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Laminar boundary layer

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• Boundary layer

• Laminar boundary layer -- Measurement
• Laminar boundary layer -- Research
• Laminar boundary layer -- Speed
• Laminar boundary layer -- Stability
• Laminar boundary layer -- Temperature

• An analytical investigation of laminar film boiling. (Argonne National Laboratory, 1959), by P. W. McFadden, R. J. Grosh, Purdue Research Foundation. Department of Mechanical Engineering, U.S. Atomic Energy Comission, and Argonne National Laboratory (page images at HathiTrust)
• Laminar or turbulent boundary-layer flows of perfect gases or reacting gas mixtures in chemical equilibrium (National Aeronautics and Space Administration ;, 1971), by E. Clay Anderson, Clark H. Lewis, Langley Research Center, and Virginia Polytechnic Institute and State University (page images at HathiTrust)
• Non-equilibrium Arc Tunnel Analysis : theory and analysis (National Aeronautics and Space Administration ;, 1975), by W. L. Bade, Jerrold M. Yos, Lyndon B. Johnson Space Center, and Avco Systems Division (page images at HathiTrust)
• NASA TR R-118 (National Aeronautics and Space Administration :, 1961), by Nathaniel B. Cohen and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TR R-146 (National Aeronautics and Space Administration ;, 1962), by Donald M. Kuehn, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• NASA TR R-95 (National Aeronautics and Space Administration :, 1961), by John Thomas Howe and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-2491 (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)
• Laminar heat-transfer and pressure measurements at a Mach number of 6 on a sharp and blunt 15° half-angle cones at angles of attack up to 90° (National Aeronautics and Space Administration, 1961), by Raul J. Conti, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• NASA TN D-6462 (National Aeronautics and Space Administration :, 1971), by Michael C. Fischer, Dal V. Maddalon, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5791 (National Aeronautics and Space Administration :, 1970), by John Benjamin Anders, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-4829 (National Aeronautics and Space Administration :, 1968), by C. L. W. Edwards, John B. Anders, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Investigation of laminar and turbulent boundary layers interacting with externally generated shock waves (National Aeronautics and Space Administration, 1969), by Earl C. Watson, William C. Rose, and John D. Murphy (page images at HathiTrust; US access only)
• NASA TN D-5516 (National Aeronautics and Space Administration ;, 1969), by Joseph G. Marvin, Yvonne S. Sheaffer, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effects of leading-edge bluntness and ramp deflection angle on laminar boundary-layer separation in hypersonic flow (National Aeronautics and Space Administration ;, 1966), by James C. Townsend and Langley Research Center (page images at HathiTrust)
• Supersonic free-flight measurements of heat transfer and transition on a 10° cone having a low temperature ratio (National Aeronautical and Space Administration, 1961), by Charles F. Merlet, Charles B. Rumsey, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• A real-gas study of low-density wedge-induced laminar separation on a highly cooled blunt flat plate at M [infinity]=12 (National Aeronautics and Space Administration, 1968), by John Benjamin Anders and C. L. W. Edwards (page images at HathiTrust)
• Methods of calculating fundamental solutions of the wave equation, with tables (National Aeronautics and Space Administration, 1959), by William A. Mersman and Ames Research Center (page images at HathiTrust)
• Solutions of the laminar compressible boundary-layer equations with transpiration which are applicable to the stagnation regions of axisymmetric blunt bodies (National Aeronautics and Space Administration, 1959), by John T. Howe, William A. Mersman, and Ames Research Center (page images at HathiTrust)
• NASA TN D-6378 (National Aeronautics and Space Administration ;, 1971), by Enrique J. Klein, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• NASA TN D-7044 (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)
• NASA TN D-6321 (National Aeronautics and Space Administration ;, 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)
