engineering, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
An Investigation of the effects of nose geometry on the aerodynamic characteristics of a full scale vertical launch ASROC forebody at M₀₀ = 0.30 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1987., 1987), by R. M. Vaeth, Calspan Corporation, Naval Ocean Systems Center (U.S.), and Arnold Engineering Development Center (page images at HathiTrust)
Real-gas effects on the aerodynamics of blunt cones as measured in a hypervelocity range (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1979., 1979), by C. J. Welsh, Inc ARO, United States. Air Force. Arnold Air Force Base, and Arnold Engineering Development Center (page images at HathiTrust)
Low Reynold number turbine blade cascade calculations (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1996., 1996), by Richard Byram Rivir, Elizabeth Ervin, Michael Dahlstom, Rolf Sondergaard, Air Force Flight Dynamics Laboratory (U.S.), and Air Force Wright Aeronautical Laboratories (page images at HathiTrust)
An investigation of the effects of shock impingement on a blunt leading edge (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 A. D. Ray, R. L. Palko, Inc ARO, United States. Air Force. Arnold Air Force Base, and Arnold Engineering Development Center (page images at HathiTrust)
Static force and moment tests of the Holloman narrow-gage rocket sled at Mach Numbers from 1.5 to 4.0 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Von Kármán Gas Dynamics Facility, Air Force Systems Command, United States Air Force, 1975., 1975), by R. H. Rhudy, J. D. Corce, Inc ARO, United States. Air Force. Arnold Air Force Base, and Arnold Engineering Development Center (page images at HathiTrust)
Evaluation of Reynolds number and tunnel wall porosity effects on nozzle afterbody drag at transonic mach numbers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1976., 1976), by C. E. Robinson, Arnold Engineering Development Center, United States. Air Force. Systems Command, and Inc ARO (page images at HathiTrust)
The Structure of high Reynolds Number turbulent boundary layers : Part A (University Park, Pennsylvania : Pennsylvania State University, Department of Mechanical Engineering, 1994., 1994), by James G. Brasseur, Pennsylvania State University. Department of Mechanical Engineering, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by Warren A. Tucker, Arthur R. Wallace, 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 H. Quinn, Warren A. Tucker, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
F/A-18 forebody vortex control (National Aeronautics and Space Administration, Ames Research Center, 1994), by Brian R. Kramer and Ames Research Center (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1946), by Laurence K. Loftin, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
Transonic Navier-Stokes calculations about a 65⁰ delta wing (National Aeronautics and Space Administration, Langley Research Center ;, 1994), by W. Kelly Londenberg and Langley Research Center (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by Frank T. Abbott, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
Vortex asymmetry development on a tangent ogive (Silver Spring, Maryland : Naval Surface Weapons Center, White Oak Laboratory, Research and Technology Department 1982., 1982), by William J. Yanta, Daniel Sternklar, Andrew B. Wardlaw, and Naval Surface Weapons Center. White Oak Laboratory (page images at HathiTrust)

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