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Filed under: Wakes (Aerodynamics) Wind-tunnel measurements of dispersion and turbulence in the wakes of nuclear reactor plants : final report, January 1975-December 1979 (The Commission :, 1980), by Robert N. Meroney, K. M. Kothari, J. A. Peterka, and U.S. Nuclear Regulatory Commission. Division of Reactor Safety Research (page images at HathiTrust) Database of ground-based anemometer measurements of wake vortices at Kennedy Airport (Federal Aviation Administration, Office of Communications, Navigation and Surveillance Systems ;, 1997), by David Burnham, Steve Abramson, Inc Scientific & Engineering Solutions, John A. Volpe National Transportation Systems Center (U.S.), and Navigation United States. Federal Aviation Administration. Office of Communications (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 (Air Force Aero Propulsion Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1979), by Arun K. Sehra (page images at HathiTrust) Measurement of velocity and vorticity fields in the wake of an airfoil in periodic pitching motion (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1987), by Earl R. Booth and Langley Research Center (page images at HathiTrust) Rotor induced-inflow-ratio measurements and CAMRAD calculations (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Danny R. Hoad and United States. Army Aerostructures Directorate (page images at HathiTrust) Wake geometry effects on rotor blade-vortex interaction noise directivity (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by R. M. Martin and Langley Research Center (page images at HathiTrust) Acoustic and aerodynamic study of a pusher-propeller aircraft model (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Paul T. Soderman, W. Clifton Horne, and Ames Research Center (page images at HathiTrust) A cockpit-display concept for executing a multiple glide-slope approach for wake-vortex avoidance (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Terence S. Abbott and Langley Research Center (page images at HathiTrust) Analysis of noise measured from a propeller in a wake (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by P. J. W. Block and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust) An exploratory investigation of a wake disruption technique for studying wake reestablishment time (National Aeronautics and Space Administration ;, 1974), by Louis E. Clark, Robert A. Jones, and Langley Research Center (page images at HathiTrust) Directivity and trends of noise generated by a propeller in a wake (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1986), by P. J. W. Block, Garl L. Gentry, and Langley Research Center (page images at HathiTrust) Experimental evaluation of a flat wake theory for predicting rotor inflow-wake velocities (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by John C. Wilson and United States. Army. Aeroflightdynamics Directorate (page images at HathiTrust) Effect of rotor wake on aerodynamic characteristics of a 1/6-scale model of the rotor systems research aircraft (National Aeronautics and Space Administration ;, 1977), by Raymond E. Mineck and United States National Aeronautics and Space Administration (page images at HathiTrust) Wake-shock interaction at a Mach number of 6 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Michael J. Walsh, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust) A distributed vortex method for computing the vortex field of a missile (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Raymond L. Barger and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust) Effect of pylon wake with and without pylon blowing on propeller thrust (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Garl L. Gentry, Mohammad Ali Takallu, Earl R. Booth, and Langley Research Center (page images at HathiTrust) Effect of inlet ingestion of a wing tip vortex on compressor face flow and turbojet stall margin (National Aeronautics and Space Administration ;, 1975), by Glenn A. Mitchell and Lewis Research Center (page images at HathiTrust) Mean-flow and turbulence measurements in the vicinity of the trailing edge of an NACA 63₁-012 airfoil (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by James C. Yu, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust) A full potential flow analysis with realistic wake influence for helicopter rotor airload prediction (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1987), by T. Alan Egolf and S. Patrick Sparks (page images at HathiTrust) Development and application of a method for predicting rotor free wake positions and resulting rotor blade air loads. Volume 1, Model and results (National Aeronautics and Space Administration ;, 1971), by S. G. Sadler, Langley Research Center, and Rochester Applied Sciences Associates (page images at HathiTrust) Development and