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Boundary layer

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• Aerodynamics
• Fluid dynamics

• Film coefficients (Physics)
• Laminar boundary layer
• Thermal boundary layer
• Turbulent boundary layer
• Wall pressure (Aerodynamics)

• 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 laminar boundary-layer flow on rotating cylinders. ([Ithaca, N. Y., Cornell University, Graduate School of Aeronautical Engineering, 1957-), by Shao-Wen Liu (page images at HathiTrust; US access only)
• The solution of the laminar-boundary-layer equation for the flat plate for velocity and temperature fields for variable physical properties and for the diffusion field at high concentration : = Über die lösung der laminaren grenzschichtgleichung an der ebenen platte für geschwindigkeits- und temperaturfeld bei veränderlichen stoffwerten und für das diffusionsfeld bei höheren konzentrationen / (Washington, D.C. : National Advisory Committee for Aeronautics, 1950), by H. Schuh and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Drag reduction by suction of the boundary layer separated behind shock wave formation at high mach numbers / (Washington, D.C. : NACA, 1947), by B. Regenscheit and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• On the three-dimensional instability of laminar boundary layers on concave walls / (Washington : NACA, 1954), by Henry Görtler and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigations on reductions of friction on wings, in particular by means of boundary layer suction / (Washington, D.C. : NACA, 1947), by Werner Pfenninger and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Boundary layer / (Washington : National Advisory Committee for Aeronautics, 1956), by L. G. Loĭt�si�anskiĭ and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Systematic investigations of the influence of the shape of the profile upon the position of the transition point / (Washington, D.C. : NACA, 1947), by K. Bussmann, A. Ulrich, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigations of the boundary-layer control on a full scale swept wing with air bled off from the turbojet / (Washington, D.C. : NACA, 1952), by Pierre Rebuffet, Ph. Poisson-Quinton, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Higher-order accurate Osher schemes with application to compressible boundary layer stability / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : National Technical Information Service, distributor, 1993), by J.J.W. Van Der Vegt and United States National Aeronautics and Space Administration (page images at HathiTrust)
• In-flight use of traversing boundary-layer probes / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971), by Edwin J. Saltzman, Flight Research Center (U.S.), and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Numerical method for the solution of large systems of differential equations of the boundary-layer type [electronic resource] / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by Michael J. Green, Philip R. Nachtsheim, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• Full-coverage film cooling on flat, isothermal surfaces : a summary report on data and predictions / (Washington, D.C. : U.S. National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by M. E. Crawford, R. J. Moffat, W. M. Kays, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• An experimental investigation of regions of separated laminar flow / (Washington : NACA, 1955), by Donald E. Gault and United States. National Advisory Committee for Aeronautics (page images at HathiTrust; US access only)
• Numerical computation of shock wave : turbulent boundary layer interaction in transonic flow over an axisymmetric curved hill / ([Washington, DC] : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1989]), by S.-W. Kim and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Nonlinear evolution of the first mode supersonic oblique waves in compressible boundary layers. (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : National Technical Information Service, 1993), by J. S. B. Gajjar and United States National Aeronautics and Space Administration (page images at HathiTrust)
• The effect of small streamwise velocity distortion on the boundary layer flow over a thin flat plate with application to boundary layer stability theory ([Washington, DC] : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1990]), by M. E. Goldstein, Stephen J. Cowley, S. J. Leib, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Similarity solutions for small cross flows in laminar compressible boundary layers, ([Washington, U.S. G.P.O.], 1961), by Ivan E. Beckwith (page images at HathiTrust)
• A theoretical method for the analysis and design of axisymmetric bodies / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by T. D. Beatty, Langley Research Center, and McDonnell Douglas Corporation (page images at HathiTrust)
• Weak incident shock interactions with Mach 8 laminar boundary layers / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Louis G. Kaufman, Charles B. Johnson, and Langley Research Center (page images at HathiTrust)
• An experimental investigation of wall boundary-layer transition Reynolds numbers in an expansion tube / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by K. James Weilmuenster and Langley Research Center (page images at HathiTrust)
• Analysis of unsteady thermal boundary layers / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by Roy W. Miller and Lewis Research Center (page images at HathiTrust)
• A study of boundary layer transition on outgassing cones in hypersonic flow / (Washington, D.C. : National Aeronautics and Space Administration, 1971), by C. J. Stalmach, United States National Aeronautics and Space Administration, Vought Aeronautics Company, and Langley Research Center (page images at HathiTrust)
• Nonparallel instability of supersonic and hypersonic boundary layers / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1991), by Nabil M. El-Hady, Langley Research Center, and Inc Analytical Services & Materials (page images at HathiTrust)
• An analysis of the coupled chemically reacting boundary layer and charring ablator, (Washington, D.C., National Aeronautics and Space Administration, 1968), by Itek Corporation. Vidya Division, Carl B. Moyer, Roald A. Rindall, Eugene P. Bartlett, and Robert M. Kendall (page images at HathiTrust)
• An analysis of the relaxation of laminar boundary layer on a flat plate after passage of an interface with application to expansion-tube flows / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by Roop N. Gupta and Langley Research Center (page images at HathiTrust)
• A finite-difference method for predicting supersonic turbulent boundary-layer flows with tangential slot injection / (Washington, D.C. : 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)
• Assessment of a transitional boundary layer theory at low hypersonic mach numbers / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by S. J. Shamroth, H. McDonald, Langley Research Center, and United Aircraft Corporation (page images at HathiTrust)
• Numerical investigation of unsteady laminar incompressible co-axial boundary layer flows (Washington, National Aeronautics and Space Administration; Springfield, Va., For sale by the Clearinghouse for Federal Scientific and Technical Information, 1967), by Urmila Agarwal, T. Paul Torda, United States National Aeronautics and Space Administration, Lewis Research Center, and Illinois Institute of Technology (page images at HathiTrust)
• A Review of flight and wind tunnel measurements of boundary layer pressure fluctuations and induced structural response / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1966), by David Alan Bies, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Experimental studies of hypersonic boundary-layer transition and effects of wind-tunnel disturbances / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by P. Calvin Stainback and Langley Research Center (page images at HathiTrust)
• Some problems of the calculation of three-dimensional boundary-layer flows on general configurations / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Tuncer Cebeci, Langley Research Center, and Douglas Aircraft Company (page images at HathiTrust)
• A model of wind shear and turbulence in the surface boundary layer / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by National Technical Information Service], 1973), by James K. Luers, George C. Marshall Space Flight Center, and University of Dayton. Research Institute (page images at HathiTrust)
• An experimental study of near wall flow parameters in the blade end-wall corner region / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1989), by Rakesh K. Bhargava, Rishi S. Raj, and Lewis Research Center (page images at HathiTrust)
• Jet-boundary corrections for lifting rotors centered in rectangular wind tunnels / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1960), by Harry H. Heyson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Subsonic annular wing theory with application to flow about nacelles / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Michael J. Mann and Langley Research Center (page images at HathiTrust)
• Calculation of compressible, nonadiabatic boundary layers in laminar, transitional and turbulent flow by the method of integral relations / (Washington, D.C. : 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)
• Calculation of turbulent boundary layers with heat transfer and pressure gradient utilizing a compressibility transformation. (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1972), by J. Schneider, J. Boccio, Langley Research Center, and Nassau County General Applied Science Laboratories (Westbury (page images at HathiTrust)
• Effects of forebody geometry on subsonic boundary-layer stability / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1990), by S. S. Dodbele, Langley Research Center, Vigyan Research Associates, and Québec) International Conference on Numerical Methods in Laminar and Turbulent Flow (5th : 1987 : Montréal (page images at HathiTrust)
• Experimental investigation in an annular cascade sector of highly loaded turbine stator blading. ([Washington] National Aeronautics and Space Administration; for sale by the Clearinghouse for Federal, Scientific and Technical Information, Springfield, Va., [1968-), by General Motors Corporation, James L. Bettner, and Lewis Research Center (page images at HathiTrust)
• Study of the pressure distribution on oscillating panels in low supersonic flow with turbulent boundary layer / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1967), by E. F. E. Zeydel, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• A boundary layer approach to the analysis of atmospheric motion over a surface obstruction / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Walter Frost, W. R. Simpson, J. R. Maus, George C. Marshall Space Flight Center, and University of Tennessee (System). Space Institute (page images at HathiTrust)
• Calculations of compressible average turbulent skin friction / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1962), by Mitchel H. Bertram (page images at HathiTrust)
• Heat-transfer and pressure distributions for laminar separated flows downstream of rearward-facing steps with and without mass suction / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Ronald D. Brown, Antoni K. Jakubowski, and Langley Research Center (page images at HathiTrust)
• Boundary-layer analysis of subsonic inlet diffuser geometries for engine nacelles / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by James A. Albers, E. John Felderman, and Lewis Research Center (page images at HathiTrust)
• Comparison of measured and calculated velocity profiles of a laminar incompressible free jet at low Reynolds numbers / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by George C. Greene and Langley Research Center (page images at HathiTrust)
• Flight-measured base pressure coefficients for thick boundary-layer flow over an aft-facing step for Mach numbers from 0.4 to 2.5 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Sheryll A. Goecke and Flight Research Center (U.S.) (page images at HathiTrust)
• Experimental and analytical study of a conically diffused flow with a nearly separated boundary layer / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Donald R. Boldman, Harvey E. Neumann, and Lewis Research Center (page images at HathiTrust)