• Theoretisch untersuchungen über stationäre potentialströmungen und grenzschichten bei hohen geschwindigkeiten (NACA, 1948), by K. Oswatitsch, K. Wieghardt, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Development of a laminar boundary layer behind a suction point (NACA, 1952), by W. Wuest and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Behavior of the laminar boundary layer for periodically oscillating pressure variation (NACA, 1949), by August Wilhelm Quick, K. Schröder, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Displacement effect of the laminar boundary layer and the pressure drag (NACA, 1951), by Henry Görtler and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• On the turbulent friction layer for rising pressure (NACA, 1951), by K. Wieghardt, W. Tillmann, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• A simple numerical method for the calculation of the laminar boundary layer (National Advisory Committee for Aeronautics, 1952), by K. Schröder and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Resistance of cascade of airfoils in gas stream at subsonic velocity (NACA, 1951), by L. G. Loĭt�si�anskiĭ and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• On motion of fluid in boundary layer near line of intersection of two planes (NACA, 1951), by L. G. Loĭt�si�anskiĭ, V. P. Bolshakov, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Lecture series "boundary layer theory." Part II, turbulent flows (NACA, 1949), by H. Schlichting and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Theoretical investigation of drag reduction in maintaining the laminar boundary layer by suction (NACA, 1947), by A. Ulrich and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• An approximate method for calculation of the laminar boundary layer with suction for bodies of arbitrary shape (NACA, 1949), by H. Schlichting and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• The flow of gases in narrow channels (NACA, 1951), by R. E. H. Rasmussen and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• An approximate method for estimating the incompressible laminar boundary-layer characteristics on a flat plate in slipping flow (NACA, 1949), by Coleman duP. Donaldson, United States. National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Laminar flow about a rotating body of revolution in an axial airstream (NACA, 1956), by H. Schlichting and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Approximate method of integration of laminar boundary layer in incompressible fluid (NACA, 1951), by L. G. Loĭt�si�anskiĭ and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• On the stability of the free laminar boundary layer between parallel streams (National Advisory Committee for Aeronautics, 1949), by Martin Lessen 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 (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)
• The compressible laminar boundary layer with fluid injection (National Advisory Committee for Aeronautics, 1955), by George M. Low and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Study of the pressure rise across shock waves required to separate laminar and turbulent boundary layers (National Advisory Committee for Aeronautics, 1952), by Coleman duP. Donaldson, Roy H. Lange, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Investigation of the stability of the laminar boundary layer in a compressible fluid (National Advisory Committee for Aeronautics ;, 1946), by Lester Lees, C. C. Lin, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Three dimensional flow studies over a spinning cone at angle of attack (Aberdeen Proving Ground, Maryland : USA, Ballistic Research Laboratories, 1974., 1974), by H. A. Dwyer, U.S. Army Ballistic Research Laboratory, and Davis. Department of Mechanical Engineering University of California (page images at HathiTrust)
• Skin friction and heat transfer characteristics of the compressible laminar boundary layer with injection of a light, medium, and heavy gas (White Oak, Maryland : United States Naval Ordnance Laboratory, 1967., 1967), by L. M. Albacete, W. J. Glowacki, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Axisymmetric laminar boundary layers with very large transverse curvature (White Oak, Maryland : United States Naval Ordnance Laboratory, 1967., 1967), by Jay M. Solomon and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• An approximate solution for compressible axisymmetric laminar boundary layers including the effects of transverse curvature (White Oak, Maryland : United States Naval Ordnance Laboratory, 1967., 1967), by Jay M. Solomon, Bernard S. Loeb, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• A digital computer program for making comparative aerodynamic heat transfer and skin friction drag calculations (White Oak, Maryland : United States Naval Ordnance Laboratory, 1967., 1967), by Donald M. Wilson and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• The drag of slightly blunted slender cones (White Oak, Maryland : United States Naval Ordnance Laboratory, 1968., 1968), by W. Carson