application of a method for predicting rotor free wake positions and resulting rotor blade air loads. Volume 2, Program listings (National Aeronautics and Space Administration ;, 1971), by S. G. Sadler, Langley Research Center, and Rochester Applied Sciences Associates (page images at HathiTrust) Exploratory investigation of sound pressure level in the wake of an oscillating airfoil in the vicinity of stall (National Aeronautics and Space Administration ;, 1972), by Robin B. Gray, G. A. Pierce, Langley Research Center, and Georgia Institute of Technology (page images at HathiTrust) Theoretical and experimental study of a new method for prediction of profile drag of airfoil sections (National Aeronautics and Space Administration ;, 1975), by Suresh H. Goradia, D. G. Lilley, Langley Research Center, and Lockheed-Georgia Company (page images at HathiTrust) The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil : drag euqations (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1989), by Cuyler W. Brooks, William D. Harvey, and Charles D. Harris (page images at HathiTrust) Wind tunnel measurements in the wakes of structures (National Aeronautics and Space Administration ;, 1977), by H. G. C. Woo, J. E. Cermak, J. A. Peterka, George C. Marshall Space Flight Center, and Colorado State University (page images at HathiTrust) A field study of wind over a simulated block building (National Aeronautics and Space Administration ;, 1977), by Walter Frost, Alireza M Shahabi, George C. Marshall Space Flight Center, and University of Tennessee (Knoxville campus). Space Institute (page images at HathiTrust) Wake analysis for supersonic decelerator applications (National Aeronautics and Space Administration ;, 1970), by Richard A. Lau, Langley Research Center, and Goodyear Aerospace Corporation (page images at HathiTrust) Evaluation of effectiveness of various devices for attenuation of trailing vortices based on model tests in a large towing basin (National Aeronautics and Space Administration ;, 1973), by Karl L. Kirkman, Alex Goodman, Clinton E. Brown, Langley Research Center, and inc Hydronautics (page images at HathiTrust) Effect of lateral spacing on wake characteristics of buildings (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Earl Logan, David S. Barber, George C. Marshall Space Flight Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust) Wind tunnel measurements of three-dimensional wakes of buildings (National Aeronautics and Space Administration, Scientific and Technical Information Office;, 1982), by Earl Logan, Shu Ho Lin, Arizona State University, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and George C. Marshall Space Flight Center (page images at HathiTrust) An experimental investigation of vortex stability, tip shapes, compressibility, and noise for hovering model rotors (National Aeronautics and Space Administration ;, 1973), by James L. Tangler, Stan J. Miley, Robert M. Wohlfeld, Langley Research Center, and Bell Helicopter Company (page images at HathiTrust) Wakes, their structure and influence upon aerodynamic decelerators (National Aeronautics and Space Administration, 1967), by Igor M. Jaremenko (page images at HathiTrust) Aircraft propeller induced structure-borne noise (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1989), by James F. Unruh, Langley Research Center, and Southwest Research Institute (page images at HathiTrust) NASA TN D-5819 (National Aeronautics and Space Administration :, 1970), by Harry H. Heyson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) Jet-wake effect of a high-bypass engine on wing-nacelle interference drag of a subsonic transport airplane (National Aeronautics and Space Administration; [for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], 1970), by James C. Patterson and Stuart G. Flechner (page images at HathiTrust; US access only) Vortex shedding from a blunt trailing edge with equal and unequal external mean velocities (National Aeronautics and Space Administration ;, 1975), by Paul F. Brinich, Marvin E. Goldstein, Donald R. Boldman, and Lewis Research Center (page images at HathiTrust) Low-speed wind-tunnel investigation of span load alteration, forward-located spoilers, and splines as trailing-vortex-hazard alleviation devices on a transport aircraft model (National Aeronautics and Space Administration ;, 1975), by Delwin R. Croom, R. Earl Dunham, and Langley Research Center (page images at HathiTrust) Characteristics of wake vortex generated by a Boeing 727 jet transport during two-segment and normal ILS approach flight paths (U.S. National Aeronautics and Space Administration ;, 1976), by R. L. Kurkowski, L. J. Garodz, Mark R. Barber, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) NASA TN D-5634 (National Aeronautics and Space Administration ;, 1970), by Heinz G. Struck, George C. Marshall Space