• A direct numerical method for predicting concentration profiles in a turbulent boundary layer over a flat plate. (Washington : National Aeronautics and Space Admin., 1972), by James Dow and Mississippi State University (page images at HathiTrust)
• Boundary layer stability on a yawed spinning body of revolution and its effect on the magnus force and moment / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by I. D. Jacobson, J. B. Morton, Langley Research Center, and University of Virginia (page images at HathiTrust)
• A review of carbon monoxide sources, sinks, and concentrations in the earth's atmosphere / (Washington : National Aeronautics and Space Admin., 1972), by M. H. Bortner and General Electric Company. Space Sciences Laboratory (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 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by Atlee M. Cunningham and Gregory S. Spragle (page images at HathiTrust)
• General solution of the laminar compressible boundary layer in the stagnation region of blunt bodies in axisymmetric flow / (Washington, D.C. : National Aeronautics and Space Administration, 1964), by Fred W. Matting, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Attached and separated boundary layers on highly cooled, ablating and nonablating models at M=13.8 / ([Washington, D.C.] : National Aeronautics and Space Administration ; for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va., [1967]), by Donald M. Kuehn and Daryl J. Monson (page images at HathiTrust)
• Discrete sonic jets used as boundary-layer trips at Mach numbers of 6 and 8.5 (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by David R. Stone, Aubrey M. Cary, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Analytical and experimental studies of shock interference heating in hypersonic flows (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by J. Wayne Keyes, Frank D. Hains, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Theoretical and experimental internal flow characteristics of a 13.97-centimeter-diameter inlet at STOL takeoff and approach conditions / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by James A. Albers and Lewis Research Center (page images at HathiTrust)
• Effects of wall cooling and angle of attack on boundary-layer transition on sharp cones at M[mathematical symbol for infinity] = 7.4 (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by George G. Mateer, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• Boundary-layer electron profiles for entry of a blunt slender body at high altitude / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by John S. Evans, Paul W. Huber, Charles J. Schnexnayder, and Langley Research Center (page images at HathiTrust)
• Influence of edge conditions on the stability of axially compressed cylindrical shells / ([Washington] : National Aeronautics and Space Administration, [1965]), by B. O. Almroth, Lockheed Missiles and Space Company, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• The numerical calculation of laminar boundary-layer separation / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by John M. Klineberg, Joseph L. Steger, and Ames Research Center (page images at HathiTrust)
• Analysis of sound propagation in ducts using the wave envelope concept / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Kenneth J. Baumeister (page images at HathiTrust)
• Boundary-layer transition and displacement-thickness effects on zero-lift drag of a series of power-law bodies at Mach 6 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by George C. Ashby, Julius E. Harris, and Langley Research Center (page images at HathiTrust)
• Sweep effect on the drag of rows of perpendicular circular cylinders in a laminar boundary layer at supersonic free-stream velocities / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Milton Lamb, Robert L. Stallings, and Langley Research Center (page images at HathiTrust)
• Experimental and numerical investigation of boundary-layer development and transition on the walls of a Mach 5 nozzle / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by William D. Harvey, Julius E. Harris, Aubrey M. Cary, and Langley Research Center (page images at HathiTrust)
• Analysis of boundary-layer transition on X-15-2 research airplane, ([Washington] National Aeronautics and Space Administration; for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va., [1966]), by Albert L. Braslow (page images at HathiTrust)
• Analysis of an existing experiment on the interaction of acoustic waves with a laminar boundary layer / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 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)
• Calculation of three-dimensional boundary layers on ship forms / (Iowa City : Iowa Institute of Hydraulic Research, University of Iowa, 1975), by Kua C. Chang, V. C. Patel, and United States. Office of Naval Research (page images at HathiTrust; US access only)
• Lift hysteresis at stall as an unsteady boundary-layer phenomenon / (Washington, D.C. : U.S. Government Printing Office, 1956), by F. K. Moore and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• A literature survey of boundary-layer development on smooth and rough surfaces at zero pressure gradient. (Iowa City, Iowa Institute of Hydraulic Research, State University of Iowa, 1951), by William Douglas Baines (page images at HathiTrust)
• Lecture series "Boundary layer theory." / (Washington : National Advisory Committee for Aeronautics, 1949), by Hermann Schlichting (page images at HathiTrust)
• Evaluation of porous materials for boundary-layer control (Wright-Patterson Air Force Base, O. : Industrial Resources Division, Air Material Command, Wright Air Development Center, U. S. Air Force, 1956), by Battelle Memorial Institute and David E. Debeau (page images at HathiTrust)
• Catalytic surface recombination in boundary-layer profiles of the Falkner-Skan type. (Buffalo, Cornell Aeronautical Laboratory, Inc., 1962), by William Joseph Rae (page images at HathiTrust)
• Boundary layer and wake modifications to compressor design systems : the effect of blade-to-blade flow variations on the mean flow field of a transonic rotor : final report, 01 September 1976-31 August 1978 / (Wright-Patterson Air Force Base, Ohio : Air Force Aero Propulsion Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1979), by Arun K. Sehra (page images at HathiTrust)
• The shock layer concept and three-dimensional hypersonic boundary layers. (Buffalo, Cornell Aeronautical Laboratory, 1961), by Hsien Kei Cheng (page images at HathiTrust)
• Helium injection into the boundary layer at an axisymmetric stagnation point (Wright-Patterson Air Force Base, Ohio, Aeronautical Research Laboratory, Office of Aerospace Research, U. S. Air Force, 1961), by Herbert Fox and Paul Andrew Libby (page images at HathiTrust)
• A flight test comparison of take-off performance of two liaison type airplane configurations. (Buffalo, Cornell Aeronautical Laboratory, Inc., 1959), by Donald W. Rhoads (page images at HathiTrust)
• On the inviscid stability of the boundary layer on a flexible wall, (Buffalo, Cornell Aeronautical Laboratory, 1960), by William Joseph Rae and Franklin Kingston Moore (page images at HathiTrust)
• A dual doppler radar study of the urban boundary layer : a summary of METROMEX results / (Boulder, Colo. : U.S. Dept. of Commerce, National Oceanic and Atmospheric Administration, Environmental Research Laboratories, [1977]), by Robert A. Kropfli, Environmental Research Laboratories (U.S.), and Wave Propagation Laboratory (page images at HathiTrust)
• A numerical method of calculating the boundary-induced interference in slotted of perforated wind tunnels of rectangular cross section / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Office of Technical Services, Department of Commerce, Washington, D.C. 20230], 1971), by James D. Keller, Ray H. Wright, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Boundary-layer transition study of several pointed bodies of revolution at supersonic speeds, (Washington, National Aeronautics and Space Administration; [for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], 1970), by William A. Cassels and James F. Campbell (page images at HathiTrust; US access only)
• Charts for estimating boundary-layer transition on flat plates / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 20230], 1970), by Edward J. Hopkins, Virginia L. Sorensen, Don W. Jillie, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Boundary-layer measurements in accelerated flows near Mach 1 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1967), by Howard L. Wesoky, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Friction and wear of poly(amide-imide), polyimide, and pyrrone polymers at 260° C (500° F) in dry air / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971), by William R. Jones, Robert L. Johnson, William F. Hady, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• A critical evaluation of analytic methods for predicting laminar boundary-layer, shock-wave interaction / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1971), by John D. Murphy, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Measurements of boundary layer transition, separation and streamline direction on rotating blades / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971), by William J. McCroskey, U.S. Army Air Mobility Research and Development Laboratory, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Integral methods in the theory of the boundary layer, (Washington, 1944), by L. G. Loĭ︠t︡si︠a︡nskiĭ and S. Reiss (page images at HathiTrust; US access only)
• Shock tube test time limitation due to turbulent wall boundary layer. ([El Segundo?], 1963), by Aerospace Corporation and Harold Mirels (page images at HathiTrust)
• Boundary layer and chemical reactions, ([Washington] National Aeronautics and Space Administration; for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va., [1969]), by B. V. Alekseev (page images at HathiTrust; US access only)
• Examination of boundary conditions for heat transfer through a porous wall / (Washington, D.C.: National Aeronautics and Space Administration:, 1971), by Raymond S. Colladay (page images at HathiTrust; US access only)
• The stagnation-point boundary layer with suction and injection in equilibrium dissociating air / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1968), by Kenneth C. Weston, Manned Spacecraft Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• The magnetosphere and its boundary / (Washington, D.C. : National Aeronautics and Space Administration, 1965), by Tatsuzo Obayashi, Goddard Space Flight Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Nonsteady discharge of subcritical flow / (Princeton, N.J. : Project Squid Headquarters, James Forrestal Research Center, Princeton University, 1960), by George Rudinger and Project Squid (page images at HathiTrust)
• On local flat-plate similarity in the hypersonic boundary layer, (Buffalo, Cornell Aeronautical Laboratory, Inc. of Cornell Laboratory, 1960), by Franklin Kingston Moore (page images at HathiTrust)
• Boundary effects of uniform size roughness elements in two-dimensional flow in open channels / (Vicksburg, Miss. : Waterways Experiment Station, 1968), by Bobby J. Brown and Yen-Hsi Chu (page images at HathiTrust)
• Boundary layer radioactive tracer technique / (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, 1955-), by Frances M. Richardson, K. O. Beatty, J. K. Ferrell, and Wright Air Development Center (page images at HathiTrust)
• Multigrid direct numerical simulation of the whole process of flow transition in 3-D boundary layers / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : National Technical Information Service, distributor, 1993), by Chaoqun Liu, Zhining Liu, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• The flow of gas in channels in the presence of heat transfer / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1965), by M. M. Nazarchuk, M. M. Nazarchuk, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Similar solutions for the compressible boundary layer on a yawed cylinder with transpiration cooling [electronic resource] / (Langley Field, VA : Langley Research Center ; Springfield, Va. : for sale by the National Technical Information Service, 1959), by Ivan E. Beckwith and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Stability analysis and minimum thrust vector control requirements of booster vehicles during atmospheric flight / (Washington, D. C. : National Aeronautics and Space Administration ; Springfield, Va. : for sale by the Clearinghouse for Federal Scientific and Technical Information, 1968), by Janos Borsody, Fred Teren, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Calculation of viscous effects on transonic flow for oscillating airfoils and comparisons with experiment / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1987), by James T. Howlett, Samuel R. Bland, and Langley Research Center (page images at HathiTrust)
