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Diffusers -- Design and construction

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• Diffusers
• Design and construction

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• Subsonic diffuser designs for interceptor applications. Volume II (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, 1973., 1973), by E. David Spong, R. W. Williams, J. V. Rejeske, P. M. Doane, Air Force Flight Dynamics Laboratory (U.S.), and McDonnell Aircraft Company (page images at HathiTrust)

• Design and experimental performance of short curved wall diffusers with axial symmetry utilizing slot suction (National Aeronautics and Space Administration ;, 1973), by Tah-teh Yang, Carl D. Nelson, William G. Hudson, Lewis Research Center, and Clemson University (page images at HathiTrust)

Items below (if any) are from related and broader terms.

• Report relating to length of outfall and types of diffusers for the ocean outfall for effluent disposal (Hyperion Engineers, 1956), by Koebig & Koebig, Mann Daniel, Holmes & Narver, and Hyperion Engineers (page images at HathiTrust)
• Effect of diffuser bleed on performance of an annular swirl can combustor (National Aeronautics and Space Administration ;, 1974), by Albert J. Juhasz and Lewis Research Center (page images at HathiTrust)
• Performance of high-area-ratio annular dump diffuser using suction-stabilized-vortex flow control (National Aeronautics and Space Administration ;, 1977), by Albert J. Juhasz, John M. Smith, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-6435 (National Aeronautics and Space Administration ;, 1971), by Albert J. Juhasz, J. D. Holdeman, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Static tests of an external flow jet augmented flap test bed with a turbojet engine (National Aeronautics and Space Administration :, 1959), by Marvin P. Fink and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Preliminary investigation of supersonic diffusers (Langley Memorial Aeronautical Laboratory, 1945), by Arthur Kantrowitz, Coleman duP. Donaldson, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99. [Part] 2, Isentropic-spike all-external compression inlet (National Advisory Committee for Aeronautics, 1951), by L. J. Obery, G. W. Englert, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Jet diffuser for simulating ram conditions on a turbojet-engine static test stand (National Advisory Committee for Aeronautics, 1947), by Robert H. Essig, David S. Gabriel, H. R. Bohanon, United States National Advisory Committee for Aeronautics, and Aircraft Engine Research Laboratory (page images at HathiTrust)
• Preliminary attempts at isothermal compression of a supersonic air stream (National Advisory Committee for Aeronautics, 1956), by E. Perchonok, F. Wilcox, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• An analog study of a shock-position diffuser control on a supersonic turbojet engine (National Advisory Committee for Aeronautics, 1956), by David Novik, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• An inlet design concept to reduce flow distortion at angle of attack (National Advisory Committee for Aeronautics, 1957), by Carl F. Schueller, Leonard E. Stitt, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Preliminary investigation of shield to improve angle-of-attack performance of nacelle-type inlet (National Advisory Committee for Aeronautics, 1957), by Milton A. Beheim, Thomas G. Piercy, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Spectrum of turbulence in a contracting stream (National Advisory Committee for Aeronautics, 1952), by Herbert Spencer Ribner, Maurice Tucker, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• NACA Wartime Reports. Series E. (National Advisory Committee for Aeronautics, 1945), by J. Austin King, Harold Klein, Aircraft Engine Research Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• NACA Wartime Reports. Series E. (National Advisory Committee for Aeronautics, 1946), by Edmund J. Baas, Paul D. Dugan, Aircraft Engine Research Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• The mixing characteristics of submerged multiple-port diffusers for heated effluents in open channel flow (University of Iowa, Iowa Institute of Hydraulic Research, 1973), by John W. Argue, William W. Sayre, Iowa Institute of Hydraulic Research, Commonwealth Edison Company, and United States. Office of Water Resources Research (page images at HathiTrust; US access only)
• Light shaping diffusers for improved visual inpsection of aircraft (Federal Aviation Administration, Office of Aviation Research, 1996), by Richard N. Shagam, Sandia National Laboratories. Aging Aircraft NDI Validation center, and United States. Office of Aviation Research (page images at HathiTrust)
• NOL mach 18 hypervelocity research tunnel (Defense Technical Information Center, 1974), by Ray H. Cornett, Alton G Keel, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Test operation of a prototype, solid-state, helium purification cell (Los Alamos, New Mexico : Los Alamos Scientific Laboratory of the University of California, 1968., 1968), by R. A. Clark, C. R. Winkelman, B. J. Melton, Los Alamos Scientific Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Investigation of subsonic duct distortion (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1969., 1969), by C. J. MacMiller, North American Rockwell Corporation, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)
• Study of compressible flow through a rectangular-to-semiannular transition duct (National Aeronautics and Space Administration, Scientific and Technical Information Program, 1995), by Jeffry Foster and Lewis Research Center (page images at HathiTrust)