Flight Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) NASA TN D-5365 (National Aeronautics and Space Administration ;, 1969), by James F. Campbell, Josephine W. Grow, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) NASA TN D-6655 (National Aeronautics and Space Administration :, 1972), by William H. Andrews, Richard R. Larson, Glenn H. Robinson, Flight Research Center (U.S.), and United States National Aeronautics and Space Administration (page images at HathiTrust) A wind-tunnel investigation of parameters affecting helicopter directional control at low speeds in ground effect (National Aeronautics and Space Administration ;, 1974), by William T. Yeager, Wayne R. Mantay, Warren H. Young, and Langley Research Center (page images at HathiTrust) Investigation of variation in base pressure over the Reynolds number range in which wake transition occurs for two-dimensional bodies at Mach numbers from 1.95 to 2.92 (National Aeronautics and Space Administration, 1959), by Vernon Van Hise and Langley Research Center (page images at HathiTrust) Evaluation of flow properties behind 120-̊ and 140-̊included-angle cones and a Viking '75 entry vehicle at Mach numbers from 1.60 to 3.95 (National Aeronautics and Space Administration ;, 1973), by Clarence A. Brown, James F. Campbell, and Langley Research Center (page images at HathiTrust) Mixing of wakes in a turbulent shear flow (National Aeronautics and Space Administration, 1959), by Salamon Eskinazi and Syracuse University (page images at HathiTrust) Aircraft vortex wakes in relation to terminal operations (National Aeronautics and Space Administration, 1963), by Joseph W. Wetmore, John P. Reeder, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only) Further analysis of broadband noise measurements for a rotating blade operating with and without its shed wake blown downstream (National Aeronautics and Space Administration ;, 1974), by James Scheiman and Langley Research Center (page images at HathiTrust) Dispersion of turbojet engine exhaust in flight (National Aeronautics and Space Administration ;, 1973), by James D. Holdeman and Lewis Research Center (page images at HathiTrust) NASA TN D-6281 (National Aeronautics and Space Administration ;, 1971), by William D. Deveikis, James Wayne Sawyer, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) A flight investigation of the trailing vortices generated by a jumbo jet transport (National Aeronautics and Space Administration ;, 1973), by Harry A. Verstynen, R. Earl Dunham, and Langley Research Center (page images at HathiTrust) Measurements of surface-pressure and wake-flow fluctations in the flow field of a Whitcomb supercritical airfoil (National Aeronautics and Space Administration ;, 1977), by Frederick W. Roos, Dennis W. Riddle, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) Low-speed wind-tunnel investigation of flight spoilers as trailing-vortex-alleviation devices on a medium-range wide-body tri-jet airplane model (National Aeronautics and Space Administration :, 1976), by Delwin R. Croom, Geoffrey M. Williams, Raymond D. Vogler, and United States National Aeronautics and Space Administration (page images at HathiTrust) Low-speed wind-tunnel investigation of flight spoilers as trailing-vortex-alleviation devices on an extended-range wide-body tri-jet airplane model (National Aeronautics and Space Administration ;, 1976), by Delwin R. Croom, John A. Thelander, Raymond D. Vogler, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust) NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1944), by Blake W. Corson, Mason F. Miller, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust) NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1945), by Myron J. Block, S. Katzoff, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust) Aircraft vortex wake decay near the ground (U.S. Department of Transportation, Federal Aviation Administration, Systems Research and Development Service ;, 1977), by S. J. Barker, J. B. Mullen, P. B. S. Lissaman, I. Tombach, United States. Federal Aviation Administration. Systems Research and Development Service, Poseidon Research, and AeroVironment Inc (page images at HathiTrust) Aircraft wake vortex takeoff tests at O'Hare International Airport (Office of Research and Development Service, U.S. Department of Transportation, Federal Aviation Administration ;, 1994), by Joseph Yarmus, John A. Volpe National Transportation Systems Center (U.S.), and United States. Federal Aviation Administration. Office of Research and Development Service (page images at HathiTrust) Wake vortex separation standards : analysis methods. (U.S. Department of Transportation, Federal Aviation Administration, Office of Communications, Navigation and Surveillance Systems ;, 1997), by J. N. Hallock, David C. Burnham, Navigation and Surveillance Systems United States. Federal Aviation Administration. Office