• Viscous hypersonic flow past a slender cone / ([Washington, D.C. :] National Aeronautics and Space Administration, [1967]), by V. S. Nikolaev (page images at HathiTrust)
• Viscous-inviscid calculations of jet entrainment effects on the subsonic flow over nozzle afterbodies / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by Richard G. Wilmoth, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Investigations of a flow field surrounding circular-arc boattail nozzles at subsonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by William Kelly Abeyounis, Lawrence E. Putnam, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Prediction method for two-dimensional aerodynamic losses of cooled vanes using integral boundary-layer parameters / (Washington, D.C. : U.S. National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by Louis J. Goldman, Raymond E. Gaugler, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Lewis Research Center (page images at HathiTrust)
• Influence of free-stream disturbances on boundary-layer transition. (Washington : National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Bill Harvey (page images at HathiTrust)
• Effect of ratio of wall boundary-layer thickness to jet diameter on mixing of a normal hydrogen jet in a supersonic stream / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Charles R. McClinton and Langley Research Center (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 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by George C. Ashby and Langley Research Center (page images at HathiTrust)
• R4 airfoil data corrected for sidewall boundary-layer effects in the Langley 0.3-meter transonic cryogenic tunnel / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1986), by Renaldo V. Jenkins and Langley Research Center (page images at HathiTrust)
• An experimental investigation of boundary layer and crossflow characteristics of the AMes 2- by 2-foot and 11- by 11-foot transonic wind-tunnel walls / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Gerald Edwin Matyk, Yasunori Kobayashu, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Mach 6 flow field surveys beneath the forebody of an airbreatinng missile / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1986), by Patrick J. Johnston, James L. Hunt, and Langley Research Center (page images at HathiTrust)
• Evaluation of some control-volume techniques for analysis of shock-boundary-layer interactions in supersonic inlets / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Warren R. Hingst and Lewis Research Center (page images at HathiTrust)
• Boundary-layer transition on a plate subjected to simultaneous spanwise and chordwise pressure gradients / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Donald R. Boldman, Paul F. Brinich, and Lewis Research Center (page images at HathiTrust)
• Effects of mass addition on blunt-body boundary-layer transition and heat transfer / (Washington : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by George E. Kaattari and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• A theoretical investigation of forebody shapes designed for natural laminar boundary-layer flow / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1979), by Raymond L. Barger, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Critical study of higher order numerical methods for solving the boundary-layer equations / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Stephen F. Wornom, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Aerodynamic heating in gaps of thermal protection system tile arrays in laminar and turbulent boundary layers / ([Washington, D.C.] : National Aeronautics and Space Administration, Scientific and Technical Information Office, 1978), by Don E. Avery (page images at HathiTrust)
• Comparison of experimental and theoretical boundary-layer separation for inlets at incidence angle at low-speed conditions / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by E. John Felderman, Lewis Research Center, and James A. Albers (page images at HathiTrust)
• Effects of roughness size on the position of boundary-layer transition and on the aerodynamics characteristics of a 55 ̊swept delta wing at supersonic speeds / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Robert L. Stallings, Milton Lamb, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Detailed transonic flow field measurements about a supercritical airfoil section / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Francis X. Hurley and Ames Research Center (page images at HathiTrust)
• A description of the active and passive sidewall-boundary-layer removal systems of the 0.3-meter transonic cryogenic tunnel / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1986), by Charles B. Johnson, Edward J. Ray, A. V. Murthy, and Langley Research Center (page images at HathiTrust)
• Characteristics of Mach 10 transitional and turbulent boundary layers / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 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)
• Inverse boundary-layer theory and comparsion with experiment / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by James E. Carter, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• In-flight transition measurement on a 10⁰ cone at Mach numbers from 0.5 to 2.0 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1982), by David F. Fisher, N. Sam Dougherty, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Dryden Flight Research Facility (page images at HathiTrust)
• Wind-tunnel measurements and comparison with flight of the boundary layer and heat transfer on a hollow cylinder at Mach 3 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by Robert L. Stallings, Milton Lamb, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Görtler vortices and transition in wall boundary layers of two Mach 5 nozzles / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Ivan E. Beckwith, Barbara B. Holley, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)
• Direct simulation of high-speed mixing layers / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by H. S. Mukunda and Langley Research Center (page images at HathiTrust)
• Wall-temperature effects on the aerodynamics of a hydrogen-fueled transport concept in Mach 8 blowdown and shock tunnels / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1983), by Jim A. Penland, Sharon H. Stack, Don C. Marcum, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Free-stream noise and transition measurements on a cone in a Mach 3.5 pilot low-disturbance tunnel / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1983), by Ivan E. Beckwith and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Modeling of the heat transfer in bypass transitional boundary-layer flows / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991), by Frederick F. Simon, Craig A. Stephens, and Lewis Research Center (page images at HathiTrust)
• Analysis of dynamic stall using unsteady boundary-layer theory / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1974]), by R. M. Scruggs, R. E. Singleton, John F. Nash, Langley Research Center, and Inc Scientific & Business Consultants (page images at HathiTrust)
• Fluctuating surface-pressure characteristics on slender cones in subsonic, supersonic, and hypersonic Mach-number flow / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by H. Heller, Anthony R. Clemente, Langley Research Center, and Beranek Bolt (page images at HathiTrust)
• Reduction of acoustic disturbances in the test section of supersonic wind tunnels by laminarizing their nozzle and test section wall boundary layers by means of suction / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by W. Pfenninger, J. Syberg, Langley Research Center, and Boeing Commercial Airplane Company (page images at HathiTrust)
• A general method for calculating three-dimensional compressible laminar and turbulent boundary layers on arbitrary wings / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Tuncer Cebeci, Judy A. Ramsey, Kalle Kaups, McDonnell Douglas Corporation, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Vorticity interaction effects on blunt bodies / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by E. Clay Anderson, David C. Wilcox, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Dynamic response of some tentative compliant wall structures to convected trubulence fields / ([Washington] : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by H. H. Nijim, Y. K. Lin, University of Illinois at Urbana-Champaign, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Vibroacoustic response of structures and perturbation Reynolds stress near structure-turbulence interface / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by S. Maekawa, Y. K. Lin, University of Illinois at Urbana-Champaign, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• A Computer program to calculate incompressible laminar and turbulent boundary layer development / (Washington, D.C. : National Aeronautics and Space Administration, 1970), by H. J. Herring, G. L. Mellor, United States National Aeronautics and Space Administration, Lewis Research Center, and Princeton University (page images at HathiTrust)
• An improved analytical model of the separation region on boattail nozzles at subsonic speeds / (Washington : National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va. : For sale by the National Technical Information Service, 1978), by Walter M. Presz, John D. Buteau, Ronald W. King, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• On the wall-normal velocity of the compressible boundary-layer equations / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991), by C. David Pruett, Inc Analytical Services and Materials, and Langley Research Center (page images at HathiTrust)
• The receptivity of boundary layers on blunt bodies to oscillations in the free stream / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1982), by C. E. Grosch, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Correlation of data related to shock-induced trailing-edge separation and extrapolation to flight Reynolds number / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1979), by J. F. Cahill, P. C. Connor, Ames Research Center, and Lockheed-Georgia Company (page images at HathiTrust)
• Transition fixing for hypersonic flow / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1967]), by James R. Sterrett and Langley Research Center (page images at HathiTrust)
• Analysis of melting boundary layers on decelerating bodies / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, 1962]), by Simon Ostrach, Jesse Hamman, Arthur W. Goldstein, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Experimental laminar, transitional, and turbulent boundary-layer profiles on a wedge at local Mach number 6.5 and comparisons with theory / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151], 1971), by Michael C. Fischer, Dal V. Maddalon, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• The influence of low wall temperature on boundary-layer transition and local heat transfer on 2-inch-diameter hemispheres at a Mach number of 4.95 and a Reynolds number per foot of 73.2 x 10⁶ / (Washington : National Aeronautics and Space Administration, [1960]), by Morton Cooper, Jerome D. Julius, Edward E. Mayo, and Langley Research Center (page images at HathiTrust)
• A simplified study on the nonequilibrium Couette and boundary-layer flows with air injection / (Washington : National Aeronautics and Space Administration, [1960]), by Paul M. Chung and Ames Research Center (page images at HathiTrust)
• Investigation by Schlieren technique of methods of fixing fully turbulent flow on models at supersonic speeds / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Mary W. Jackson, K. R. Czarnecki, and Langley Research Center (page images at HathiTrust)
• A semiempirical model for boundary layer diffusion in forced convection flow / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1970]), by Alex Vary and Lewis Research Center (page images at HathiTrust)
