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Airplanes -- Turbojet engines -- Air intakes -- Noise

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• Airplanes -- Turbojet engines -- Air intakes
• Airplanes -- Turbojet engines -- Noise

• Airplanes -- Turbojet engines -- Air intakes -- Noise -- Mathematical models
• Airplanes -- Turbojet engines -- Air intakes -- Noise -- Measurement

• Effect of entry-lip design on aerodynamics and acoustics of high-throat-Mach-number inlets for the quiet, clean, short-haul experimental engine (National Aeronautics and Space Administration ;, 1975), by Brent A. Miller, Howard L. Wesoky, and Benjamin J. Dastoli (page images at HathiTrust)
• Analytical and experimental studies of acoustic performance of segmented liners in a compressor inlet (National Aeronautics and Space Administration ;, 1977), by R. E. Motsinger, General Electric Company, and United States National Aeronautics and Space Administration (page images at HathiTrust)

• Combined quadrupole-dipole model for inlet flow distortion noise from a subsonic fan (National Aeronautics and Space Administration ;, 1974), by Marvin E. Goldstein, Thomas F. Gelder, James H. Dittmar, and Lewis Research Center (page images at HathiTrust)
• Optimal one-section and two-section circular sound-absorbing duct liners for plane-wave and monopole sources without flow (National Aeronautics and Space Administration ;, 1976), by Harold C. Lester, Joe W. Posey, and United States National Aeronautics and Space Administration (page images at HathiTrust)

• Study of noise and inflow distortion sources in the NASA QF-1B fan using measured blade and vane pressures (National Aeronautics and Space Administration ;, 1977), by Donald Hanson and United States National Aeronautics and Space Administration (page images at HathiTrust)