Lyons, H. S. Brown, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Investigation of substructure heating on cracked ablative heat shields (White Oak, Maryland : United States Naval Ordnance Laboratory, 1969., 1969), by Erhard M. Winkler, M. T. Madden, J. A. Koenig, Richard L. Humphrey, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Supersonic ablation studies with teflon (White Oak, Maryland : United States Naval Ordnance Laboratory, 1969., 1969), by Erhard M. Winkler, J. A. Koenig, Richard L. Humphrey, M. T. Madden, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• On the hypersonic flow past blunted, flat delta wings (White Oak, Maryland : United States Naval Ordnance Laboratory, 1970., 1970), by Arnold Polak and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Calculation of laminar skin friction on a porous plate by a refined integral method (White Oak, Maryland : United States Naval Ordnance Laboratory, 1970., 1970), by Tse-Fou Zien and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Study of boundary-layer flows with pressure gradient and mass transfer by a simple integral method (White Oak, Maryland : United States Naval Ordnance Laboratory, 1971., 1971), by Tse-Fou Zien and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• An experimental investigation of the laminar boundary layer on a spinning ogive cylinder in supersonic flow (White Oak, Maryland : United States Naval Ordnance Laboratory, 1972., 1972), by William C. Ragsdale, Robert G. Ball, Michael A. Brown, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• A numerical analysis of CO₂ laser radiation absorption in SF₆ -air laminar boundary layers (White Oak, Maryland : United States Naval Ordnance Laboratory, 1973., 1973), by John D. Anderson and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• The characteristics of a laminar boundary layer on a spinning tangent ogive cylinder at angle of attack (Albuquerque, New Mexico : Sandia Laboratories, 1972., 1972), by H. R. Vaughn, Oscar L. George, Sandia Corporation, and U.S. Atomic Energy Commission (page images at HathiTrust)
• A magnus theory for bodies of revolution (Albuquerque, New Mexico : Sandia Laboratories, Aeroballistics Division, 1973., 1973), by H. R. Vaughn, G. E. Reis, Sandia Corporation, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Approximate analysis of heat transfer in transpired boundary layers at limiting Prandtl numbers (Silver Spring, Maryland : Naval Ordnance Laboratory, White Oak, 1974., 1974), by Tse-Fou Zien and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Research on rotating stall in axial flow compressors. Part II, On the separation of the unsteady laminar boundary layer (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1959., 1959), by R. A. Hartunian, F. K. Moore, Wright Air Development Center, United States. Air Force. Air Research and Development Command, and Armed Services Technical Information Agency (U.S.) (page images at HathiTrust)
• Experiments on laminar separation from a moving wall (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1959., 1959), by Robert J. Vidal, Wright Air Development Center, and United States. Air Force. Air Research and Development Command (page images at HathiTrust)
• Summary of laminar boundary layer control research (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1964., 1964), by Northrop Corporation. Boundary Layer Research Section and United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• Study of the effect of free-stream turbulence upon disturbances in the pre-transitional laminar boundary layer (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1982., 1982), by James M. Kendall, Air Force Wright Aeronautical Laboratories, Air Force Flight Dynamics Laboratory (U.S.), and Jet Propulsion Laboratory (U.S.) (page images at HathiTrust)
• Inhibition of flow separation at high speed. Volume 2, Calculation of nonadiabatic laminar boundary layers (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1969., 1969), by Frederick K. Goodwin, Larry L. Lynes, Jack Norman Nielsen, Air Force Flight Dynamics Laboratory (U.S.), and Nielsen Engineering & Research (page images at HathiTrust)
• Inhibition of flow separation at high speed. Volume 3, Experimental results for laminar boundary layers (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1969., 1969), by Jack Norman Nielsen, Frederick K. Goodwin, Larry L. Lynes, Air Force Flight Dynamics Laboratory (U.S.), and Nielsen Engineering & Research (page images at HathiTrust)
• Mark IV supersonic-hypsersonic arbitrary-body program modifications and computer graphics. Volume II, Computer graphics (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1980., 1980), by S. Taylor, Air Force Flight Dynamics Laboratory (U.S.), Air Force Wright Aeronautical Laboratories, and inc Science Applications (page images at HathiTrust)