• Experimental determination of the recovery factor and analytical solution of the conical flow field for a 20 ̊included angle cone at Mach numbers of 4.6 and 6.0 and stagnation temperatures to 2600 ̊R / (Washington : National Aeronautics and Space Administration, [1961]), by Frank A. Pfyl, Leroy L. Presley, and Ames Research Center (page images at HathiTrust)
• Experimental boundary-layer edge Mach numbers for two space shuttle orbiters at hypersonic speeds / (Washington, DC : National Aeronautics and Space Administration, 1972), by George C. Ashby, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Wind-tunnel investigation of a 3/8-scale automobile model over a moving-belt ground plane / (Washington, D. C. : National Aeronautics and Space Administration ; Springfield, Va. : for sale by the Clearinghouse for Federal Scientific and Technical Information, 1967), by Thomas R. Turner, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Heat transfer and pressure distribution at a mach number of 6.8 on bodies with conical flares and extensive flow separation.&bJonh V. Becker and Peter F. Korycinski. (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce], [1962]), by John V. Becker, Peter F. Korycinski, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Turbulence, heat-transfer, and boundary layer measurements in a conical nozzle with a controlled inlet velocity profile / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce], [1966]), by Donald R. Boldman, Anthony Fortini, James F. Schmidt, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Investigation at transonic speeds of loading over a 30 deg sweptback wing of aspect ratio 3, taper ratio 0.2, and NACA 65A004 airfoil section mounted on a body / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, [1960]), by Donald D. Arabian and United States National Aeronautics and Space Administration (page images at HathiTrust)
• An investigation of heat transfer within regions of separated flow at a Mach number of 6.0 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1965]), by Paul F. Holloway, Helen S. Creekmore, James R. Sterrett, and Langley Research Center (page images at HathiTrust)
• Interference heating on a swept cylinder in region of intersection with a wedge at Mach number 8 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1965]), by Dennis M. Bushnell and Langley Research Center (page images at HathiTrust)
• Effect of fabrication-type surface roughness on transition on ogive-cylinder models at Mach number of 1.61 and 2.01 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce], [1963]), by Paul W. Howard, K. R. Czarnecki, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effects of boundary-layer suction and spoilers on transonic flutter derivatives for a midspan control surface on an upswept wing / (Washington, [D.C.] : National Aeronautics and Space Administration, 1960), by Jone A. Wyss, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Evaluation of a technique to generate artificially thickened boundary layers in supersonic and hypersonic flows / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ; Springfield, Va. : For sale by the National Technical Information Service, 1991), by A. Robert Porro and Lewis Research Center (page images at HathiTrust)
• The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil : suction coefficient analysis / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ; Springfield, Va. : For sale by the National Technical Information Service, 1991), by Cuyler W. Brooks, William D. Harvey, Charles D. Harris, and Langley Research Center (page images at HathiTrust)
• Status of linear boundary-layer stability theory and the en method, with emphasis on swept-wing applications / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by Jerry N. Hefner, Dennis M. Bushnell, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Calculation of laminar heating rates on three-dimensional configurations using the axisymmetric analogue / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by H. Harris Hamilton, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Flight-measured laminar boundary layer transition phenomena including stability theory analysis / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Technical Information Service, 1985), by Clifford J. Obara, Bruce J. Holmes, and Langley Research Center (page images at HathiTrust)
• F-8 supercritical wing flight pressure, boundary-layer, and wake measurements and comparisons with wind tunnel data / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by Lawrence C. Montoya, Richard D. Banner, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Comparison of theoretical and experimental boundary-layer development in a Mach 2.5 mixed-compression inlet / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Warren R. Hingst, Charles E. Towne, and Lewis Research Center (page images at HathiTrust)
• Experimental evaluation of a Mach 3.5 axisymmetric inlet / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1975]), by J. Syberg, J. L. Koncsek, Ames Research Center, and Boeing Commercial Airplane Company (page images at HathiTrust)
• Full-coverage film cooling heat transfer study : summary of data for normal-hole injection and 30 ̊slant-hole injection / (Washington : U.S. National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by M. E. Crawford, Lewis Research Center, Stanford University, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Higher-order numerical methods derived from three-point polynomial interpolation / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1976]), by Stanley G. Rubin, Prem K. Khosla, Langley Research Center, and Nassau County General Applied Science Laboratories (Westbury (page images at HathiTrust)
• STAN5 - a program for numerical computation of two-dimensional internal and external boundary layer flows / (Washington : National Aeronautics and Space Administration ; For sale by the National Technical Information Service, 1976), by M. E. Crawford, W. M. Kays, Stanford University, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Heat transfer to a full-coverage film-cooled surface with 30 ̊slant-hole injection / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1976), by M. E. Crawford, R. J. Moffat, W. M. Kays, Stanford University, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Hyperbolic/parabolic development for the GIM-STAR code / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1980), by L. W. Spradley, A. W. Ratliff, J. F. Stalnaker, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Basic experimental study of the coupling between flow instabilities and incident sound / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1984), by K. K. Ahuja, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, Lockheed-Georgia Company, and Lewis Research Center (page images at HathiTrust)
• General design method for three-dimensional potential flow fields / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; Springfield, Va. : For sale by the National Techincal Information Service, 1980-1985), by John D. Stanitz and Lewis Research Center (page images at HathiTrust)
• Heat transfer to a full-coverage, film-cooled surface with compound-angle (30 ̊and 45)̊ hole injection / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by H. K. Kim, W. M. Kays, R. J. Moffat, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Full-coverage film cooling : 3-dimensional measurements of turbulence structure and prediction of recovery region hydrodynamics / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va. : For sale by the National Technical Information Service], 1979), by S. Yavuzkurt, W. M. Kays, R. J. Moffat, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• A transonic interactive boundary-layer theory for laminar and turbulent flow over swept wings / (Washington, D.C. : 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)
• Sidewall boundary-layer measurements with upstream suction in the Langley 0.3-meter Transonic Cryogenic Tunnel / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988), by A. V. Murthy and Langley Research Center (page images at HathiTrust)
• Analysis of turbulent flow and heat transfer on a flat plate at high mach numbers with variable fluid properties, ([Washington, U.S. G.P.O.], 1959), by R. G. Deissler (page images at HathiTrust)
• Testing of transition-region models, test cases and data [microform] / ([Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; [Springfield, Va. : For sale by the National Technical Information Service, 1991]), by Bart A. Singer, Venkit Iyer, Surya P. G. Dinavahi, United States. National Aeronautics and Space Administration. Scientific and Technical Information Division, Inc ViGYAN, Inc Analytical Services & Materials, and High Technology Corporation (page images at HathiTrust)
• The eigenvalue spectrum of the Orr-Sommerfeld problem / (Washington : National Aeronautics and Space Administration ;, 1976), by B. N. Antar (page images at HathiTrust)
• Inverse solutions for laminar boundary-layer flows with separation and reattachment / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by James E. Carter and Langley Research Center (page images at HathiTrust)
• Correlation formulas and tables of density and some transport properties of equilibrium dissociating air for use in solutions of the boundary-layer equations / (Washington : National Aeronautics and Space Administration, [1960]), by Nathaniel B. Cohen and Langley Research Center (page images at HathiTrust)
• An approximation method for the integration of the equations of a nonstationary laminar boundary layer in an incompressible fluid / (Washington, D.C. : National Aeronautics and Space Administration, 1960), by L. A. Rozin (page images at HathiTrust)
• On the relation between the generation of a lift force on a wing and the character of the flow in the boundary layer / (Washington : National Aeronautics and Space Administration, 1960), by I. V. Ostoslavskiĭ and T. A. Grumondz (page images at HathiTrust)
• Boundary-layer equations and their boundary conditions in the case of motion at supersonic velocities in a moderately rarefied gas / (Washington, D.C. : National Aeronautics and Space Administration, 1960), by I︠U︡. N. Lunkin (page images at HathiTrust)
• On the calculation of steady boundary layers for continuous suction, with discontinuously variable suction velocity / (Washington, D.C. : National Aeronautics and Space Administration, 1961), by Werner C. Rheinboldt (page images at HathiTrust)
• "Similar" three-dimensional boundary layers / (Washington, D.C. : National Aeronautics and Space Administration, 1961), by Theo Geis (page images at HathiTrust)
• The leading-edge effects on the laminar flat-plate boundary layer and the aerodynamic heating at Mach 10.4 / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Howard W. Stone, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Pressure and heat transfer on blunt curved plates with concave and convex surfaces in hypersonic flow / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1968), by Davis H. Crawford, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• An experimental investigation of boundary-layer transition on a 10 ̊half-angle cone at Mach 6.9 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151], 1970), by Michael C. Fischer, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• A method for analyzing the interaction of an oblique shock wave with a boundary layer / (Washington, D.C. : National Aeronautics and Space Administration, 1970), by William C. Rose, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• Boundary-layer velocity profiles downstream of three-dimensional transition trips on a flat plate at Mach 3 and 4 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1969]), by John B. Peterson, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• A method for solving the nonsimilar laminar boundary-layer equations including foreign gas injection / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Joseph G. Marvin, Yvonne S. Sheaffer, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Boundary lubrication and thermal stability studies with five liquid lubricants in nitrogen to 400° C / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971), by William R. Jones, William F. Hady, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Starting phenomena for hypersonic inlets with thick turbulent boundary layers at Mach 6 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971), by Theodore J. Goldberg, Jerry N. Hefner, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Laminar boundary-layer separation induced by flares on cylinders with highly cooled boundary layers at a Mach number of 15 / (Washington, D.C. : National Aeronautics and Space Administration : For sale by the Office of Technical Services, Dept. of Commerce, [1965]), by Donald M. Kuehn and Ames Research Center (page images at HathiTrust)