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

• Dynamic response of a Mach 2.5 axisymmetric inlet and turbojet engine with a poppet-valve-controled inlet-stability bypass system when subjected to internal and external airflow transients (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1980), by Bobby W. Sanders, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Turbojet-exhaust-nozzle secondary-airflow pumping as an exit control of an inlet-stability bypass system for a Mach 2.5 axisymmetric mixed-compression inlet (NASA, Scientific and Technical Information Office ;, 1980), by Bobby W. Sanders, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Data on effects of incident-reflecting shocks on the turbulent boundary layer (National Aeronautics and Space Administration ;, 1966), by S. Z. Pinckney and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effects of inlet distortion on a static pressure probe mounted on the engine hub in an F-15 airplane (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Donald L. Hughes, Karen G. Mackall, Lawrence P. Myers, and Dryden Flight Research Facility (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)
• Design of a very-low-bleed Mach 2.5 mixed-compression inlet with 45 percent internal contraction (National Aeronautics and Space Administration ;, 1975), by Joseph F. Wasserbauer, Harvey E. Neumann, Robert J. Shaw, and Lewis Research Center (page images at HathiTrust)
• Low-speed wind-tunnel investigation of the aerodynamic and acoustic performance of a translating-grid choked-flow inlet (National Aeronautics and Space Administration ;, 1974), by John M. Abbott, Richard L. Golladay, Brent A. Miller, and Lewis Research Center (page images at HathiTrust)
• FORTRAN program to generate engine inlet flow contour maps and distortion parameters (National Aeronautics and Space Administration ;, 1974), by John H. Dicus and Lewis Research Center (page images at HathiTrust)
• Steady-state inlet temperature distortion effects on the stall limits of a J85-GE-13 turbojet engine (National Aeronautics and Space Administration ;, 1974), by Charles M. Mehalic, Roy A. Lottig, and Lewis Research Center (page images at HathiTrust)
• Analog computer implementation of four instantaneous distortion indices (National Aeronautics and Space Administration ;, 1974), by William G. Costakis and Lewis Research Center (page images at HathiTrust)
• Aerodynamic analysis of several high throat Mach number inlets for the Quiet Clean Short-Haul Experimental Engine (National Aeronautics and Space Administration ;, 1975), by James A. Albers, John J. Hirn, Norbert O. Stockman, and Lewis Research Center (page images at HathiTrust)
• Performance and surge limits of a TF30-P-3 turbofan engine/axisymmetric mixed-compression inlet propulsion system at Mach 2.5 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Joseph F. Wasserbauer, Robert J. Shaw, Harvey E. Neumann, and Lewis Research Center (page images at HathiTrust)
• Evaluation of some control-volume techniques for analysis of shock-boundary-layer interactions in supersonic inlets (National Aeronautics and Space Administration ;, 1975), by Warren R. Hingst and Lewis Research Center (page images at HathiTrust)
• Low-speed wind tunnel tests of a 50.8-centimeter (20-in.) 1.15-pressure-ratio fan engine model (National Aeronautics and Space Administration ;, 1974), by Howard L. Wesoky and Lewis Research Center (page images at HathiTrust)
• Cruise performance of an isolated 1.15 pressure ratio turbofan propulsion system simulator at Mach numbers from 0.6 to 0.85 (National Aeronautics and Space Administration ;, 1974), by Fred W. Steffen and Lewis Research Center (page images at HathiTrust)
• Instantaneous distortion in a Mach 2.5, 40-percent-internal-contraction inlet and its effect on turbojet stall margin (National Aeronautics and Space Administration ;, 1974), by Paul L. Burstadt, James E. Calogeras, and Lewis Research Center (page images at HathiTrust)
• Transonic off-design drag and performance of three mixed-compression axisymmetric inlets (National Aeronautics and Space Administration ;, 1975), by Richard R. Woollett, David A. Choby, Edward T. Meleason, and Lewis Research Center (page images at HathiTrust)
• Experimental investigation of a simple distortion index utilizing steady-state and dynamic distortions in a Mach 2.5 mixed-compression inlet and turbofan engine (National Aeronautics and Space Administration ;, 1975), by William G. Costakis and Lewis Research Center (page images at HathiTrust)
• Model investigation of inlet plenum flow straightening techniques for altitude test facility (National Aeronautics and Space Administration ;, 1976), by Stephen M. Riddlebaugh, Heinz G. Linke, and Lewis Research Center (page images at HathiTrust)
• An investigation of several NACA 1-series axisymmetric inlets at Mach numbers from 0.4 to 1.29 (National Aeronautics and Space Administration ;, 1974), by Richard J. Re and Langley Research Center (page images at HathiTrust)
