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Turbulent boundary layer

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Filed under: Turbulent boundary layer

Big eddies and mixing processes in the Great Lakes (U.S. Environmental Protection Agency, Office of Research and Development :, 1973), by G. T. Csanady and United States. Environmental Protection Agency. Office of Research and Development (page images at HathiTrust)
On the motions of particles in turbulent flows (The Commission :, 1980), by S. L. Lee, F. Durst, Universität Karlsruhe, State University of New York at Stony Brook. Department of Mechanical Engineering, and U.S. Nuclear Regulatory Commission. Division of Reactor Safety Research (page images at HathiTrust)
Pressure gradient effects on supersonic boundary layer turbulence : final report (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1979., 1979), by A. J. Laderman, Air Force Flight Dynamics Laboratory (U.S.), and Ford Aerospace & Communications Corporation. Fluid Mechanics Section (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)
Flow visualization by elastic light scattering in the boundary layer of a supersonic flow (National Aeronautics and Space Administration, Langley Research Center, 2000), by G. C. Herring, Mervin E. Hillard, and Langley Research Center (page images at HathiTrust)
Investigation of small surface protuberances upstream of turbulent boundary layer separation produced by a skewed shock wave at Mach 3 (Air Force Aero Propulsion Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Syspems Command, 1976), by Robert H Korkegi and Air Force Aero Propulsion Laboratory (U.S.) Ramjet Technology Branch (page images at HathiTrust)
Calculation of the turbulent boundary layer and of transition on a plane plate (National Aeronautics and Space Administration; for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va., 1967), by René Hirsch (page images at HathiTrust; US access only)
Fluctuating pressures measured beneath a high-temperature, turbulent boundary layer on a flat plate at a Mach number of 5 (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1989), by Tony L. Parrott, Cindy W. Albertson, Michael G. Jones, 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)
Data on effects of incident-reflecting shocks on the turbulent boundary layer (National Aeronautics and Space Administration ;, 1966), by S. Z. Pinckney and United States National Aeronautics and Space Administration (page images at HathiTrust)
Exploratory investigation of the effect of porous surfaces on hypersonic turbulent boundary layers (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by Ralph D. Watson, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Drag of two-dimensional small-amplitude symmetric and asymmetric wavy walls in turbulent boundary layers (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by John C. Lin, R. Balasubramanian, Michael J. Walsh, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Flight-measured pressure characteristics of aft-facing steps in high Reyonlds number flow at Mach numbers of 2.20, 2.50, and 2.80 and comparison with other data (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Sheryll Goecke Powers and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Turbulent boundary layers over nonstationary plane boundaries (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Alan T. Roper, Garl L. Gentry, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Pressure and heat-transfer distributions in a simulated wing-elevon cove with variable leakage at a free-stream Mach number of 6.9 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by William D. Deveikis, Whitney Bartlett, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Three-dimensional turbulent-mixing-length modeling for discrete-hole coolant injection into a crossflow (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Chi R. Wang, S. Stephen Papell, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Comparison of several methods for predicting separation in a compressible turbulent boundary layer (National Aeronautics and Space Administration ;, 1974), by Philip M. Gerhart, Lawrence J. Bober, and Lewis Research Center (page images at HathiTrust)
Calculation of the pressure distribution on axisymmetric boattails including effects of viscous interactions and exhaust jets in subsonic flow (National Aeronautics and Space Administration ;, 1974), by Josef Rom, Lawrence J. Bober, and Lewis Research Center (page images at HathiTrust)
Methods for estimating pressure and thermal loads induced by elevon deflections on hypersonic-vehicle surfaces with turbulent boundary layers (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Louis G. Kàufman, Charles B. Johnson, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Experimental evaluation of compliant surfaces at low speeds (National Aeronautics and Space Administration ;, 1974), by Kenneth W. McAlister, Tom M. Wynn, U.S. Army Air Mobility Research and Development Laboratory, and Ames 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)
Flight transition data for angles of attack at Mach 22 with correlations of the data (National Aeronautics and Space Administration ;, 1975), by Charles B. Johnson, Christine M. Darden, and Langley Research Center (page images at HathiTrust)
Characteristics of Mach 10 transitional and turbulent boundary layers (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Ralph D. Watson, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Turbulent-flow separation criteria for overexpanded supersonic nozzles (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by E. Leon Morrisette, Theodore J. Goldberg, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Numerical investigation of separated transonic turbulent flows with a multiple-time-scale turbulence model (National Aeronautics and Space Administration ;, 1990), by S. W. Kim, Lewis Research Center. Institute for Computational Mechanics in Propulsion, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Mean-flow and turbulence measurements in the vicinity of the trailing edge of an NACA 63₁-012 airfoil (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by James C. Yu, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
Aerothermal environment in chordwise gaps between split elevons at Mach 6.8 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by L. Roane Hunt, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
In-flight boundary-layer measurements on a hollow cylinder at a Mach number of 3.0 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Robert D. Quinn, Leslie Gong, Hugh L. Dryden Flight Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
A finite-difference method for predicting supersonic turbulent boundary-layer flows with tangential slot injection (National Aeronautics and Space Administration, 1972), by E. W. Miner, C. H. Lewis, Langley Research Center, and Virginia Polytechnic Institute and State University (page images at HathiTrust)
An experimental investigation of vortex generation in a turbulent boundary layer undergoing adverse pressure gradient (National Aeronautics and Space Administration ;, 1972), by Victor Zakkay, Wladimiro Calarese, Langley Research Center, and New York University (page images at HathiTrust)
An experimental study of slot injection into a supersonic stream (National Aeronautics and Space Administration ;, 1973), by Michael Kenworthy, Joseph A. Schetz, Langley Research Center, and Virginia Polytechnic Institute and State University (page images at HathiTrust)
Flight test results of a trailing edge flap designed for direct-lift control (National Aeronautics and Space Administration ;, 1969), by Charles R. Taylor, Boeing Company, and Ames Research Center (page images at HathiTrust)
An investigation of the high speed turbulent boundary layer with heat transfer and arbitrary pressure gradient (National Aeronautics and Space Administration ;, 1970), by Constantino Economos, J. L. Boccio, Langley Research Center, and Nassau County General Applied Science Laboratories (Westbury (page images at HathiTrust)