• Effects of shock impingement and other factors on leading-edge heat transfer / (Washington, D. C. : National Aeronautics and Space Administration ; Springfield, Va. : for sale by the Clearinghouse for Federal Scientific and Technical Information, 1968), by Dennis M. Bushnell, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Boundary layer measurements in an accelerated flow with and without heat transfer / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1971]), by Howard L. Wesoky, Charlene May, and Lewis Research Center (page images at HathiTrust)
• Laminar boundary layer in the presence of suction, ([Washington] National Aeronautics and Space Administration; for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va., [1970]), by L. F. Kozlov (page images at HathiTrust; US access only)
• Heat-transfer measurements on a flat plate and attached fins at Mach numbers of 3.51 and 4.44 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1964), by Earl A. Price, Robert L. Stallings, Paul W. Howard, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Afterbody pressures on two-dimensional boattailed bodies having turbulent boundary layers at Mach 5.98 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1964), by W. Frank Staylor, Theodore J. Goldberg, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• A method for determining the total drag of a pointed body of revolution in supersonic flow with turbulent boundary layer / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Charlie M. Jackson, Rudeen S. Smith, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Use of Preston tubes for measuring hypersonic turbulent skin friction / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Earl R. Keener, Edward J. Hopkins, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• The eckert reference formulation applied to high-speed laminar boundary layers of nitrogen and carbon dioxide / (Washington, D.C. : National Aeronautics and Space Administration, 1966), by H. A. Simon, J. P. Hartnett, and C. S. Liu (page images at HathiTrust; US access only)
• Theoretical laminar convective heat transfer and boundary-layer characteristics on cones at speeds to 24 km/sec / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia], 1964), by Gary T. Chapman, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust; US access only)
• Boundary layers on rotating spheres and other axisymmetric shapes / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Office of Technical Services, Department of Commerce, Washington, D.C. 20230], 1964), by Jay Fox, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Integral methods in compressible laminar boundary layers and their application to hypersonic pressure interactions / (Washington, D.C. : National Aeronautics and Space Administration, 1965), by Yat-Yung Chan (page images at HathiTrust; US access only)
• Laminar boundary layer on a cone in supersonic flow with uniform mass transfer / (Washington, D.C. : National Aeronautics and Space Administration, 1966), by Paul A. Libby (page images at HathiTrust; US access only)
• An analytical study of separated flows induced by shock wave - boundary layer interaction / (Washington, D.C. : National Aeronautics and Space Administration, 1966), by M. S. Holden (page images at HathiTrust; US access only)
• Heat and mass transfer at a general three-dimensional stagnation point / (Washington, D.C. : National Aeronautics and Space Administration, 1967), by Paul A. Libby (page images at HathiTrust; US access only)
• The solution of laminar boundary layer equations by the finite differnce method, (Santa Monica, Cal., 1960), by Douglas Aircraft Company and J. C. Wu (page images at HathiTrust; US access only)
• Transition caused by the Laminar flow separation / (Washington : NACA, 1952), by T. Maekawa, S. Atsumi, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• The boundary layer in a corner ([Princeton, N.J.] Princeton University, 1959), by Sin-I. Cheng, Richard H. Levy, and United States. Air Force. Air Research and Development Command (page images at HathiTrust; US access only)
• Effects of boundary layer buildup in shock tubes upon chemical rate measurements / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1968), by Marvin Warshay, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Viscous hypersonic flow : theory of reacting and hypersonic boundary layers. (New York : McGraw-Hill, 1962), by William H. Dorrance (page images at HathiTrust)
• The three-dimensional boundary layer / ([Inyokern, 1951?]), by Calif.) Naval Ordnance Test Station (Inyokern and Wallace D. Hayes (page images at HathiTrust)
• Airborne LIDAR Raps studies, February, 1974 / (Las Vegas, Nev. : U.S. Environmental Protection Agency, Environmental Monitoring and Support Laboratory, 1976), by John A. Eckert (page images at HathiTrust; US access only)
• New methods in laminar boundary-layer theory. (New York, Pergamon Press, 1961), by D. Meksyn (page images at HathiTrust)
• NACA Conference on Boundary Layers; a compilation of the papers presented, Langley Memorial Aeronautical Laboratory, Langley Field, Va., August 14, 1947. ([Washington?, 1947?]), by United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Aerodynamic considerations on the injection of tornado-generated missiles from ground level into tornado flow fields / (Washington : The Division ; Springfield, Va. : for sale by National Technical Information Service, 1979), by R. T. Hall, Naval Surface Weapons Center, and United States. Office of Nuclear Reactor Regulation. Division of Site Safety and Environmental Analysis (page images at HathiTrust)
• Heat transfer to boundary layers with pressure gradients /, by Ralph Alois Seban, Hugh Won Chan, United States. Air Force. Air Research and Development Command. sponsor, Wright Air Development Center issuing body, and Berkeley University of California (page images at HathiTrust)
• On the flow over a finite wedge in the lower transonic region /, by Hideo Yoshihara, United States. Air Force. Air Research and Development Command. sponsor, and Wright Air Development Center issuing body (page images at HathiTrust)
• Effects of the upstream influence of a shock wave at supersonic speeds in the presence of a separated boundary layer /, by Lloyd E. Daniels, H. Yoshihara, sponsor United States. Air Force. Air Research and Development Command, and issuing body Wright Air Development Center (page images at HathiTrust)
• An experimental study of the interaction of strong sound fields with free convection boundary layers /, by Arthur L. Sprott, Frederick L. Durand, Jack P. Holman, United States. Air Force. Air Research and Development Command. sponsor, and Wright Air Development Center issuing body (page images at HathiTrust)
• Survey of boundary layer heat transfer at high velocities and high temperatures /, by E. R. G. Eckert, United States. Air Force. Air Research and Development Command. sponsor, Wright Air Development Center issuing body, University of Minnesota, and United States. Department of the Air Force. Wright Air Development Center (page images at HathiTrust)
• Exact solution of laminar heat transfer in wedge-shaped passages with various boundary conditions /, by J. T. Yen, United States. Air Force. Air Research and Development Command. sponsor, University of Minnesota, Heat Transfer Laboratory, and Wright Air Development Center (page images at HathiTrust)
• Investigation of shock : boundary-layer interaction on the spike of a conical-spike nose inlet / (Washington, D.C. : National Advisory Committee for Aeronautics, 1957), by George A. Wise, William H. Sterbentz, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Investigation at transonic speeds of aerodynamic characteristics of an unswept semielliptical air inlet in the root of a 45©� sweptback wing / (Washington, D.C. : National Advisory Committee for Aeronautics, 1955), by Gene J. Bingham, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• A method for the design of porous-wall wind tunnels / (Washington, D.C. : National Advisory Committee for Aeronautics, 1956), by George M. Stokes, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Experimental investigation of temperature recovery factors on bodies of revolution at supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by William R. Wimbrow and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• The use of a luminescent lacquer for the visual indication of boundary-layer transition / (Washington, D.C. : National Advisory Committee for Aeronautics, 1951), by Jackson R. Stalder, Ellis G. Slack, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Generalization of boundary-layer momentum-integral equations to three-dimensional flows including those of rotating system / (Washington, D.C. : National Advisory Committee for Aeronautics, 1951), by Artur Mager and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• A visualization study of secondary flows in cascades / (Washington, D.C. : National Advisory Committee for Aeronautics, [1953]), by Arthur G. Hansen, George R. Costello, Howard Z. Herzig, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Comparison of secondary flows and boundary-layer accumulations in several turbine nozzles / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by Milton G. Kofskey, Howard Z. Herzig, Hubert W. Allen, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Boundary-layer studies on spinning bodies of revolution /, by Walter B. Sturek, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Correlation parameters for two-dimensional jet interaction /, by Richard E. Lottero and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• Boundary layer studies on a spinning cone /, by Walter B. Sturek and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• Similarity solution of the boundary layer equations for flow over a moving wall /, by James Edward Danberg, Kevin S. Fansler, and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• Additional two-dimensional wake and jet-like flows /, by James Edward Danberg, Kevin S. Fansler, and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• An integral analysis of boundary layers on moving walls /, by Kevin S. Fansler, James Edward Danberg, and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• Boundary layer studies on a spinning tangent-oglive-cylinder model /, by Walter B. Sturek and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• Boundary layer transition on the NOL standard cone in the Ballistic Research Laboratories' supersonic wind tunnels /, by J. C. McMullen and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• CO₂ laser radiation absorption in SF₆ -air boundary layers /, by John D. Anderson, Joseph Knott, Jerry L. Wagner, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Numerical analysis of boundary layer problems /, by Wm. D. Murphy and Courant Institute of Mathematical Sciences (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 /, by W. J. Glowacki, S. W. Chi, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• an Integral approach to transient heat-conduction problems with phase transition /, by Tse-Fou Zien and Naval Surface Weapons Center. White Oak Laboratory (page images at HathiTrust)