• Theoretical study of VTOL tilt-nacelle axisymmetric inlet geometries (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by J. Dennis Hawk, Norbert O. Stockman, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Lewis Research Center (page images at HathiTrust)
• Airflow and thrust calibration of an F100 engine, S/N P680059, at selected flight conditions (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Thomas J. Biesiadny, Jose R. Rodriguez, Douglas Lee, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Mechanical characteristics of stability-bleed valves for a supersonic inlet (National Aeronautics and Space Administration ;, 1977), by George H. Neiner, Gary L. Cole, Miles O. Dustin, and United States National Aeronautics and Space Administration (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 vortex generators in a Mach 2.5 low-bleed full-scale 45-percent-internal-contraction axisymmetric inlet (National Aeronautics and Space Administration ;, 1975), by Harvey E. Neumann, Robert J. Shaw, Joseph F. Wasserbauer, and Lewis Research Center (page images at HathiTrust)
• Noise suppression by an acoustically treated three-ring inlet on a TF-34 engine (U.S. National Aeronautics and Space Administration ;, 1976), by Gene L. Minner, Laurence J. Heidelberg, Richard G. Goldman, and Lewis Research Center (page images at HathiTrust)
• Frequency response of an axial-flow compressor exposed to inlet pressure perturbations (National Aeronautics and Space Administration ;, 1974), by Edward J. Milner, Francis J. Paulovich, Leon M. Wenzel, and Lewis Research Center (page images at HathiTrust)
• Pressure-activated stability-bypass-control valves to increase the stable airflow range of a Mach 2.5 inlet with 40 percent internal contraction (National Aeronautics and Space Administration ;, 1974), by Glenn A. Mitchell, Bobby W. Sanders, and Lewis Research Center (page images at HathiTrust)
• Forward-slanted slot throat stability bypass to increase the stable airflow range of a Mach 2.5 inlet with 60-percent internal contraction (National Aeronautics and Space Administration ;, 1974), by Robert J. Shaw, Bobby W. Sanders, Glenn A. Mitchell, and Lewis Research Center (page images at HathiTrust)
• Distributed porous throat stability bypass to increase the stable airflow range of a Mach 2.5 inlet with 60 percent internal contraction (National Aeronautics and Space Administration ;, 1974), by Robert J. Shaw, Bobby W. Sanders, Glenn A. Mitchell, and Lewis Research Center (page images at HathiTrust)
• Distributed educated throat stability bypass to increase the stable airflow range of a Mach 2.5 inlet with 60-percent internal contraction (National Aeronautics and Space Administration ;, 1974), by Robert J. Shaw, Bobby W. Sanders, Glenn A. Mitchell, and Lewis Research Center (page images at HathiTrust)
• Throat stability-bypass systems to increase the stable airflow range of a Mach 2.5 inlet with 60-percent internal contraction (National Aeronautics and Space Administration ;, 1974), by Glenn A. Mitchell, Robert J. Shaw, Bobby W. Sanders, and Lewis 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)
• Effect of a 180-̊extent inlet pressure distortion on the internal flow conditions of a TF30-P-3 engine (National Aeronautics and Space Administration ;, 1975), by Claude E. de Bogdan and Lewis Research Center (page images at HathiTrust)
• Effect of afterburner lights and inlet unstarts on a mixed-compression-inlet turbofan engine operating at Mach 2.5 (National Aeronautics and Space Administration ;, 1975), by Robert J. Baumbick, Carl J. Daniele, Peter G. Batterton, and Lewis Research Center (page images at HathiTrust)
• Low-speed wind-tunnel investigation of the aerodynamic and acoustic performance of several sonic inlet takeoff and approach geometries (National Aeronautics and Space Administration ;, 1976), by John M. Abbott, Richard L. Golladay, and Lewis Research Center (page images at HathiTrust)
• An investigation of several NACA 1-series inlets at Mach numbers from 0.4 to 1.29 for mass-flow ratios near 1.0 (U.S. National Aeronautics and Space Administration ;, 1976), by Richard J. Re and Langley Research Center (page images at HathiTrust)
• Incidence angle bounds for lip flow separation of the 13.97-centimeter-diameter inlets (U.S. National Aeronautics and Space Administration ;, 1976), by Roger W. Luidens, John M. Abbott, and Lewis Research Center (page images at HathiTrust)
• Boundary-layer bleed system study for a full-scale, mixed-compression inlet with 45 percent internal contraction (U.S. National Aeronautics and Space Administration ;, 1976), by Robert J. Shaw, Harvey E. Neumann, Joseph F. Wasserbauer, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Study of noise sources in a subsonic fan using measured blade pressures and acoustic theory (National Aeronautics and Space Administration ;, 1975), by Donald B. Hanson, Langley Research Center, and United Technologies Corporation. Hamilton Standard Division (page images at HathiTrust)
• Analysis of the dynamic response of a supersonic inlet to flow-field perturbations upstream of the normal shock (National Aeronautics and Space Administration ;, 1975), by Gary L. Cole, Ross G. Willoh, and Lewis Research Center (page images at HathiTrust)