An experimental investigation of turbulent boundary layers along curved surfaces (National Aeronautics and Space Administration, 1972), by Ronald M. C. So, George L. Mellor, Lewis Research Center, and Princeton University (page images at HathiTrust)
NASA CR-1845 (National Aeronautics and Space Administration ;, 1971), by J. G. Hicks, J. F. Nash, Lockheed-Georgia Company, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
Calculation of compressible, nonadiabatic boundary layers in laminar, transitional and turbulent flow by the method of integral relations (National Aeronautics and Space Administration, 1971), by Gary D. Kuhn, United States. National Aeronautical and Space Administration, Nielsen Engineering & Research, and Langley Research Center (page images at HathiTrust)
Laminar or turbulent boundary-layer flows of perfect gases or reacting gas mixtures in chemical equilibrium (National Aeronautics and Space Administration ;, 1971), by E. Clay Anderson, Clark H. Lewis, Langley Research Center, and Virginia Polytechnic Institute and State University (page images at HathiTrust)
Calculation of turbulent boundary layers with heat transfer and pressure gradient utilizing a compressibility transformation. Part 1, Summary report (National Aeronautics and Space Administration ;, 1971), by C. Economos, J. Boccio, Langley Research Center, and Nassau County General Applied Science Laboratories (Westbury (page images at HathiTrust)
Calculation of turbulent boundary layers with heat transfer and pressure gradient utilizing a compressibility transformation. Part II, Constant property turbulent boundary layer flow with simultaneous mass transfer and pressure gradient (National Aeronautics and Space Administration ;, 1972), by J. Boccio, C. Economos, Langley Research Center, and Nassau County General Applied Science Laboratories (Westbury (page images at HathiTrust)
Calculation of turbulent boundary layers with heat transfer and pressure gradient utilizing a compressibility transformation. Part III, Computer program manual (National Aeronautics and Space Administration ;, 1972), by J. Schneider, J. Boccio, Langley Research Center, and Nassau County General Applied Science Laboratories (Westbury (page images at HathiTrust)
Narrow band cross-correlation analysis of fluctuating pressures beneath a turbulent boundary layer (National Aeronautics and Space Administration, 1968), by C. M. Ailman and A. S. Hopkins (page images at HathiTrust; US access only)
Spiral longitudinal vortices ... (National Aeronautics and Space Administration, 1964), by J. G. Spangler, C. S. Wells, Ling-Temco-Vought, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Spectra and space-time correlations of the fluctuating pressures at a wall beneath a supersonic turbulent boundary layer perturbed by steps and shock waves (National Aeronautics and Space Administration, 1966), by W. V. Speaker (page images at HathiTrust; US access only)
A method of calculating compressible turbulent boundary layers (National Aeronautics and Space Administration, 1968), by H. James Herring and George L. Mellor (page images at HathiTrust; US access only)
Supersonic turbulent boundary-layer flows with mass injection through slots and/or porous walls (National Aeronautics and Space Administration ;, 1975), by Alvin L. Murray, Langley Research Center, and Virginia Polytechnic Institute and State University (page images at HathiTrust)
Skin friction reduction by slot injection at mach 0.8 (U.S. National Aeronautics and Space Administration ;, 1976), by Victor Zakkay, Chi R. Wang, United States National Aeronautics and Space Administration, Langley Research Center, and New York University (page images at HathiTrust)
Control of shock wave - boundary layer interactions by bleed in supersonic mixed compression inlets (National Aeronautics and Space Administration ;, 1975), by Michael K. Fukuda, Eli Reshotko, Warren R. Hingst, Lewis Research Center, and Case Western Reserve University (page images at HathiTrust)
Skin friction reduction in supersonic flow by injection through slots, porous sections and combinations of the two (National Aeronautics and Space Administration ;, 1975), by Joseph A. Schetz, Johannes VanOvereem, Langley Research Center, and Virginia Polytechnic Institute and State University (page images at HathiTrust)
Prediction of compliant wall drag reduction, part I (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1977), by Steven A. Orszag, inc Cambridge Hydrodynamics, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
A study of surface pressure fluctuations in hypersonic turbulent boundary layers (National Aeronautics and Space Administration ;, 1974), by K. R. Raman, Ames Research Center, and Nielsen Engineering & Research (page images at HathiTrust)
On the theory of compliant wall drag reduction in turbulent boundary layers (National Aeronautics and Space Administration, 1974), by Robert L. Ash, Langley Research Center, and Old Dominion University (page images at HathiTrust)
Use of multiple discrete wall jets for delaying boundary layer separation (National Aeronautics and Space Administration ;, 1974), by J. D. McLean, H. J. Herring, Lewis Research Center, and Princeton University (page images at HathiTrust)
Further studies of unsteady boundary layers with flow reversal (U.S. National Aeronautics and Space Administration;, 1976), by John F. Nash, Ames Research Center, and inc Sybucon (page images at HathiTrust)
Atmospheric flow over two-dimensional bluff surface obstructions (National Aeronautics and Space Administration, 1976), by Juergen Bitte, Walter Frost, George C. Marshall Space Flight Center, and University of Tennessee (Knoxville campus). Space Institute (page images at HathiTrust)
Finite element analysis of low speed viscous and inviscid aerodynamic flows (National Aeronautics and Space Administration ;, 1977), by A. J. Baker and United States National Aeronautics and Space Administration (page images at HathiTrust)
An experimental investigation of shock wave-turbulent boundary layer interactions with and without boundary layer suction : a data summary report (National Aeronautics and Space Administration ;, 1977), by Chen-Chih Sun, Morris E. Childs, and University of Washington (page images at HathiTrust)
Parametric study of relaminarization of turbulent boundary layers on nozzle walls (National Aeronautics and Space Administration ;, 1974), by J. P. Kreskovsky, H. McDonald, S. J. Shamroth, Langley Research Center, and United Aircraft Corporation. Research Laboratories (page images at HathiTrust)
A low speed two-dimensional study of flow separation on the GA(W)-1 airfoil with 30-percent chord Fowler flap (National Aeronautics and Space Administration, 1977), by H. C. Seetharam, W. H. Wentz, Wichita State University, and Langley Research Center (page images at HathiTrust)
Experimental and theoretical investigation of three-dimensional turbulent boundary layers and turbulence characteristics inside an axial flow inducer passage (National Aeronautics and Space Administration ;, 1977), by A. K. Anand, B. Lakshminarayana, Pennsylvania State University, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Thin radiating shock layer about a blunt body (National Aeronautics and Space Administration ;, 1970), by Y. S. Chou, L. H. Blake, Ames Research Center, and Lockheed Aircraft Corporation (page images at HathiTrust)
Investigation of blown boundary layers with an improved wall jet system (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by K. R. Saripalli, R. L. Simpson, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Measurements of laminar and turbulent flow in a curved duct with thin inlet boundary layers (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by A. M. K. P. Taylor, M. Yianneskis, James H. Whitelaw, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Transitional boundary-layer solutions using a mixing-length and a two-equation turbulence model (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by E. Clay Anderson, David C. Wilcox, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Operational manual for two-dimensional transonic code TSFOIL (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Stephen S. Stahara, Ames Research Center, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Nielsen Engineering & Research (page images at HathiTrust)