of Communications, John A. Volpe National Transportation Systems Center (U.S.), and United States. Department of Transportation. Research and Special Programs Administration (page images at HathiTrust) Downwash characteristics and vortex-sheet shape behind a 63 degree swept-back wing-fuselage combination at a Reynolds number of 6,100,000 (National Advisory Committee for Aeronautics, 1952), by William H. Tolhurst and Ames Research Center (page images at HathiTrust) Heat transfer on an afterbody immersed in the separated wake of a hemisphere (National Advisory Committee for Aeronautics, 1958), by Helmer V. Nielsen and Ames Research Center (page images at HathiTrust) Airplane motions and loads induced by flying through the flow field generated by an airplane at low supersonic speeds (National Advisory Committee for Aeronautics, 1957), by Gareth H. Jordan, Stanley P. Butchart, Earl R. Keener, Flight Research Center (U.S.), United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust) An analytical study of the effect of airplane wake on the lateral dispersion of aerial sprays (National Advisory Committee for Aeronautics, 1953), by Wilmer H. Reed and United States National Advisory Committee for Aeronautics (page images at HathiTrust) Observations on the flows past blunt bodies at transonic speeds (National Aeronautics and Space Administration, 1960), by Philip E. Everhart, Walter F. Lindsey, and United States National Aeronautics and Space Administration (page images at HathiTrust) NACA Wartime Reports. Series L. (National Advisory Committee for Aeronautics, 1945), by Myron J. Block, S. Katzoff, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust) Safety issues related to wake vortex encounters during visual approach to landing (National Transportation Safety Board ;, 1994), by United States. National Transportation Safety Board (page images at HathiTrust) Free molecular solutions for the satellite wake and the orifice (Purdue University, 1964), by Winthrop Adolph Gustafson and R. E. Kiel (page images at HathiTrust) Growth of the turbulent wake behind a supersonic sphere (Aberdeen, Maryland : Aberdeen Proving Ground, 1962., 1962), by C. H. Murphy, Elizabeth R. Dickinson, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust) Growth of the turbulent inner wake behind large spheres at supersonic velocities (Aberdeen, Maryland : Aberdeen Proving Ground, 1964., 1964), by Walter F. Braun, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust) Experiments on wake optical properties (Aberdeen, Maryland : Aberdeen Proving Ground, 1975., 1975), by George D. Kahl, Donald D. Shear, David B. Sleator, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust) Preliminary radiation measurements of high speed flows over cylinders and spheres (Aberdeen Proving Ground, Maryland : U.S. Army Materiel Command, Ballistic Research Laboratories, 1966., 1966), by Wallace H. Clay and U.S. Army Ballistic Research Laboratory (page images at HathiTrust) Prediction of normal force, pitching moment, and yawing force on bodies of revolution at angles of attack up to 50 degrees using a concentrated vortex flow-field model (White Oak, Maryland : United States Naval Ordnance Laboratory, 1973., 1973), by Andrew B. Wardlaw, W. J. Glowacki, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust) Aircraft wake vortices : an assessment of the current situation (Federal Aviation Administration, Research and Development Service ;, 1990), by T. E. Sullivan, J. N. Hallock, John A. Volpe National Transportation Systems Center (U.S.), and United States. Federal Aviation Administration. Research and Development Service (page images at HathiTrust) Flight test investigation of rotorcraft wake vortices in forward flight (FAA Technical Center ;, 1996), by Stephen A. Teager and Federal Aviation Administration Technical Center (U.S.) (page images at HathiTrust) Behavior of extraction parachutes in the wake of a powered airplane model (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1968., 1968), by H. G. Heinrich, G. D. Hulcher, Air Force Flight Dynamics Laboratory (U.S.), and University of Minnesota. Department of Aerospace Engineering and Mechanics (page images at HathiTrust) Velocity distribution in the wake of bodies of revolution based on drag coefficient (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, United States Air Force, 1963., 1963), by Helmut G. Heinrich, Donald J. Eckstrom, Wright-Patterson Air Force Base (Ohio), United States. Air Force. Systems Command. Aeronautical Systems Division, and University of Minnesota. Department of Aerospace Engineering and Mechanics (page images at HathiTrust) Shroud tests of pressure and heat transfer over short afterbodies with separated wakes (Wright-Patterson Air Force Base, Ohio. Wright Air Development Center, Air Research and Development Command, United States Air Force, 1958., 1958), by