• Some higher order integral identities with application to bounding techniques /, by J. H. Bramble, B. E. Hubbard, College Park. Institute for Fluid Dynamics and Applied Mathematics University of Maryland, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Investigation at supersonic and subsonic Mach numbers of auxiliary inlets supplying secondary air flow to ejector exhaust nozzles / (Washington, D.C. : National Advisory Committee for Aeronautics, [1956]), by Donald P. Hearth, Robert W. Cubbison, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Comparison of results of experimental and theoretical studies of blade-outlet boundary-layer characteristics of stator blade for a high subsonic Mach number turbine / (Washington, D.C. : National Advisory Committee for Aeronautics, 1957), by Cavour H. Hauser, William J. Nusbaum, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Influence of wall boundary layer upon the performance of an axial-flow fan rotor / (Washington, D.C. : National Advisory Committee for Aeronautics, 1947./), by Emanuel Boxer, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• The effect of the inlet mach number and inlet-boundary-layer thickness on the performance of a 23©� conical-diffuser-tail-pipe combination / (Washington, D.C. : National Advisory Committee for Aeronautics, 1950), by Jerome Persh, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Investigation of a simple device for preventing separation due to shock and boundary-layer interaction / (Washington, D.C. : National Advisory Committee for Aeronautics, 1950), by Coleman duP. Donaldson, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Experimental investigation of the mixing loss behind trailing edge of a cascade of three 90©� supersonic turning passages / (Washington, D.C. : National Advisory Committee for Aeronautics, 1950), by Luke L. Liccini, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Low-speed wind-tunnel investigation of a triangular sweptback air inlet in the root of a 45 degree sweptback wing / (Washington, D.C. : National Advisory Committee for Aeronautics, 1950), by Arvid L. Keith, Jack Schiff, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Preliminary investigation of the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA RM-10) at a Mach number of 1.61 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1952), by K. R. Czarnecki, Archibald R. Sinclair, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Average skin-friction coefficients from boundary-layer measurements on an ogive-cylinder body in flight at supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by J. Dan Loposer, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Factors affecting transition at supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, 1953), by K. R. Czarnecki, Archibald R. Sinclair, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Normal force, center of pressure, and zero-lift drag of several ballistic-type missiles at Mach numbers of 4.05 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1954), by Edward F. Ulmann, Robert W. Dunning, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Attainable circulation of airfoils in cascade / (Washington, D.C. : National Advisory Committee for Aeronautics, 1949), by Arthur W. Goldstein, Artur Mager, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Analysis of turbulent free-convection boundary layer on flat plate / (Washington, D.C. : National Advisory Committee for Aeronautics, 1950), by E. R. G. Eckert, Thomas W. Jackson, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Influence of wall boundary layer upon the performance of an axial-flow fan rotor / (Washington, D.C. : National Advisory Committee for Aeronautics, 1951), by Emanuel Boxer 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 / (Washington, D.C. : 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)
• Exact solutions of laminar-boundary-layer equations with constant property values for porous wall with variable temperature / (Washington, D.C. : National Advisory Committee for Aeronautics, [1954]), by Patrick L. Donoughe, John N. B. Livingood, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Preliminary results from a free-flight investigation of boundary-layer transition and heat transfer on a highly polished 8-inch-diameter hemisphere-cylinder at Mach numbers up to 3 and Reynolds numbers based on a length of 1 foot up to 17.7 x 10⁶ / (Washington, D.C. : National Advisory Committee for Aeronautics, 1957), by J. R. Hall, Robert O. Piland, Katherine C. Speegle, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Heat, mass, and momentum transfer for flow over a flat plate with blowing or suction / (Washington, D.C. : National Advisory Committee for Aeronautics, 1954), by H. S. Mickley and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Calculation of the velocity profiles of the incompressible laminar boundary layer on a yawed spinning cone and the magnus effect /, by Ira D. Jacobson, Jeffrey B. Morton, Allen Gregory Vollmer, U.S. Army Ballistic Research Laboratory, and University of Virginia. School of Engineering and Applied Science (page images at HathiTrust)
• Contributions of a wall shear stress to the Magnus effect on nose shapes /, by Ira D. Jacobson, U.S. Army Ballistic Research Laboratory, and University of Virginia (page images at HathiTrust)
• Experimental verification of the inertial oscillations of a fluid in a cylinder during spin-up /, by K. D. Aldridge, U.S. Army Ballistic Research Laboratory, and University of British Columbia. Department of Geophysics and Astronomy (page images at HathiTrust)
• Wall heat transfer effects on supersonic nozzle wall boundary-layer temperature profiles /, by Walter B. Sturek, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Compressible turbulent boundary layer computations for flow with longitudinal curvature /, by Walter B. Sturek, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Preliminary surveys of the three dimensional boundary layer on a yawed, spinning body of revolution /, by Walter B. Sturek, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Characteristics of the sidewall and floor boundary layers in BRL supersonic wind tunnel no. 1 /, by Clarence W. Kitchens, Raymond Sedney, Clarence C. Bush, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
• The effects of steady, three-dimensional perturbations in boundary layers /, by Raymond Sedney and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• Computational implications of the zone of dependence concept for three-dimensional boundary layers on a spinning body /, by Clarence W. Kitchens, Raymond Sedney, Nathan Gerber, and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• A nonsimilar moving wall boundary layer problem /, by James Edward Danberg, Kevin S. Fansler, and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• The structure of three-dimensional separated flows in obstacle-boundary layer interactions /, by Raymond Sedney, Clarence W. Kitchens, and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• A solution for laminar flow past rotating cylinder in crossflow /, by Kevin S. Fansler, James Edward Danberg, and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• The singular nature of three-dimensional perturbations of boundary layers and the small cross flow theory /, by Raymond Sedney and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• The role of the zone of dependence concept in three-dimensional boundary-layer calculations /, by Clarence W. Kitchens, Nathan Gerber, Raymond Sedney, and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• Turbulent boundary layers in blast wave and shock tube flows /, by Raymond Sedney, Clarence W. Kitchens, and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• Vertical profiles of wind speeds from measurements of high towers /, by M. M. Borisenko, M. V. Zavarina, and Air Force Cambridge Research Laboratories (U.S.) (page images at HathiTrust)
• On the use of a scale-dependent filter in channel model integrations / (Hanscom AFB, Massachusetts : Air Force Cambridge Research Laboratories, Air Force Systems Command, United States Air Force, 1975), by Stephen Mudrick and Air Force Cambridge Research Laboratories (U.S.) (page images at HathiTrust)
• Hermite interpolation algorithm for constructing reasonable analytic curves through discrete data points / (L.G. Hanscom Field, Bedford, Massachusetts : Air Force Cambridge Research Laboratories, Air Force Systems Command, United States Air Force, 1973), by Paul Tsipouras, René V. Cormier, and Air Force Cambridge Research Laboratories (U.S.) (page images at HathiTrust)
• Atmospheric transmittance from 0.25 to 28.5 micrometers : supplement LOWTRAN 3B (1976) /, by J. E. A. Selby, R. A. McClatchey, Eric P. Shettle, and U.S. Air Force Geophysics Laboratory (page images at HathiTrust)
• The boundary layer in the confinement of a one-dimensional plasma /, by W. Paskievici, H. Weitzner, A. Sestero, U.S. Atomic Energy Commission. New York Operations Office, and Courant Institute of Mathematical Sciences (page images at HathiTrust)
• A critical review of analytical methods for estimating control forces produced by secondary injection : the two dimensional problem /, by Michael J Werle and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Solutions of the second-order boundary-layer equations for laminar incompressible flow /, by Michael J Werle and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• A hot-wire stagnation temperature probe /, by William Joseph Yanta and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• A fine-wire stagnation temperature probe /, by William Joseph Yanta and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• The effect of base bleed on the drag and magnus characteristics of a rotating body of revolution /, by Frank J Regan, Virginia L. Schermerhorn, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• On the numerical determination of shrinkage stresses /, by Frances Bauer, Edward L. Reiss, Courant Institute of Mathematical Sciences, and U.S. Atomic Energy Commission. AEC Research and Development Report (page images at HathiTrust)
• Stresses in cantilver plates /, by Frances Bauer, Edward L. Reiss, Courant Institute of Mathematical Sciences, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Viscous shock-layer flow in the windward plane of cones at angle of attack /, by R. R Eaton, P. C. Kaestner, Sandia Corporation, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Temperature-step effects on direct measurement of skin-friction drag /, by Robert L. P. Voisinet and Naval Surface Weapons Center. White Oak Laboratory (page images at HathiTrust)
• Diagnostics for and evaluations of new physical parameterization schemes for global NWP models /, by Chien-Hsiung Yang, Samuel Y.K. Yee, Donald C. Norquist, Kenneth E. Mitchell, United States. Air Force. System Command. Air Force Geophysics Laboratory. issuing agency, and sponsor Geophysics Laboratory (U.S.). Atmospheric Sciences Division (page images at HathiTrust)
• Skin friction, heat transfer, and pressure measurements on hypersonic inlet compression surfaces in the Mach number range 7.5 to 16 /, by M. O. Ryder, sponsor Cornell Aeronautical Laboratory, and sponsor Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• An experimental and analytical investigation of hypersonic inlet boundary layers /, by J. F. Stroud, L. D. Miller, sponsor Air Force Flight Dynamics Laboratory (U.S.), and sponsor Lockheed-California Company (page images at HathiTrust)
• Heating in regions of interfering flow fields /, by C. E. Gulbran, S. L. Strack, D. S. Miller, E. Redeker, and sponsor Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Boundary-layer measurements on several porous materials with suction applied / (Washington, D.C. : National Advisory Committee for Aeronautics, [1952]), by George B. McCullough, Bruno J. Gambucci, United States. National Advisory Committee for Aeronautics. NACA research memorandum, and Ames Research Center (page images at HathiTrust)
• Heat transfer to blunt nose shapes with laminar boundary layers at high supersonic speeds / (Washington, D.C. : National Advisory Committee for Aeronautics, [1957]), by John O. Jr Reller, United States. National Advisory Committee for Aeronautics. NACA research memorandum, and Ames Research Center (page images at HathiTrust)
• An investigation of a thermal ice-prevention system for a C-46 cargo airplane. 1 - Analysis of the thermal design for wings, empennage, and windshield / (Washington, D.C. : National Advisory Committee for Aeronautics, [1945]), by Carr Neel, Ames Research Center, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• A study of velocity profiles in the momentum integral method with slip boundary conditions / ([Albuquerque, New Mexico], [Sandia Corporation], 1963), by K. J. Touryan, Sandia Corporation, and U.S. Atomic Energy Commission (page images at HathiTrust; US access only)
• A Preliminary assessment of the monostatic acoustic sounder as a forecast aid in the prediction of advection fogs at a Massachusetts coastal station /, by Bruce A. Kunkel and U.S. Air Force Geophysics Laboratory (page images at HathiTrust)
• Blending of Surface and Rawinsonde Data in Mesoscale Objective Analysis /, by Samuel Y. K. Yee, Arthur J. Jackson, and U.S. Air Force Geophysics Laboratory (page images at HathiTrust)