A visual investigation of turbulence in stagnation flow about a circular cylinder (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Willy Z. Sadeh, Herbert J. Brauer, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Colorado State University (page images at HathiTrust)
Simulation of turbulent wall pressure (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Robert L. Ash, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
Finite-difference solution of the compressible stability eigenvalue problem (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Mujeeb R. Malik, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, Systems and Applied Sciences Corporation, and Langley Research Center (page images at HathiTrust)
Turbulent boundary layer heat transfer experiments : convex curvature effects including introduction and recovery (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by T. W. Simon, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
Interference drag in a simulated wing-fuselage juncture (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by L. Kubendran, J. Hubbartt, H. McMahon, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
A Three-dimensional turbulent compressible subsonic duct flow analysis for use with constructed coordinate systems (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by R. Levy, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Mean velocities and Reynolds stresses in a juncture flow (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by H. McMahon, J. Hubbartt, L. Kubendran, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Georgia Institute of Technology, and Langley Research Center (page images at HathiTrust)
Analysis of an existing experiment on the interaction of acoustic waves with a laminar boundary layer (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by M. R. Schopper, Langley Research Center, Systems and Applied Sciences Corporation, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Turbulent boundary layer over solid and porous surfaces with small roughness (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Fred Y. Kong, Fayette Collier, Joseph A. Schetz, Virginia Polytechnic Institute and State University. Aerospace and Ocean Engineering Dept, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
An analytical study of the measured wall pressure field under supersonic turbulent boundary layers (National Aeronautics and Space Administration, 1968), by Thomas J. Black (page images at HathiTrust; US access only)
Interaction between a normal shock wave and a turbulent boundary layer at high, transonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Thomas Charles Adamson, Arthur F. Messiter, M. S. Liou, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Flow separation in shock wave boundary layer interactions at hypersonic speeds (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by A. Hamed, Langley Research Center, and Joint Institute for Advancement of Flight Sciences (page images at HathiTrust)
A transonic interactive boundary-layer theory for laminar and turbulent flow over swept wings (National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988), by Shawn H. Woodson, Fred R. DeJarnette, and Langley Research Center (page images at HathiTrust)
NASA TR R-117 (National Aeronautics and Space Administration :, 1961), by Donald M. Kuehn and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
NASA TR R-368 (National Aeronautics and Space Administration ; [For sale by the Office of Technical Services, Department of Commerce, Washington, D.C. 20230], 1971), by Julius E. Harris, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Analytical and experimental investigation of circulation control by means of a turbulent Coanda jet (National Aeronautics and Space Administration ;, 1972), by E. S. Levinsky, T. T. Yeh, Ames Research Center, and Air Vehicle Corporation (page images at HathiTrust)
NASA TN D-2420 (National Aeronautics and Space Administration :, 1964), by Edwin J. Saltzman, United States National Aeronautics and Space Administration, and Flight Research Center (U.S.) (page images at HathiTrust; US access only)
Transition fixing for hypersonic flow (National Aeronautics and Space Administration ;, 1967), by James R. Sterrett and Langley Research Center (page images at HathiTrust)
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)
NASA TN D-4401 (National Aeronautics and Space Administration ;, 1968), by K. R. Czarnecki, Russell B. Sorrells, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Turbulent heat-transfer prediction method for application to scramjet engines (National Aeronautics and Space Administration ;, 1974), by S. Z. Pinckney and Langley Research Center (page images at HathiTrust)
Theoretical face pressure and drag characteristics of forward-facing steps in supersonic turbulent boundary layers (National Aeronautics and Space Administration, 1975), by D. K. Patel and K. R. Czarnecki (page images at HathiTrust)
NASA TN D-6462 (National Aeronautics and Space Administration :, 1971), by Michael C. Fischer, Dal V. Maddalon, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Experimental investigation of the influence of the turbulent boundary layer on the pressure distribution over a rigid two-dimensional wavy wall (National Aeronautics and Space Administration ;, 1971), by Lado Muhlstein, Richard G. Beranek, George C. Marshall Space Flight Center, and Ames Research Center (page images at HathiTrust)
NASA TN D-6192 (National Aeronautics and Space Administration ;, 1971), by Ivan E. Beckwith, Frank L. Clark, William D. Harvey, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Velocity, intermittency, and turbulence intensity measurements in the boundary layer of an accelerated flow (National Aeronautics and Space Administration, 1970), by Donald R. Boldman, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-5798 (National Aeronautics and Space Administration :, 1970), by Peter A. Gaspers, Daniel N. Petroff, Lado Muhlstein, Ames 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)
Theoretical study of reactive and nonreactive turbulent coaxial jets (U.S. National Aeronautics and Space Administration ;, 1976), by Roop N. Gupta, N. T. Wakelyn, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-5863 (National Aeronautics and Space Administration :, 1970), by Aubrey M. Cary, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Performance and boundary-layer evaluation of a sonic inlet (National Aeronautics and Space Administration ;, 1976), by James F. Schmidt, Robert S. Ruggeri, and Lewis Research Center (page images at HathiTrust)
NASA TN D-5433 (National Aeronautics and Space Administration ;, 1969), by Dennis M. Bushnell, William V. Feller, William D. Harvey, Charles B. Johnson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-5440 (National Aeronautics and Space Administration ;, 1969), by Wei J. Chyu, Richard D. Hanly, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Downstream influence of swept slot injection in hypersonic turbulent flow (National Aeronautics and Space Administration ;, 1977), by Jerry N. Hefner, Dennis M. Bushnell, Aubrey M. Carey, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-5496 (National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by William D. Harvey, Ivan E. Beckwith, Dennis M. Bushnell, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Summary of available information on Reynolds analogy for zero-pressure-gradient, compressible, turbulent-boundary-layer flow (National Aeronautics and Space Administration ;, 1970), by Aubrey M. Cary, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
FORTRAN program for calculating compressible laminar and turbulent boundary layers in arbitrary pressure gradients (National Aeronautics and Space Administration ;, 1970), by William D. McNally (page images at HathiTrust)
Investigation of laminar and turbulent boundary layers interacting with externally generated shock waves (National Aeronautics and Space Administration, 1969), by Earl C. Watson, William C. Rose, and John D. Murphy (page images at HathiTrust; US access only)