Martin H. Bloom, Adrian Pallone, United States. Air Force. Air Research and Development Command, Wright Air Development Center, and Polytechnic Institute of Brooklyn. Department of Aeronautical Engineering and Applied Mechanics (page images at HathiTrust) Pressure distribution in the wake of two bodies revolution at transonic and supersonic speeds (Wright-Patterson Air Force Base, Ohio : Aeronautical Systems Division, Air Force Systems Command, United States Air Force, 1963., 1963), by Helmut G. Heinrich, R. Sheldon Hess, University of Minnesota. Department of Aerospace Engineering and Mechanics, Wright-Patterson Air Force Base (Ohio), and United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust) Radar cross section of underdense turbulent wakes (Air Force Cambridge Research Laboratories, Air Force System Command, United States Air Force, 1973), by Ronald L. Fante and Air Force Cambridge Research Laboratories (U.S.) (page images at HathiTrust) Response of aircraft encountering aircraft wake turbulence (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1974., 1974), by Robert C. Nelson and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust) A method for calculating helicopter vortex paths and wake velocities (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1970., 1970), by E. S. Levinsky, T. Strand, Air Vehicle Corporation, Air Force Flight Dynamics Laboratory (U.S.), and Wright-Patterson Air Force Base (Ohio) (page images at HathiTrust) Stability of compressible wake and jet flows (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1983, 1983), by G. R. Verma, Wilbur L. Hankey, S. J. Scherr, Air Force Wright Aeronautical Laboratories, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust) Effect of suction on the wake structure of a three-dimensional turret (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1983, 1983), by S. C. Purohit, Air Force Wright Aeronautical Laboratories, Air Force Flight Dynamics Laboratory (U.S.), and University of Dayton. Research Institute (page images at HathiTrust) Analytical nodel of supersonic, turbulent, near-wake flows (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Engine Test Facility, Air Force Systems Command, United States Air Force, 1976., 1976), by C. E. Peters, W. J. Phares, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust) Analytical study of ventilated wind tunnel boundary interference on V/STOL models including wake curvature and decay effects (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1974., 1974), by E. M. Kraft, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust) Some measurements of a wake-boundary layer interaction (Wright-Patterson Air Force Base, Ohio : Aeronautical Research Laboratories, Air Force Research Division, Air Research and Development Command, United States Air Force, 1960., 1960), by R. Eichhorn, T. L. Eddy, United States. Air Force. Aeronautical Research Laboratories, and University of Minnesota (page images at HathiTrust) On Three-dimensional swirling wakes (Washington, D.C. : Air Force Office of Scientific Research, United States Air Force, 1962., 1962), by Martin H. Steiger, United States. Air Force. Office of Scientific Research, and Polytechnic Institute of Brooklyn. Department of Aeronautical Engineering and Applied Mechanics (page images at HathiTrust) Supersonic flow measurements in the body vortex wake of an ogive nose cylinder (Eglin Air Force Base, Florida : Air Force Armament Laboratory, Armament Development and Test Center, Air Force Systems Command, United States Air Force, 1978., 1978), by William L. Oberkampf, T. J. Bartel, United States. Air Force. Systems Command, and Air Force Armament Laboratory (page images at HathiTrust) Finite-difference solution of the laminar supersonic near wake : a posteriori error study and physical discussion (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, United States Air Force, 1974., 1974), by Bruce B. Ross, Sin-I Cheng, Aerospace Research Laboratories (U.S.), and Princeton University. Gas Dynamics Laboratory (page images at HathiTrust) Active control of wake/blade-row interaction noise through the use of blade surface actuators (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993), by Kenneth A. Kousen, Joseph M. Verdon, United States. National Aeronautics and Space Administration. Scientific and Technical Information Program, and Lewis Research Center (page images at HathiTrust) Computation of turbulent boundary layers employing the defect wall-function method (National Aeronautics and Space Administration, Langley Research Center, 1994), by Douglas L. Brown and Langley Research Center (page images at HathiTrust) NACA wartime reports (Langley Memorial Aeronautical Laboratory, 1945), by Donald D. Baals, Mary J. Mourhess, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
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