• Wind-tunnel investigation of the boundary layer on an NACA 0009 airfoil having 0.25- and 0.50-airfoil chord plain sealed flaps / (Washington, D.C. : National Advisory Committee for Aeronautics, 1948), by Jack D. Brewer, Josephine F. Polhamus, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• An Experimental investigation of the effect of surface heating on boundary-layer transition on a flat plate in supersonic flow / (Washington, D.C. : National Advisory Committee for Aeronautics, 1951), by Robert W. Higgins, Constantine C. Pappas, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Transportation of bed material due to wave action /, by George Kalkanis and Coastal Engineering Research Center (U.S.) (page images at HathiTrust)
• Models for the aerosols of the lower atmosphere and the effects of humidity variations on their optical properties /, by Eric P. Shettle, Robert W. Fenn, and U.S. Air Force Geophysics Laboratory (page images at HathiTrust)
• Research on sound propagation in sound-absorbent ducts with superimposed air streams : Volume 2 /, by F. Mechel, W. Schilz, and sponsor Aerospace Medical Research Laboratories (U.S.) (page images at HathiTrust)
• Hypersonic boundary layer transition experiments /, by Kenneth F. Stetson, issuing agency Air Force Wright Aeronautical Laboratories, and sponsor Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Research on sound propagation in sound-absorbent ducts with superimposed air streams : Volume 3 /, by F. Mechel, W. Schilz, P. Mertens, and sponsor Aerospace Medical Research Laboratories (U.S.) (page images at HathiTrust)
• Cavity oscillation in cruise missile carrier aircraft /, by Harold W. Bartel, James M. McAvoy, issuing agency Air Force Wright Aeronautical Laboratories, sponsor Air Force Flight Dynamics Laboratory (U.S.), and sponsor Lockheed-Georgia Company (page images at HathiTrust)
• Research on sound propagation in sound-absorbent ducts with superimposed air streams : Volume 1 /, by F. Mechel and sponsor Aerospace Medical Research Laboratories (U.S.) (page images at HathiTrust)
• Turbulent heat transfer on blunt-nosed bodies in two-dimensional and general three-dimensional hypersonic flow /, by Roberto Vaglio-Laurin, sponsor United States. Air Force. Air Research and Development Command, issuing body Wright Air Development Center, and sponsor Polytechnic Institute of Brooklyn. Department of Aeronautical Engineering and Applied Mechanics (page images at HathiTrust)
• Experiments in transonic flow /, by Jean G. Goppert, Joseph Flatt, issuing body United States. Air Force. Air Matériel Command, and sponsor California Institute of Technology (page images at HathiTrust)
• Final report : studies in hypersonic flow theory /, by Milton Van Dyke, Stanford University. Department of Aeronautics and Astronautics. sponsor, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• Point heat sources and the temperature-vorticity analogy in compressible boundary layers /, by W. J. McCroskey, United States. Air Force. Office of Scientific Research. issuing body, and Princeton University. Department of Aeronautical Engineering. sponsor (page images at HathiTrust)
• Velocity distributions in laminar and turbulent boundary layers with constant and variable free stream velocity, (Berkeley, Calif., 1954), by California. University. Institute of Engineering Research, D. Doughty, and R. A. Seban (page images at HathiTrust; US access only)
• Boundary-layer transition under hypersonic conditions /, by J. Leith Potter, Jack D. Whitfield, United States. Air Force. Arnold Air Force Base. sponsor, Arnold Engineering Development Center. issuing body, and Inc. ARO (page images at HathiTrust)
• Investigation of suction controlled boundary layer on a Northrop model at Mach numbers of 2, 5, 3, and 3.5 /, by W. T. Strike, J. C. Donaldson, Inc. sponsor ARO, and Arnold Engineering Development Center. issuing agency (page images at HathiTrust)
• A survey of transition research at AEDC /, by Jack D. Whitfield, N. Sam Dougherty, United States. Air Force. Systems Command. issuing body, sponsor Arnold Engineering Development Center, and Inc. ARO (page images at HathiTrust)
• An Evaluation of nozzle afterbody code : ARO2P /, by Frederick C. Guyton, United States. Air Force. Arnold Air Force Base. sponsor, Arnold Engineering Development Center. issuing body, and Calspan Corporation. sponsor (page images at HathiTrust)
• Artificially induced boundary-layer transition on blunt-slender cones using distributed roughness and spherical-type tripping devices at hypersonic speeds /, by A. H. Boudreau, United States. Air Force. Systems Command. issuing body, sponsor Arnold Engineering Development Center, and Inc. ARO (page images at HathiTrust)
• An experimental and analytic investigation of a transonic shock-wave/boundary-layer interaction /, by M. C. Alstatatt, United States. Air Force. Systems Command. issuing body, sponsor Arnold Engineering Development Center, and Inc. ARO (page images at HathiTrust)
• Investigation of drag reduction by boundary-layer suction on a flat plate and a 36-deg swept wing at supersonic speeds /, by S. R. Pate, J. S. Deitering, Inc. AEDC Division. sponsor Sverdrup/ARO, and Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• Investigation of boundary-layer transition on swept wings at mach numbers 2.5 to 5 /, by S. R. Pate, R. E. Brillhart, Inc. AEDC Division. sponsor Sverdrup/ARO, and Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• The Use of boundary-layer suction for maintaining laminar flow downstream of a reflected incidence shock wave on a flat plate at free-stream Mach numbers 2.5, 3, and 3.5 /, by S. R. Pate, Inc. sponsor ARO, Air Force Flight Dynamics Laboratory (U.S.). sponsor, and Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• Effects of unit Reynolds number, nose bluntness, and roughness on boundary layer transition /, by J. Leith Potter, Jack D. Whitfield, Inc. sponsor ARO, United States. Air Force. Arnold Air Force Base. sponsor, and Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• The effect of centrifugal forces on boundary layer transition for a highly heated body /, by Eugene Sevigny, sponsor United States. Air Force. Air Research and Development Command, issuing body Wright Air Development Center, and sponsor Polytechnic Institute of Brooklyn. Department of Aerospace Engineering and Applied Mechanics (page images at HathiTrust)
• Investigation of the effects of nose bluntness on natural and induced boundary-layer transition on axisymmetric bodies in supersonic flow /, by Jack D. Coats, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Computational study of inlet active flow control /, by Sonya T. Smith, Matthew Goettke, Angela Scribben, sponsor Howard University. Department of Mechanical Engineering, and Ohio). Air Vehicles Directorate Air Force Research Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
• Evaluation of critical sting length on a 7-deg cone as determined by measurements of dynamic stability derivatives and base pressure for Mach numbers 0.2 through 1.3 /, by Frederick B. Cyran, Edward J. Marquart, Bob L. Uselton, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Experiments in numerical studies of low density and real gas effects on regions of shock wave/boundary layer interaction in hypervelocity flows /, by Michael S. Holden, Ronald A. Parker, Matthew MacLean, Timothy P. Wadhams, and issuing body United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• An investigation of separated flows on two-dimensional models at Mach numbers 5 and 8 /, by A. L. Baer, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• The shock shape and shock detachment distance for spheres and flat-faced bodies in low-density, hypervelocity, argon flow /, by A. B. Bailey, W. H. Sims, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Mathematical fluid dynamic modeling of plasma stall-spin departure control /, by N. Malmuth, Victor Soloviev, Alexander Valerievich Fedorov, and issuing body United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• A comparison of transition Reynolds numbers from 12-in. and 40-in. supersonic tunnels /, by C. J. Schueler, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Boundary-layer transition correlation on a slender cone in wind tunnels and flight for indications of flow quality /, by N. Sam Dougherty, David F. Fisher, sponsor Hugh L. Dryden Flight Research Center, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• An analysis of initial static pressure probe measurements in a low-density hypervelocity wind tunnel /, by David E. Boylan, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Analysis of the three-dimensional compressible turbulent boundary layer on a sharp cone at incidence in supersonic and hypersonic flow /, by John C. Adams, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Flow characteristics of a 12-in. intermittent supersonic tunnel /, by A. Anderson, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Engineering model of unsteady flow in a cavity /, by R. C. Bauer, R. E. Dix, sponsor Calspan Corporation, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• The influence of slight leading-edge bluntness on boundary-layer transition at a Mach number of eight /, by Jack D. Whitfield, J. Leith Potter, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Inviscid and viscous hypersonic nozzle flow with finite rate chemical reactions /, by E. S. Levinsky, Jerome James Brainerd, sponsor General Dynamics Corporation. Astronautics Division, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Boundary-layer transition on cones near Mach one in an aeroballistic range /, by J. Leith Potter, J. R. Myers, Arnold Engineering Development Center. sponsor, United States. Air Force. Systems Command. issuing body, and Inc. ARO (page images at HathiTrust)
• Direct numerical simulation and experimental validation of hypersonic boundary-layer receptivity and instability /, by Xiaolin Zhong, Los Angeles. Mechanical University of California, and issuing body United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Experimental heat transfer to blunt axisymmetric bodies near the limit of continuum flow /, by J. Leith Potter, John T. Miller, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Boundary-layer characteristics at Mach numbers 2 through 5 in the test section of the 12-inch supersonic tunnel /, by D. R. Bell, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Development of LES methodology for the analysis of high-Reynolds number 2-D and 3-D dynamic stall phenomenon /, by K. N. Ghia, Urmila Ghia, sponsor University of Cincinnati. Department of Aerospace Engineering and Engineering Mechanics, and issuing body United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• An integral equation method for boundary interference in a perforated-wall wind tunnel at transonic speeds /, by E. M. Kraft, Arnold Engineering Development Center. sponsor, United States. Air Force. Systems Command. issuing body, and Inc. ARO (page images at HathiTrust)
• Investigations of the interaction of boundary layer and shock waves in transonic flow /, by H. W. Liepmann, Jospeh Platt, Jean G. Goppert, sponsor California Institute of Technology, and issuing body United States. Air Force. Air Matériel Command (page images at HathiTrust)
• Calculation of the boundary-layer flow in the windward symmetry plane of a spherically blunted axisymmetric body at angle of attack, including streamline-swallowing effects /, by Arloe W. Mayne, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Analysis of laminar boundary layers on right circular cones at angle of attack, including streamline-swallowing effects /, by Arloe Wesley Mayne, Inc ARO, and Arnold Engineering Development Center (page images at HathiTrust)
• Numerical calculation of the subsonic and transonic turbulent boundary layer on an infinite yawed airfoil /, by John C. Adams, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Method for transition prediction in high-speed boundary layers /, by Thorwald Herbert, Nay Lin, G. K. Stuckert, and Ohio) Wright Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
• Homogeneous boundary layer at an axisymmetric stagnation point with large rates of injection /, by Paul A. Libby, issuing body United States. Air Force. Air Research and Development Command, sponsor Polytechnic Institute of Brooklyn. Aerodynamics Laboratory, and sponsor United States. Wright Air Development Division (page images at HathiTrust)
• Calculation of the boundary-layer growth in a Ludwieg tube /, by James C. Sivells, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• The effect of pressure gradients on transition zone length in hypersonic boundary layers /, by Roger L. Kimmel and Ohio) Wright Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