Analysis of a turbulent boundary layer over a moving ground plane (National Aeronautics and Space Administration ;, 1972), by Alan T. Roper, Garl L. Gentry, and Langley Research Center (page images at HathiTrust)
Heat-transfer measurements at a Mach number of 2 in the turbulent boundary layer on a flat plate having a stepwise temperature distribution (National Aeronautics and Space Administration, 1959), by Raul J. Conti and Langley Research Center (page images at HathiTrust)
Preliminary surveys of the wall boundary layer in a Mach 6 axisymmetric tunnel (National Aeronautics and Space Administration ;, 1970), by Robert A. Jones, William V. Feller, 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 separation studies for two-dimensional wedges and curved surfaces at Mach numbers of 4.8 to 6.2 (National Aeronautics and Space Administration, 1962), by James R. Sterrett, James C. Emery, and Langley Research Center (page images at HathiTrust)
Free flight observation of a separated turbulent flow including heat transfer up to Mach 8.5 (National Aeronautics and Space Administration, 1960), by Dudley George McConnell and Lewis Research Center (page images at HathiTrust)
Effects of Mach number on pitot-probe displacment in a turbulent boundary layer (National Aeronautics and Space Administration ;, 1974), by Jerry M. Allen and Langley Research Center (page images at HathiTrust)
NASA TN D-1795 (National Aeronautics and Space Administration, 1963), by John B. Peterson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Pressure fluctuations in turbulent boundary layers (National Aeronautics and Space Administration, 1965), by M. V. Lowson, George C. Marshall Space Flight Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
NASA TN D-6759 (National Aeronautics and Space Administration ;, 1972), by Jerry M. Allen, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Interference heating from interactions of shock waves with turbulent boundary layers at Mach 6 (National Aeronautics and Space Administration ;, 1974), by Charles B. Johnson, Louis G. Kaufman, and Langley Research Center (page images at HathiTrust)
Similar solutions for turbulent boundary layer with large favorble pressures gradients (nozzle flow with heat transfer) (National Aeronautics and Space Administration, 1971), by James F. Schmidt, Carroll Todd, Donald R. Boldman, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
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)
NASA TN D-3858 (National Aeronautics and Space Administration :, 1967), by Richard D. Samuels, Jerry B. Adcock, John B. Peterson, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
The compressible turbulent boundary layer on a blunt swept slab with and without leading-edge blowing (National Aeronautics and Space Administration ;, 1971), by James L. Hunt, Ivan E. Beckwith, Dennis M. Bushnell, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Accuracy of pitot-pressure rakes for turbulent boundary-layer measurements in supersonic flow (National Aeronautics and Space Administration ;, 1971), by Earl R. Keener, Edward J. Hopkins, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
Engineering prediction of turbulent skin friction and heat transfer in high-speed flow (National Aeronautics and Space Administration ;, 1974), by Aubrey M. Cary, Mitchel H. Bertram, 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)
NASA TN D-6594 (National Aeronautics and Space Administration :, 1972), by Donald R. Boldman, Robert W. Graham, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-6595 (National Aeronautics and Space Administration :, 1972), by Donald R. Boldman, Robert C. Ehlers, James F. Schmidt, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Evaluation of mean and turbulent velocity measurements in subsonic accelerated boundary layers (National Aeronautics and Space Administration ;, 1976), by V. A. Sandborn, H. L. Seegmiller, and Ames Research Center (page images at HathiTrust)
Some characteristics of turbulent boundary layers in rapidly accelerated flows (National Aeronautics and Space Administration ;, 1971), by Paul F. Brinich, Harvey E. Neumann, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1946), by Neal Tetervin, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
Grenzschichten in flüssigkeiten mit kleiner reibung (National Advisory Committee for Aeronautics, 1950), by H. Blasius and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Heat transmission in the boundary layer (NACA, 1949), by L. E. |q Kalikhman and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
On the recording of turbulent longitudinal and transverse fluctuations (NACA, 1951), by Helmut Reichardt and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
On the theory of the turbulent boundary layer (National Advisory Committee for Aeronautics, 1953), by Julius C. Rotta and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Calculation of turbulent expansion processes (NACA, 1945), by Walter Tollmien and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Mixing-length formulations for turbulent boundary layers over arbitrarily rough surfaces (David W. Taylor Naval Ship Research and Development Center, 1984), by Paul S. Granville and David W. Taylor Naval Ship Research and Development Center (page images at HathiTrust)
Eddy viscosities and mixing lengths for turbulent boundary layers on flat plates, smooth or rough (David W. Taylor Naval Ship Research and Development Center, 1986), by Paul S. Granville and David W. Taylor Naval Ship Research and Development Center (page images at HathiTrust)
Calculation of compressible turbulent boundary layers with pressure gradients and heat transfer (National Aeronautics and Space Administration ;, 1969), by Larry L. Lynes, Gary D. Kuhn, Jack Norman Nielsen, Nielsen Engineering & Research, and Ames Research Center (page images at HathiTrust)
Experimental convective heat transfer to a 4-inch and 6-inch hemisphere at Mach numbers from 1.62 to 3.04 (National Advisory Committee for Aeronautics, 1954), by Leo T. Chauvin, Joseph P. Maloney, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Normal force, center of pressure, and zero-lift drag of several ballistic-type missiles at Mach numbers of 4.05 (National Advisory Committee for Aeronautics, 1954), by Edward F. Ulmann, Robert W. Dunning, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Measurements of aerodynamic heat transfer in turbulent separated regions at a Mach number of 1.8 (National Advisory Committee for Aeronautics, 1958), by Benjamine J. Garland, J. R. Hall, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Measurements in the boundary layer of a yawed wing (National Advisory Committee for Aeronautics, 1949), by A. M. Kuethe, W. H. Curry, P. B. McKee, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Approximate turbulent boundary-layer development in plane compressible flow along thermally insulated surfaces with application to supersonic-tunnel contour correction (National Advisory Committee for Aeronautics, 1950), by Maurice Tucker and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Investigation of separation of the turbulent boundary layer (National Advisory Committee for Aeronautics, 1950), by G. B. Schubauer, P. S. Klebanoff, 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)
Characteristics of turbulence in a boundary layer with zero pressure gradient (National Advisory Committee for Aeronautics, 1954), by P. S. Klebanoff and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Study of the pressure rise across shock waves required to separate laminar and turbulent boundary layers (National Advisory Committee for Aeronautics, 1952), by Coleman duP. Donaldson, Roy H. Lange, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
The effects of artificial stimulation of the turbulent boundary layer in rectangular conduits. (Waterways Experiment Station, 1956), by Waterways Experiment Station (U.S.) (page images at HathiTrust)
On the equations of a thick axisymmetric turbulent boundary layer (Institute of Hydraulic Research, University of Iowa, 1974), by V. C. Patel, Iowa Institute of Hydraulic Research, and Naval Ship Research and Development Center (page images at HathiTrust; US access only)