• An experimental investigation of two large annular diffusers with swirling and distorted inflow (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1980), by United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, William T. Eckert, and Aeromechanics Laboratory (page images at HathiTrust)
• Distortion in a full-scale bicone inlet with internal focused compression and 45 percent internal contraction (National Aeronautics and Space Administration ;, 1974), by Joseph F. Wasserbauer, Robert J. Shaw, Harvey E. Neumann, and Lewis Research Center (page images at HathiTrust)
• Effect of inducer inlet and diffuser throat areas on performance of a low pressure ratio sweptback centrifugal compressor (National Aeronautics and Space Administration ;, 1975), by Hugh A. Klassen and Lewis Research Center (page images at HathiTrust)
• Comparison of experimental and theoretical boundary-layer separation for inlets at incidence angle at low-speed conditions (National Aeronautics and Space Administration ;, 1975), by E. John Felderman, Lewis Research Center, and James A. Albers (page images at HathiTrust)
• Performance of a vortex-controlled diffuser in an annular swirl-can combustor at inlet Mach numbers up to 0.53 (National Aeronautics and Space Administration, Scientific and Technical Information Office, 1979), by John M. Smith (page images at HathiTrust)
• Effect of wall edge suction on the performance of a short annular dump diffuser with exit passage flow resistance (National Aeronautics and Space Administration ;, 1975), by Albert J. Juhasz and Lewis Research Center (page images at HathiTrust)
• Effect of wall suction on performance of a short annular diffuser at inlet Mach numbers up to 0.5 (National Aeronautics and Space Administration ;, 1975), by Albert J. Juhasz and Lewis Research Center (page images at HathiTrust)
• Pressure recovery performance of conical diffusers at high subsonic Mach numbers (National Aeronautics and Space Administration ;, 1973), by Francis X. Dolan, Peter W. Runstadler, Lewis Research Center, and inc Creare (page images at HathiTrust)
• Design and experimental performance of short curved wall diffusers with axial symmetry utilizing slot suction (National Aeronautics and Space Administration ;, 1973), by Tah-teh Yang, Carl D. Nelson, William G. Hudson, Lewis Research Center, and Clemson University (page images at HathiTrust)
• Mean-flow measurements of the flow field diffusing bend (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Oden J. McMillan, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Nielsen Engineering & Research, and Lewis Research Center (page images at HathiTrust)
• Performance of an asymmetric short annular diffuser with a nondiverging inner wall using suction (National Aeronautics and Space Administration ;, 1974), by Albert J. Juhasz and Lewis Research Center (page images at HathiTrust)
• Experimental and analytical study of a conically diffused flow with a nearly separated boundary layer (National Aeronautics and Space Administration ;, 1973), by Donald R. Boldman, Harvey E. Neumann, and Lewis Research Center (page images at HathiTrust)
• Effect of diffusers, shrouds, and mass injection on the starting and operating characteristics of a Mach 5 free jet tunnel (National Aeronautics and Space Administration :, 1971), by John K. Molloy, J. Wayne Keyes, Ernest A. Mackley, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Performance of a low-pressure-ratio centrifugal compressor with four diffuser designs (National Aeronautics and Space Administration ;, 1973), by Hugh A. Klassen and Lewis Research Center (page images at HathiTrust)
• Performance characteristics of two 6° and two 12° diffusers at high flow rates (National Advisory Committee for Aeronautics, 1949), by William J. Nelson, Eileen G. Popp, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (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 (National Advisory Committee for Aeronautics, 1950), by Jerome Persh, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Comparison of rocket performance using exhaust diffuser and conventional techniques for altitude simulation (National Aeronautics and Space Administration, 1959), by Joseph N. Sivo, Daniel J. Peters, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Untersuchungen ueber den diffusorenwirkungsgrad und ueber die erzielung einwandfreier parallelstrahlen bei ueberschallwindkanaelen (Dayton, Ohio : Air Documents Division, Intelligence Department, Air Materiel command, Wright-Patterson Air Force Base, 1948., 1948), by Klaus Oswatitsch (page images at HathiTrust)
• Vorticity-stream function formulation of compressible and incompressible turbulent internal flows (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Engine Test Facility, Air Force Systems Command, United States Air Force, 1979., 1979), by John C. Chien, Inc ARO, United States. Air Force. Arnold Air Force Base, and Arnold Engineering Development Center (page images at HathiTrust)