• A study of aerodynamic control in stalled flight long laminar separation bubble analysis (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1985., 1985), by Frank A. Dvorak, D. H. Choi, Air Force Flight Dynamics Laboratory (U.S.), Air Force Wright Aeronautical Laboratories, and Inc Analytical Methods (page images at HathiTrust)
• Two-dimensional supersonic nonadiabatic flow and axisymmetric supersonic adiabatic and nonadiabatic flows (Wright-Patterson Air Force Base, Ohio : b Air Force Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, 1966., 1966), by Jack Norman Nielsen, Frederick K. Goodwin, Larry L. Lynes, Wright-Patterson Air Force Base (Ohio), Itek Corporation, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Mark IV supersonic-hypsersonic arbitrary-body program modifications and computer graphics. Volume I, Surface streamline tracing (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1981., 1981), by S. Taylor, Air Force Flight Dynamics Laboratory (U.S.), Air Force Wright Aeronautical Laboratories, and inc Science Applications (page images at HathiTrust)
• Condensation heat transfer. Part II, Solution of the film condensation problem by successive analytical iteration (Wright-Patterson Air Force Base, Ohio : Directorate of Materials and Processes, Aeronautical Systems Division, Air Force Systems Command, 1963., 1963), by Jon H. Lee and United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• Inhibition of flow separation at high speed. Volume IV, Calculation of nonadiabatic laminar boundary layers on conical compression surfaces (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1969., 1969), by Frederick K. Goodwin, Larry L. Lynes, Air Force Flight Dynamics Laboratory (U.S.), and Nielsen Engineering & Research (page images at HathiTrust)
• An experimental investigation of the surface pressure and the laminar boundary layer on a blunt flat plate in hypersonic flow (Wright-Patterson Air Force Base, Ohio : Fluid Dynamics Laboratory, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1963., 1963), by G. M. Gregorek, J. D. Lee, Theodore C. Nark, United States. Air Force. Systems Command. Aeronautical Systems Division, and Ohio State University (page images at HathiTrust)
• Supersonic flow about general three-dimensional blunt bodies. Volume II, Heat transfer due to the interaction between a swept planar shock wave and a Laminar boundary layer (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1962., 1962), by A. Martellucci, Paul A. Libby, Nassau County General Applied Science Laboratories (Westbury, and United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)
• Interaction between air flow and airborne sound in a duct (Wright-Patterson Air Force Base, Ohio : Aerospace Medical Research Laboratories, Aerospace Medical Division, Air Force Systems Command, United States Air Force, 1965., 1965), by Fridolin P. Mechel, W. M. Schilz, P. A. Mertens, and Aerospace Medical Research Laboratories (U.S.) (page images at HathiTrust)
• Heating in regions of interfering flow fields (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1967., 1967), by C. E. Gulbran, S. L. Strack, D. S. Miller, E. Redeker, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Hall effects in a laminar boundary layer of the Hartmann type (Everett, Massachusetts : Avco Everett Research Laboratory, 1959., 1959), by James A. Fay, United States. Air Force. Air Research and Development Command, and Avco-Everett Research Laboratory (page images at HathiTrust)
• Real-gas laminar boundary layers in hypervelocity nozzles (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1965., 1965), by Willard E. Summers, Inc ARO, United States. Air Force. Arnold Air Force Base, and Arnold Engineering Development Center (page images at HathiTrust)
• Understanding and predicting shockwave and turbulent boundary layer interactions (Arlington, Virginia. : Air Force Office of Scientific Research, 2009., 2009), by M. Pino Martin, Alexander J. Smits, Princeton University. Department of Mechanical and Aerospace Engineering, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Real gas scale effects on hypersonic laminar boundary-layer parameters including effects of entropy-layer swallowing (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1975., 1975), by J. C. Adams, E. O. Marchand, A. W. Mayne, W. R. Martindale, United States. Air Force. Arnold Air Force Base, United States. Air Force. Systems Command. Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