A unified view of the law of the wall using mixing-length theory (Institute of Hydraulic Research, University of Iowa, 1972), by Virandrakumar Chaturbhai Patel and Naval Ship Research and Development Center (page images at HathiTrust; US access only)
Additional measurements of the drag of surface irregularities in turbulent boundary layers (NACA, 1951), by W. Tillmann and United States National Advisory Committee for Aeronautics (page images at HathiTrust; US access only)
The Nature and variability of integrated boundary layer winds (Air Force Cambridge Research Laboratories, Air Force Systems Command, United States Air Force, 1974), by René V. Cormier and Air Force Cambridge Research Laboratories (U.S.) (page images at HathiTrust)
Measurements of hypersonic turbulent heat transfer on a highly cooled cone (White Oak, Maryland : United States Naval Ordnance Laboratory, 1967., 1967), by Donald M. Wilson and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
An analytical investigation of the flat plate turbulent boundary layer in compressible flow (White Oak, Maryland : United States Naval Ordnance Laboratory, 1967., 1967), by Neal Tetervin and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
A digital computer program for making comparative aerodynamic heat transfer and skin friction drag calculations (White Oak, Maryland : United States Naval Ordnance Laboratory, 1967., 1967), by Donald M. Wilson and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
An approximate method for the calculation of the reynolds analogy factor for a compressible turbulent boundary layer in a pressure gradient (White Oak, Maryland : United States Naval Ordnance Laboratory, 1967., 1967), by Neal Tetervin and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
An experimental investigation of the surface Pitot probe including effects of heat transfer and compressibility (White Oak, Maryland : United States Naval Ordnance Laboratory, 1968., 1968), by David L. Brott, Roland E. Lee, William Joseph Yanta, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
An exploratory theoretical investigation of the effect of longitudinal surface curvature on the turbulent boundary layer (White Oak, Maryland : United States Naval Ordnance Laboratory, 1969., 1969), by Neal Tetervin and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
A generalization to turbulent boundary layers of Mangler's transformation between axisymmetric and two-dimensional laminar boundary layers (White Oak, Maryland : United States Naval Ordnance Laboratory, 1969., 1969), by Neal Tetervin and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
A correlation of heat-transfer and skin-friction data and an experimental Reynolds analogy factor for highly cooled turbulent boundary layers at Mach 5.0 (White Oak, Maryland : United States Naval Ordnance Laboratory, 1969., 1969), by Donald M. Wilson and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Velocity profile, skin-friction balance and heat-transfer measurements of the turbulent boundary layers at Mach 5 and zero-pressure gradient (White Oak, Maryland : United States Naval Ordnance Laboratory, 1969., 1969), by Roland E. Lee, A. C. Leonas, William Joseph Yanta, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Hypersonic-turbulent boundary-layer separation over a cone-cylinder-flare configuration (White Oak, Maryland : United States Naval Ordnance Laboratory, 1969., 1969), by Arnold Polak, Chris A. Kalivretenos, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Investigation of substructure heating on cracked ablative heat shields (White Oak, Maryland : United States Naval Ordnance Laboratory, 1969., 1969), by Erhard M. Winkler, M. T. Madden, J. A. Koenig, Richard L. Humphrey, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Supersonic ablation studies with teflon (White Oak, Maryland : United States Naval Ordnance Laboratory, 1969., 1969), by Erhard M. Winkler, J. A. Koenig, Richard L. Humphrey, M. T. Madden, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
An experimental investigation of the compressible turbulent boundary layer with a favorable pressure gradient (White Oak, Maryland : United States Naval Ordnance Laboratory, 1969., 1969), by David L. Brott, Roland E. Lee, Robert L. Voisinet, William Joseph Yanta, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Two-dimensional jet interaction with a mach 4 mainstream (White Oak, Maryland : United States Naval Ordnance Laboratory, 1970., 1970), by Michael J Werle, David G. Shaffer, Richard T. Driftmyer, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Flow visualization studies of a fin protuberance partially Immersed in a turbulent boundary layer at mach 5 (White Oak, Maryland : United States Naval Ordnance Laboratory, 1970., 1970), by Allen E. Winkelmann and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Drag of several surface protrusion patterns at M = 5.0 (White Oak, Maryland : United States Naval Ordnance Laboratory, 1970., 1970), by John A. Darling and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
The prediction of turbulent boundary-layer separation Influenced by blowing (White Oak, Maryland : United States Naval Ordnance Laboratory, 1971., 1971), by Arnold Polak and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Calculation of magnus forces on axisymmetric bodies at small angles of attack with incompressible turbulent boundary layers (White Oak, Maryland : United States Naval Ordnance Laboratory, 1972., 1972), by Neal Tetervin and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Measurements of a mach 4.9 zero-pressure-gradient turbulent boundary layer with heat yransfer. Part 1, Data compilation (White Oak, Maryland : United States Naval Ordnance Laboratory, 1972., 1972), by Robert L. P. Voisinet, Roland E. Lee, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
A forward facing step study: the step height less than the boundary-layer thickness (White Oak, Maryland : United States Naval Ordnance Laboratory, 1973., 1973), by Richard T. Driftmyer and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Measurements of upstream history effects in compressible turbulent boundary layers (White Oak, Maryland : United States Naval Ordnance Laboratory, 1973., 1973), by David F. Gates and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
An aircraft investigation of turbulence in the lower layers of a marine boundary layer (Boulder, Colo. : Environmental Research Laboratories, 1973., 1973), by Robert Louis Grossman, B. R. Bean, and Environmental Research Laboratories (U.S.) (page images at HathiTrust)
A magnus theory for bodies of revolution (Albuquerque, New Mexico : Sandia Laboratories, Aeroballistics Division, 1973., 1973), by H. R. Vaughn, G. E. Reis, Sandia Corporation, and U.S. Atomic Energy Commission (page images at HathiTrust)
On the application and interpretation of coherent motion detectors (1991), by Charles Paul Gendrich (page images at HathiTrust; US access only)
Turbulent boundary layers in adverse pressure gradients (Baltimore, Maryland : Department of Aeronautics, the Johns Hopkins University, June 1953., 1953), by Francis H. Clauser and Johns Hopkins University. Department of Aeronautics (page images at HathiTrust; US access only)
Measurements of a supersonic favorable-pressure-gradient turbulent boundary layer with heat Transfer : part 1 -data compilation. (Silver Spring, Maryland : Naval Ordnance Laboratory, 1973., 1973), by Robert L. P. Voisinet, Roland E. Lee, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Comparative measurements of total temperature in a supersonic turbulent boundary layer using a conical equilibrium and combined temperature-pressure probe. (Silver Spring, Maryland : Naval Ordnance Laboratory, 1974, 1974), by R. L. P. Voisinet, H. U. Meier, Roland E. Lee, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Compressible turbulent skin friction on rough and rough/wavy walls in adiabatic flow. (Silver Spring, Maryland : Naval Ordnance Laboratory, White Oak, 1974., 1974), by Daniel C. Reda and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Analytical procedures used to obtain and evaluate the eddy viscosity and mixing length extracted from incompressible turbulent boundary layer data (Silver Spring, Maryland : Naval Ordnance Laboratory, 1974., 1974), by W. J. Glowacki and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Interacting supersonic turbulent boundary layers over a two-dimensional protuberance. (Silver Spring, Maryland : Naval Ordnance Laboratory, White Oak, 1974., 1974), by Arnold Polak and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