• A mehod for the prediction of the effects of free-stream disturbances on boundary-layer transition /, by J. A. Benek, M. Dean High, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Solution for the transient one-dimensional heat conduction in an infinite slab /, by John T Miller, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Free flight hypersonic heat transfer and boundary layer transition studies: HTV flights A-40 and A-41 /, by James E. Brunk, Warren N. White, issuing body Aerospace Research Laboratories (U.S.), and sponsor Curtiss-Wright Corporation (page images at HathiTrust)
• A Generalized base-flow analysis with initial boundary-layer and chemistry effects /, by John H. Fox, Inc. sponsor ARO, United States. Air Force. Arnold Air Force Base. sponsor, and United States. Air Force. Systems Command. Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• A study of flow separation in regions of shock wave-boundary layer interaction in hypersonic flow /, by Michael S. Holden, issuing body Aerospace Research Laboratories (U.S.), and sponsor New York University. Aerospace and Energetics Laboratory (page images at HathiTrust)
• Separated and nonseparated turbulent flows about axisymmetric nozzle afterbodies., by John A. Benek, Inc. sponsor ARO, United States. Air Force. Arnold Air Force Base. sponsor, and United States. Air Force. Systems Command. Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• Inlet technology for air launched missiles (U) inlet configuration definition studies., by L. C. Dunsworth, K. E. Woodgrift, Marquardt Company. sponsor, United States. Air Force. Systems Command. sponsor, and Air Force Aero Propulsion Laboratory (U.S.). issuing body (page images at HathiTrust)
• Pressure distribution tests of several sharp leading edge wings, bodies, and body-wing combinations at Mach 5 and 8 /, by R. E. Randall, J. L. Burk, D. R. Bell, Inc. sponsor ARO, United States. Air Force. Air Research and Development Command. sponsor, and Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• An analysis of transonic viscous/inviscid interactions on axisymmetric bodies with solid strings or real plumes /, by Steven F. Yaros, Inc. sponsor ARO, United States. Air Force. Arnold Air Force Base. sponsor, and United States. Air Force. Systems Command. Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• Receptivity in boundary-layer transition to turbulence /, by William S. Saric, issuing body United States. Air Force. Office of Scientific Research, and sponsor Arizona State University. College of Engineering and Applied Sciences (page images at HathiTrust)
• Stability analysis of the compressible, adiabatic similar boundary layer equations (lower branch) /, by G. R. Verma, Wilbur L. Hankey, S. J. Scherr, Air Force Wright Aeronautical Laboratories. issuing agency, and sponsor Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Catalytic surface recombination in boundary-layer profiles of the Falkner-Skan type /, by William J. Rae, United States. Air Force. Office of Scientific Research. issuing body, and Cornell Aeronautical Laboratory. sponsor (page images at HathiTrust)
• Force and pressure tests of two elliptic ogive body shapes at Mach numbers 5, 6, and 8 /, by Jack L. Burk, Inc. sponsor ARO, United States. Air Force. Air Research and Development Command. sponsor, and Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• Preliminary experimental results of the reduction of viscous effects in a low-density supersonic nozle by wall cryopumping /, by W. N. MacDermott, Arnold Engineering Development Center. issuing body, Inc. sponsor ARO, and United States. Air Force. Air Research and Development Command. sponsor (page images at HathiTrust)
• Theoretical and experimental investigation of flow over single and double backward facing steps /, by Douglas Eugene Abbott, S. J. Kline, issuing body United States. Air Force. Office of Scientific Research, and sponsor Stanford University. Department of Mechanical Engineering (page images at HathiTrust)
• Flat-plate boundary-layer transition at hypersonic speeds /, by R. E. Deem, J. S. Murphy, C. R. Erickson, Air Force Flight Dynamics Laboratory (U.S.). sponsor, North American Aviation. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Comments on hypersonic boundary-layer transition /, by Kenneth F. Stetson, sponsor Wright Research and Development Center, sponsor Air Force Flight Dynamics Laboratory (U.S.), and issuing body United States. Air Force. Systems Command (page images at HathiTrust)
• Experimental study of the turbulence production mechanism in boundary layer flows /, by R. E. Falco, Michigan State University. Department of Mechanical Engineering. sponsor, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• Laminar boundary layer along inviscid surface streamlines over inclined axisymmetric bodies in incompressible flow /, by Fred R. Dejarnette, Lee H. Kania, issuing body Air Force Wright Aeronautical Laboratories, sponsor Air Force Flight Dynamics Laboratory (U.S.), and sponsor North Carolina State University. Department of Mechanical and Aerospace Engineering (page images at HathiTrust)
• The compressible turbulent boundary layer with surface mass transfer /, by F. Culick, issuing body United States. Air Force. Office of Scientific Research, and sponsor Massachusetts Institute of Technology. Naval Supersonic Laboratory (page images at HathiTrust)
• The response of the laminar boundary layer to impulsive motions /, by Martin Lewis Rosenzweig, issuing body United States. Air Force. Office of Scientific Research, and sponsor Cornell University (page images at HathiTrust)
• An experimental investigation of the flow structure of the turbulent boundary layer /, by Peter W. Runstadler, William C. Reynolds, S. J. Kline, sponsor Stanford University. Department of Mechanical Engineering, and issuing body United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Nonlinear stability of unsteady viscous flow /, by Alric P. Rothmayer, Iowa State University. sponsor, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• Stability of boundary layers at high supersonic and hypersonic speeds /, by T. Herbert, Ohio State University. Department of Mechanical Engineering. sponsor, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• Calculation of skin friction intwo-dimensional, transonic, turbulent flow /, by T. W. Swafford, Inc. sponsor ARO, United States. Air Force. Arnold Air Force Base. sponsor, and United States. Air Force. Systems Command. Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• Low-density stagnation-point heat transfer in hypersonic air flow /, by Charles F. Wittliff, Merle R. Wilson, issuing body Aerospace Research Laboratories (U.S.), and sponsor Cornell Aeronautical Laboratory (page images at HathiTrust)
• A Study of turbulent boundary layer structure /, by John L. Lumley, Cornell University. sponsor, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• Applications of the aerotherm BLIMP boundary-layer program to nonablating reentry flight conditions /, by Emmett E. Edenfield, Inc. sponsor ARO, United States. Air Force. Arnold Air Force Base. sponsor, and United States. Air Force. Systems Command. Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• Real gas scale effects on hypersonic laminar boundary-layer parameters including effects of entropy-layer swallowing /, by J. C. Adams, E. O. Marchand, A. W. Mayne, W. R. Martindale, United States. Air Force. Arnold Air Force Base. sponsor, United States. Air Force. Systems Command. Arnold Engineering Development Center. issuing body, and Inc. ARO (page images at HathiTrust)
• Investigation of the turbulence producing structures in the boundary layer /, by S. J. Kline, Stanford University. Thermosciences Division. sponsor, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• An experimental study of boattail pressures at high subsonic Mach numbers and high Reynolds numbers /, by John D. Lee, issuing body Aerospace Research Laboratories (U.S.), and sponsor Ohio State University. Research Foundation (page images at HathiTrust)
• DNS studies of transitional hypersonic reacting flows over 3-D hypersonic vehicles /, by Xiaolin Zhong, Los Angeles. Mechanical University of California, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• Fundamental aspects of the structure of supersonic turbulent boundary layers /, by Alexander J. Smits, Princeton University. Department of Mechanical and Aerospace Engineering. sponsor, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• Instability of laminar separation bubbles : causes and effects /, by Tuncer Cebeci, McDonnell Douglas Corporation. Douglas Aircraft Company. sponsor, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• On three-dimensional free-mixing /, by Martin H Bloom, issuing body United States. Air Force. Office of Scientific Research, and sponsor Polytechnic Institute of Brooklyn. Department of Aeronautical Engineering and Applied Mechanics (page images at HathiTrust)
• A Correlation of artifically induced boundary-layer transition data from blunt slender cones at hypersonic speeds /, by A. H. Boudreau, Inc. sponsor ARO, United States. Air Force. Arnold Air Force Base. sponsor, and United States. Air Force. Systems Command. Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• (U) Physical models for supersonic turbulent boundary layer structure /, by Alexander J. Smits, Princeton University. Department of Mechanical and Aerospace Engineering. Gas Dynamics Laboratory. sponsor, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• On the mixing theory of Crocco and Lees and its application to the interaction of shock wave and laminar boundary layer., by Sin-I Cheng, I. D. Chang, issuing body United States. Air Force. Office of Scientific Research, and sponsor Princeton University. Department of Aeronautical Engineering (page images at HathiTrust)
• Structure and control of the wall region in a turbulent boundary layer /, by John Guckenheimer, John L. Lumley, Phillip Holmes, Sidney Leibovich, Cornell University. sponsor, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• Boundary layer transition at supersonic speeds : three dimensional roughness effects (spheres) /, by E. R. Van Driest, C. B. Blumer, United States. Air Force. Office of Scientific Research. issuing body, and North American Aviation. Space and Information Systems Division. sponsor (page images at HathiTrust)
• Separated flow studies /, by Wilbur L. Hankey and issuing body Aerospace Research Laboratories (U.S.) (page images at HathiTrust)
• Direct numerical simulation of flow transition in compressible boundary layer around airfoils /, by Chaoqun Liu, Guohua Xiong, Wei Zhao, Zhining Liu, issuing body United States. Air Force. Office of Scientific Research, and sponsor Louisiana Tech University (page images at HathiTrust)
• Hypersonic viscous flow /, by Hsien K. Cheng, University of Southern California. Department of Aerospace Engineering. sponsor, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• Preliminary report on the fin-wing interaction problem /, by L. Ting, Paul A. Libby, Nassau County General Applied Science Laboratories (Westbury, Wright Air Development Center. issuing body, and United States. Air Force. Air Research and Development Command. sponsor (page images at HathiTrust)
• Shear layer breakdown in compressible flow /, by J. D. A. Walker, Lehigh University. Department of Mechanical Engineering and Mechanics. sponsor, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• Some measurements of a wake-boundary layer interaction /, by R. Eichhorn, T. L. Eddy, United States. Air Force. Aeronautical Research Laboratories. issuing body, and University of Minnesota. sponsor (page images at HathiTrust)
• Research on flow control /, by William C. Reynolds, United States. Air Force. Office of Scientific Research. issuing body, and Stanford University. Department of Mechanical Engineering. sponsor (page images at HathiTrust)
• On the Mach number independence principle for a hypersonic boundary layer /, by N. C. Freeman, Sau-hai Lam, issuing body United States. Air Force. Office of Scientific Research, sponsor United States. Air Force. Air Research and Development Command, and sponsor Princeton University. Department of Aeronautical Engineering (page images at HathiTrust)
• A Final report on three-dimensional structure of transitional boundary layers /, by William S. Saric, Arizona State University. Department of Mechanical and Aerospace Engineering. sponsor, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• Studies of hypersonic boundary layer behavior /, by A. J. Smits, G. L. Brown, R. B. Miles, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)

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