• A Three-dimensional turbulent compressible subsonic duct flow analysis for use with constructed coordinate systems (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by R. Levy, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Performance characteristics of plane-wall two-dimensional diffusers (National Advisory Committee for Aeronautics, 1953), by Elliott G. Reid and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Methods of analysis of the performance of ocean outfall diffusers with application to the proposed Hyperion outfall ([Hyperion Engineers?, 1956), by Norman H. Brooks and Hyperion Engineers (page images at HathiTrust; US access only)
• Numerical analysis of turbulent separated subsonic diffuser flows (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Engine Test Facility, Air Force Systems Command, United States Air Force, 1977., 1977), by J. C. Chien, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
• Numerical computation of subsonic conical diffuser flows with nonuniform turbulent inlet conditions (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Engine Test Facility, Air Force Systems Command, United States Air Force, 1977., 1977), by J. C. Chien, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
• The Alperin jet-diffuser ejector (AJDE) development, testing, and performance verification report (China Lake, California : Naval Weapons Center, Systems Development Department, 1976., 1976), by Morton Alperin, Charles A. Smith, Kiunn Jenq Wu, United States. Naval Air Systems Command, and Naval Weapons Center (page images at HathiTrust)

• Effect of wall edge suction on the performance of a short annular dump diffuser with exit passage flow resistance (National Aeronautics and Space Administration ;, 1975), by Albert J. Juhasz and Lewis Research Center (page images at HathiTrust)
• Effect of wall suction on performance of a short annular diffuser at inlet Mach numbers up to 0.5 (National Aeronautics and Space Administration ;, 1975), by Albert J. Juhasz and Lewis Research Center (page images at HathiTrust)

• Supersonic inlet diffusers and introduction to internal aerodynamics. (Minneapolis-Honeywell Regulator Co., Aeronautical Division, 1956), by Rudolf Hermann (page images at HathiTrust)
• Effects of suction boundary-layer control on the performance of a short annular diffuser with an upstream terminal normal shock (National Aeronautics and Space Administration :, 1962), by Charles J. Shoemaker, John R. Henry, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Experimental investigation of direct control of diffuser pressure on 16-inch ram-jet engine (National Advisory Committee for Aeronautics, 1955), by William R. Dunbar, Herbert G. Hurrell, George Vasu, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• A proposed ram-jet control system operated by use of diffuser pressure recovery (National Advisory Committee for Aeronautics, 1952), by Maxime A. Faget, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)

More items available under broader and related terms at left.