A Study of the effect of pressure gradient on the eddy viscosity and mixing length for incompressible equilibrium turbulent boundary layers (Silver Spring, Maryland : Naval Ordnance Laboratory, 1974., 1974), by W. J. Glowacki, S. W. Chi, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
Supersonic mixing of jets and turbulent boundary layers (Wright Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1957., 1957), by Harry E. Bailey, Arnold M. Kuethe, United States. Air Force. Air Research and Development Command, and Wright Air Development Center (page images at HathiTrust)
Inhibition of flow separation at high speed. Volume 1, Supersonic turbulent boundary layers (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1969., 1969), by Larry L. Lynes, Frederick K. Goodwin, Jack Norman Nielsen, Air Force Flight Dynamics Laboratory (U.S.), and Nielsen Engineering & Research (page images at HathiTrust)
Calculation of high speed inlet flows using the Navier-Stokes equations. Volume 1, Description of results / Doyle D. Knight. (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1980., 1980), by Doyle D. Knight, Air Force Flight Dynamics Laboratory (U.S.), and Rutgers University. Department of Mechanical & Aerospace Engineering (page images at HathiTrust)
Study of the effect of free-stream turbulence upon disturbances in the pre-transitional laminar boundary layer (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1982., 1982), by James M. Kendall, Air Force Wright Aeronautical Laboratories, Air Force Flight Dynamics Laboratory (U.S.), and Jet Propulsion Laboratory (U.S.) (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)
Mark IV supersonic-hypsersonic arbitrary-body program modifications and computer graphics. Volume II, Computer graphics (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1980., 1980), by S. Taylor, Air Force Flight Dynamics Laboratory (U.S.), Air Force Wright Aeronautical Laboratories, and inc Science Applications (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)
Finite span effects on flap heating and effectiveness in a turbulent boundary layer (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1980., 1980), by L. A. Cassel, S. Taylor, L. D. McMillen, Air Force Wright Aeronautical Laboratories, Air Force Flight Dynamics Laboratory (U.S.), and inc Science Applications (page images at HathiTrust)
Mark IV supersonic-hypsersonic arbitrary-body program modifications and computer graphics. Volume I, Surface streamline tracing (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 S. Taylor, Air Force Flight Dynamics Laboratory (U.S.), Air Force Wright Aeronautical Laboratories, and inc Science Applications (page images at HathiTrust)
Heat transfer and flow with separated and reattached boundary layers as produced by surface irregularities (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1956., 1956), by R. A. Seban, Berkeley. Institute of Engineering Research University of California, and Wright Air Development Center (page images at HathiTrust)
Boundary layer effects : proceedings of the 7th U.S. Air Force/Federal Republic of Germany Data Exchange Agreement Meeting (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1978., 1978), by Anthony W. Fiore, Air Force Flight Dynamics Laboratory (U.S.), Germany (West), United States Air Force, and Ohio) U.S. Air Force/Federal Republic of Germany Data Exchange Agreement Meeting (7th : 1978 : Wright Patterson Air Force Base (page images at HathiTrust)
Viscous and interacting flow field effects : proceedings of the 9th U.S. Air Force and the Federal Republic of Germany Data Exchange Agreement Meeting (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1984., 1984), by Md.) U.S. Air Force/Federal Republic of Germany Data Exchange Agreement Meeting (9th : 1984 : Silver Springs, Anthony W. Fiore, Air Force Flight Dynamics Laboratory (U.S.), and Air Force Wright Aeronautical Laboratories (page images at HathiTrust)
Prediction of pressure fuctuations associated with maneuvering re-entry weapons. Volume 1 (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1977., 1977), by Anthony L. Laganelli, John R. Howe, Air Force Flight Dynamics Laboratory (U.S.), United States. Air Force. Systems Command, and General Electric Company. Re-entry and Environmental Systems Division (page images at HathiTrust)
Three-dimensional turbulent boundary layers (Stanford, California : Stanford University, Department of Mechanical Engineering, Thermosciences Division, 1992., 1992), by O. Sendstad, Parviz Moin, Stanford University. Stanford University. Thermosciences Division, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Shock wave - turbulent boundary layer interaction in high speed flow (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, United States Air Force, 1975., 1975), by Michael S. Holden, Aerospace Research Laboratories (U.S.), and Calspan Corporation (page images at HathiTrust)
Effects of mass transfer into laminar and turbulent boundary layers over cones at angle of attack (Blacksburg, Virginia : Virginia Polytechnic Institute and State University, 1975., 1975), by Michael C. Frieders, Arnold Engineering Development Center, and Virginia Polytechnic Institute and State University (page images at HathiTrust)
Analytical approximation of two-dimensional separated turbulent boundary-layer velocity profiles (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1980., 1980), by T. W. Swafford, R. K. Matthews, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Fundamental studies of subsonic and transonic flow separation. Part I. First phase summary report (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1975., 1975), by Zhengming Wu, K. Anjaneyulu, Herbert Venghaus, L. Shen, R. Nygaard, C. H. Chen, K. C. Reddy, G. M. Elfstrom, Trevor H. Moulden, University of Tennessee (System). Space Institute, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Investigation of the physics of screech in supersonic jets and turbulent boundary layers at high Reynolds number and control of separation through oscillatory blowing (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, United States Air Force, 1996., 1996), by Hassan M. Nagib, Michael Hites, I. Wygnanski, Ahmed Naguib, Candace Wark, United States. Air Force. Office of Scientific Research, and Illinois Institute of Technology (page images at HathiTrust)
Turbulent boundary layer characteristics at high Reynolds number (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, 1975., 1975), by V. Zakkay, Aerospace Research Laboratories (U.S.), and New York University. Aerospace and Energetics Laboratory (page images at HathiTrust)
Dominance of radiated aerodynamic noise on boundary-layer transition in supersonic-hypersonic wind tunnels : theory and application (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Von Karman Gas Dynamics Facility, Air Force Systems Command, United States Air Force, 1978., 1978), by Samuel R. Pate, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
Evaluation of a method for computation of separated, turbulent, compressible boundary layers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1976., 1976), by M. C. Altstatt, Arnold Engineering Development Center, United States. Air Force. Systems Command, and Inc ARO (page images at HathiTrust)
Direct numerical simulation of compressible turbulent flows using adaptive spectral element method (Huntsville, Alabama : University of Alabama at Huntsville, Department of Mechanical Engineering, 1994., 1994), by T. J. Chung, K. T. Yoon, University of Alabama in Huntsville, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Stability and transition analysis for reentry tool, STAR (Arlington, Virginia. : Air Force Office of Scientific Research, 2006., 2006), by Helen L. Reed, Texas A & M University. Aerospace Engineering Department, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Separated and nonseparated turbulent flows about axisymmetric nozzle afterbodies. Part I, Detailed surface measurements (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1979., 1979), by John A. Benek, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