• Investigation of flow separation on a two-dimensional flat plate haveing a variable-san trailing-edge flap at M [free stream] = 3 and 5 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1964., 1964), by S. R. Pate, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Combined effects of viscous interaction and ideal source flow on pressure and heat-transfer distributions over hemisphere cylinders at M infinity is approximately 18 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Von Kármán Gas Dynamics Facility, Air Force Systems Command, United States Air Force, 1965., 1965), by R. H. Eaves, Clark H. Lewis, Inc ARO, United States. Air Force. Arnold Air Force Base, and Arnold Engineering Development Center (page images at HathiTrust)
• Laminar boundary layer along inviscid surface streamlines over inclined axisymmetric bodies in incompressible flow (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1988., 1988), by Fred R. Dejarnette, Lee H. Kania, Air Force Wright Aeronautical Laboratories, Air Force Flight Dynamics Laboratory (U.S.), and North Carolina State University. Department of Mechanical and Aerospace Engineering (page images at HathiTrust)
• Investigation of drag reduction by boundary layer suction on a 50-deg swept tapered wing at M (free-stream) = 2.5 to 4 (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1964., 1964), by S. R. Pate, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Some heat transfer problems in hypersonic flow ([Brooklyn, New York] : Polytechnic Institute of Brooklyn, Department of Aeronautical Engineering and Applied Mechanics, [1959], 1959), by Antonio Ferri, United States. Air Force. Air Research and Development Command, and Polytechnic Institute of Brooklyn (page images at HathiTrust)
• A computer study of hypersonic laminar boundary-layer/shock-wave interaction using the time-dependent compressible Navier-Stokes equations (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Von Darman Gas Dynamics Facility, Air Force Systems Command, United States Air Force, 1976., 1976), by B. K. Hodge, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
• Laminar boundary-layer separation on flared bodies at supersonic and hypersonic speeds (Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1965., 1965), by J. Don Gray, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Flow transition in gas turbine airfoil boundary layers: fundamentals and empiricisms (Wright-Patterson Air Force Base, Ohio : Aero Propulsion Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1985., 1985), by Gregory S. West, Lit S. Han, Air Force Wright Aeronautical Laboratories, and University of Dayton. Research Institute (page images at HathiTrust)
• The response of the laminar boundary layer to impulsive motions ([Washington, D.C.] : [United States Air Force, Office of Scientific Research], [1959], 1959), by Martin Lewis Rosenzweig, United States. Air Force. Office of Scientific Research, and Cornell University (page images at HathiTrust)
• Analytical, numerical, and experimental results on turbulent boundary layers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1976., 1976), by David L. Whitfield, Arnold Engineering Development Center, United States. Air Force. Systems Command, and Inc ARO (page images at HathiTrust)
• Wave evolution and laminar-turbulent transition in fully 3D supersonic flows (Bolling Air Force Base, D.C. : Air Force Office of Scientific Research, United States Air Force, 1996., 1996), by T. Herbert and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Three-dimensional laminar boundary-layer analysis of upwash patterns and entrained vortex formation on sharp cones at angle of attack (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1971., 1971), by John C. Adams, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Point heat sources and the temperature-vorticity analogy in compressible boundary layers (Washington, D.C. : Air Force Office of Scientific Research, United States Air Force, 1962., 1962), by W. J. McCroskey, United States. Air Force. Office of Scientific Research, and Princeton University. Department of Aeronautical Engineering (page images at HathiTrust)
• Stagnation point boundary layer with large wall-to-freestream enthalpy ratio (Los Angeles, California : Space and Missile Systems Organization, Los Angeles Air Force Station, Air Force Systems Command, United States Air Force, 1967., 1967), by Harold Mirels, William E Welsh, United States. Air Force. Systems Command, Space and Missile Systems Organization (U.S.), and Aerospace Corporation (page images at HathiTrust)
• An experimental study of the receptivity of a compressible laminar boundary layer (Arlington, Virginia. : Air Force Office of Scientific Research, 2008., 2008), by Garry L. Brown, Hadassah Naiman, Princeton University, and United States. Air Force. Office of Scientific Research (page images at HathiTrust)

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