Experiments on the interaction with a turbulent boundary layer of a skewed shock wave of variable strength at mach 2.5 (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, 1975., 1975), by L. Michael Freeman, Robert H. Korkegi, and Aerospace Research Laboratories (U.S.) (page images at HathiTrust)
Advancing detached eddy simulation (Arlington, Virginia. : Air Force Office of Scientific Research, 2007., 2007), by Kyle D. Squires, Arizona State University. Department of Mechanical and Aerospace Engineering, 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)
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)
Three-dimensional shock wave-turbulent boundary layer interactions at Mach 6 (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, United States Air Force, 1975., 1975), by C. Herbert Law and Aerospace Research Laboratories (U.S.) (page images at HathiTrust)
Developing new generation of models for turbulent flows (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, United States Air Force, 1997., 1997), by Katepalli R. Sreenivasan, United States. Air Force. Office of Scientific Research, and Yale University. Department of Engineering and Applied Science (page images at HathiTrust)
An analytical and experimental study of the plane, incompressible, turbulent free shear layer with arbitrary velocity ratio and pressure gradient (Stanford, California : Department of Mechanical Engineering, Stanford University, 1963., 1963), by C. M. Sabin, Stanford University. Department of Mechanical Engineering, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Effects of acoustic and vortical disturbances on the turbulent boundary layer at free-stream Mach number 0.5 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1977., 1977), by John A. Benek, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
An Improved interaction method for calculating exhaust nozzle boattail flows (Mountain View, California : Nielsen Engineering & Research, Inc., 1980., 1980), by Gary D. Kuhn, United States. Air Force. Arnold Air Force Base, Arnold Engineering Development Center, and Nielsen Engineering & Research (page images at HathiTrust)
Controlled experiments on instabilities and transition to turbulence on elliptic cones at hypersonic mach numbers (Arlington, Virginia : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 2002., 2002), by Thomas C. Corke, University of Notre Dame, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Prediction of turbulent skin friction for two-dimensional, rib-type surface roughness using a discrete element approach (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1985., 1985), by Robert P. Taylor, Hugh W. Coleman, B. K. Hodge, Air Force Wright Aeronautical Laboratories, Air Force Flight Dynamics Laboratory (U.S.), and Rockwell International (page images at HathiTrust)
A robust scheme for control of skin friction and heat transfer in turbulent boundary layers via new instability mechanism (Arlington, Virginia. : Air Force Office of Scientific Research, 1998., 1998), by Fazle Hussain, Wade Schoppa, University of Houston. Department of Mechanical Engineering, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
A Method of calculating turbulent-boundary-layer growth at hypersonic Mach numbers (Arnold Air Force Base, Tennessee, Arnold Engineering Development Center, Air Research and Development Command, United States Air Force, 1959., 1959), by James C. Sivells, Robert G. Payne, Inc ARO, United States. Air Force. Arnold Air Force Base, and Arnold Engineering Development Center (page images at HathiTrust)
Analytical description of the complete two-dimensional turbulent boundary-layer velocity profile (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1977., 1977), by David L. Whitfield, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
Control of separation for turbulent boundary layers subjected to wall curvature and streamwise pressure gradients (Arlington, Virginia : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 2005., 2005), by Hermann F. Fasel, University of Arizona. Department of Aerospace and Mechanical Engineering, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Analysis of the three-dimensional compressible turbulent boundary layer on a sharp cone at incidence in supersonic and hypersonic flow (Arnold Air Force Base, Tennessee : Von Kármán Gas Dynamics Facility, Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1972., 1972), by John C. Adams, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Numerical investigation of surface curvature effects in compressible turbulent flows (Bolling Air Force Base, D. C. : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 1994., 1994), by L. D. Kral, John F. Donovan, McDonnell Douglas Aerospace (Firm), and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Noise generation in transonic wind tunnels (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1975., 1975), by M. O. Varner, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Viscous flow interaction studies : final report on work unit 7064 02 06 (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, 1975., 1975), by Robert H. Korkegi and Aerospace Research Laboratories (U.S.) (page images at HathiTrust)
Wing pressure distribution and boundary layer data obtained from C-5A flight testing (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, United States Air Force, 1974., 1974), by Jones F. Cahill, William A. Stevens, Aerospace Research Laboratories (U.S.), and Lockheed-Georgia Company (page images at HathiTrust)
Turbulent flow control (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, United States Air Force, 1995., 1995), by William C. Reynolds, United States. Air Force. Office of Scientific Research, and Stanford University. Department of Mechanical Engineering (page images at HathiTrust)
Wall temperature effects on two- and three-dimensional transonic turbulent boundary layers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1973., 1973), by J. C Adams, Arloe W Mayne, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Flow transition in gas turbine airfoil boundary layers: fundamentals and empiricisms (Wright-Patterson Air Force Base, Ohio : Aero Propulsion Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1985., 1985), by Gregory S. West, Lit S. Han, Air Force Wright Aeronautical Laboratories, and University of Dayton. Research Institute (page images at HathiTrust)
Research on supersonic turbulent separated and reattached flows (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, United States Air Force, 1975., 1975), by Seymour M. Bogdonoff, G. Simpers, G. S. Settles, Irwin E. Vas, Aerospace Research Laboratories (U.S.), and Princeton University. Gas Dynamics Laboratory (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)
Two-dimensional turbulent boundary layer separation on a flat plate with ramp at freestream Mach numbers of 3.7 and 6.3 in supersonic and hypersonic flow (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, 1975., 1975), by V. Zakkay, Aerospace Research Laboratories (U.S.), and New York University. Aerospace and Energetics Laboratory (page images at HathiTrust)
Wall models for large-eddy simulation based on optimal control theory (Arlington, Virginia. : Air Force Office of Scientific Research, 2006., 2006), by Parviz Moin, Meng Wang, Jeremy A. Templeton, Stanford University. Department of Mechanical Engineering, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Numerical study of separated turbulent flows (Wright-Patterson Air Force Base, Ohio : Aeronautical Research Laboratories, Air Force Systems Command, 1974., 1974), by David C. Wilcox, Aerospace Research Laboratories (U.S.), and United States. National Technical Information Service (page images at HathiTrust)
Wave evolution and laminar-turbulent transition in fully 3D supersonic flows (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, United States Air Force, 1996., 1996), by T. Herbert and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Theoretical investigation of 3-D shock wave-turbulent boundary layer interactions : part VII (New Brunswick, New Jersey : Rutgers University, Department. of Mechanical and Aerospace Engineering, 1988., 1988), by Doyle D. Knight, United States. Air Force. Office of Scientific Research, and Rutgers University. Department of Mechanical & Aerospace Engineering (page images at HathiTrust)
A Method for computing boundary-layer flows, including normal pressure gradient and longitudinal curvature effects (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 Arloe W. Mayne, United States. Air Force. Arnold Air Force Base, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
An experimental investigation of the flow structure of the turbulent boundary layer (Stanford, California : Department of Mechanical Engineering, Stanford University, 1963., 1963), by Peter W. Runstadler, William C. Reynolds, S. J. Kline, Stanford University. Department of Mechanical Engineering, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Transition in high-speed boundary layers : numerical investigations using DNS and LES (Arlington, Virginia : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 2005., 2005), by Hermann F. Fasel, University of Arizona. Department of Aerospace and Mechanical Engineering, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Parametric study of hypersonic turbulent boundary layers with heat transfer (Wright-Patterson Air Force Base, Ohio : Aeronautical Research Laboratories, Hypersonic Research Laboratory, Air Force Systems Command, United States Air Force, 1974., 1974), by J. S. Shang, Aerospace Research Laboratories (U.S.), and Hypersonic Research Laboratory (U.S.) (page images at HathiTrust)
Integral analysis of ducted two-stream mixing with recirculation (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Engine Test Facility, Air Force Systems Command, United States Air Force, 1978., 1978), by C. E. Peters, W. J. Phares, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
Uniform roughness studies (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Directorate, Wright Laboratory, Air Force Systems Command, United States Air Force, 1992., 1992), by David E. Klett, M. Kithcart, Ohio) Wright Laboratory (Wright-Patterson Air Force Base, Air Force Flight Dynamics Laboratory (U.S.), North Carolina Agricultural and Technical State University, and Wright-Patterson Air Force Base (Ohio) (page images at HathiTrust)
Integral solution of compressible turbulent boundary layers using improved velocity profiles (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1978., 1978), by David L. Whitfield, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
Critical sting length as determined by the measurement of pitch-damping derivatives for laminar, transitional, and turbulent boundary layers at Mach number 3 for reduced frequencies of 0.0033 and 0.0056 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Von Karman Gas Dynaqmics Facility, Air Force Systems Command, United States Air Force, 1977., 1977), by Bob L. Uselton, Fred B. Cyran, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
Numerical study of a three-dimensional turbulent boundary layer (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 1990., 1990), by Parviz Moin, United States. Air Force. Office of Scientific Research, and Stanford University. Department of Mechanical Engineering (page images at HathiTrust)
Fundamental studies of subsonic and transonic flow separation. Part III. Third phase summary report (Tullahoma, Tennessee : The University of Tennesse Space Institute, Gas Dynamics Division, 1979., 1979), by Zhengming Wu, Arnold Engineering Development Center, and University of Tennessee (System). Space Institute (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)
Investigation of supersonic boundary layer transition and turbulent structure (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 1990., 1990), by Alexander J. Smits, R. B. Miles, Princeton University. Gas Dynamics Laboratory, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Boundary layer transition and surface roughness effects in hypersonic flow (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 1981., 1981), by Michael S. Holden, Calspan Corporation. Advanced Technology Center, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Holographic interferometry measurements of subsonic turbulent boundary layers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1979., 1979), by D. W. Sinclair, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
Two-dimensional compression corner and planar shock wave interactions with a supersonic, turbulent boundary layer (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, 1975., 1975), by C. Herbert Law, Aerospace Research Laboratories (U.S.), and Aerospace Research Laboratories (U.S.). Theoretical Aerodynamics Research Laboratory (page images at HathiTrust)
Continued computational investigation of MEMS : hybrid surfaces (Arlington, Virginia : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 2003., 2003), by David B. Goldstein, University of Texas at Austin. Department of Aerospace Engineering and Engineering Mechanics, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
Development and validation of RNG methodology for compressible turbulence (New Brunswick, New Jersey : Rutgers University, Department. of Mechanical and Aerospace Engineering, 1993., 1993), by George Karniadakis, United States. Air Force. Office of Scientific Research, and Rutgers University. Department of Mechanical & Aerospace Engineering (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)
Simple models for turbulent wave-current bottom boundary layer flow (Vicksburg, Mississippi : Coastal Engineering Research Center, U.S. Army Engineer Waterways Experiment Station, 1991., 1991), by Ole Secher Madsen, Palitha Nalin Wikramanayake, U.S. Army Engineer Waterways Experiment Station, Coastal Engineering Research Center (U.S.), Dredging Research Program (U.S.), and Ralph M. Parsons Laboratory for Water Resources and Hydrodynamics (page images at HathiTrust)
Bottom friction under waves in the presence of a weak current (Environmental Research Laboratories, Marine Ecosystems Analysis Program [Office], 1978., 1978), by William Denny Grant, Atlantic Oceanographic and Meteorological Laboratories, Marine EcoSystems Analysis Program, and Massachusetts Institute of Technology (page images at HathiTrust)
Computation of turbulent boundary layers employing the defect wall-function method (National Aeronautics and Space Administration, Langley Research Center, 1994), by Douglas L. Brown and Langley Research Center (page images at HathiTrust)
Turbulent boundary layer measurement techniques (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1986., 1986), by F. Kevin Owen, A. W. Fiore, Air Force Wright Aeronautical Laboratories, Air Force Flight Dynamics Laboratory (U.S.), and Inc Complere (page images at HathiTrust)
Experimental study on high subsonic turbulent flow incipient separation (Redstone Arsenal, Alabama ; U.S. Army Missile Command, 1976., 1976), by Jain-Ming Wu, Hideki Kuwano, Redstone Arsenal (Ala.), United States. Army. Missile Command, and University of Tennessee (System). Space Institute (page images at HathiTrust)
Calculation of high speed inlet flows using the Navier-Stokes equations. Volume II, User's and programmer's guide (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1980., 1980), by Doyle D. Knight, Air Force Flight Dynamics Laboratory (U.S.), Air Force Wright Aeronautical Laboratories, and Rutgers University. Department of Mechanical & Aerospace Engineering (page images at HathiTrust)
Measurements of local skin friction in a microbubble modified turbulent boundary layer (Arlington, Virginia : Office of Naval Research, 1984., 1984), by N. K. Madavan, C. L. Merkle, S. Deutsch, Pennsylvania State University. Applied Research Laboratory, United States. Naval Sea Systems Command, and United States. Office of Naval Research (page images at HathiTrust)

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