• Effect of simulated downstream flow blockage doors on the performance of an axial-flow fan rotor (National Aeronautics and Space Administration; [for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], 1970), by Walter Martin Osborn and Jack M. Wagner (page images at HathiTrust; US access only)
• Investigation of a mixed-compression axisymmetric inlet system at Mach numbers 0.6 to 3.5 (National Aeronautics and Space Administration; [for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], 1970), by Donald B. Smeltzer and Norman E. Sorensen (page images at HathiTrust; US access only)
• Coupled supersonic inlet-engine control using overboard bypass doors and engine speed to control normal shock position (National Aeronautics and Space Administration, 1970), by Gary L. Cole, George H. Neiner, Robert E. Wallhagen, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• An analysis of the capabilities and limitations of turbine air cooling methods (National Aeronautics and Space Administration ;, 1970), by Jack B. Esgar, Albert Kaufman, Raymond S. Colladay, and Lewis Research Center (page images at HathiTrust)
• NASA TN D-5330 (National Aeronautics and Space Administration ;, 1969), by Bernhard H. Anderson, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• A mathematical analysis of supersonic inlet dynamics (National Aeronautics and Space Administration ;, 1968), by Ross G. Willoh, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
• NASA TN D-6319 (National Aeronautics and Space Administration:, 1971), by Dudley G. McConnell (page images at HathiTrust; US access only)
• Boundary-layer analysis of subsonic inlet diffuser geometries for engine nacelles (National Aeronautics and Space Administration ;, 1974), by James A. Albers, E. John Felderman, and Lewis Research Center (page images at HathiTrust)
• Experimental investigation of two-stage air-cooled turbine suitable for flight at Mach 2.5 (National Aeronautics and Space Administration, 1959), by Harold J. Schum, Robert R. Nunamaker, Donald A. Petrash, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Performance summary and analysis of a Mach 3.0 design axisymmetric all-external-compression double-cone inlet Mach number range 3.0 to 0.8 (National Aeronautics and Space Administration, 1960), by John L. Allen, Glenn A. Mitchell, Owen H. Davis, and Lewis Research Center (page images at HathiTrust)
• Effect of circumferential total-pressure gradients typical of single-inlet duct installations on performance of an axial-flow turbojet engine (National Advisory Committee for Aeronautics, 1955), by S. C. Huntley, Curits L. Walker, Joseph N. Sivo, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (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 (National Advisory Committee for Aeronautics, 1955), by Gene J. Bingham, United States. National Adviosry Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Investigation of fixed-geometry supersonic inlets with bypass ducts for matching turbojet-engine air-flow requirements over a range of transonic and supersonic speeds (National Advisory Committee for Aeronautics, 1958), by Abraham Leiss, Walter J. Kouyoumjian, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Performance of a turbojet engine in combination with an external-internal-compression inlet to mach 2.88 (National Aeronautics and Space Administration, 1960), by David N. Bowditch, William K. Tabata, Bernhard H. Anderson, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Method and graphs for the evaluation of air-induction systems (U.S. Government Printing Office, 1953), by George B. Brajnikoff and United States National Advisory Committee for Aeronautics (page images at HathiTrust; US access only)
• Results of a 0.1-scale B-1 inlet model test at transonic and supersonic Mach numbers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1971., 1971), by F. J. Graham, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (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)
• Blockage study of a 1/16-scale B-1 inlet model in the 1-ft transonic and supersonic tunnels of the Propulsion Wind Tunnel Facility (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1972., 1972), by C. F. Anderson, F. M. Jackson, Arnold Engineering Development Center, United States. Air Force. Systems Command, and Inc ARO (page images at HathiTrust)
• Results of a 0.2-scale B-1 inlet verification model test at transonic and supersonic Mach numbers (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1972., 1972), by John F. Riddell, F. M. Jackson, Arnold Engineering Development Center, United States. Air Force. Systems Command, and Inc ARO (page images at HathiTrust)
• Supersonic inlet investigation. Volume I, Summary report (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1971., 1971), by T. W. Tsukahira, Gordon R. Hall, M. Yaamada, W. F. Wong, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Northrop Corporation. Aircraft Division (page images at HathiTrust)
• Supersonic inlet investigation. Volume III, Wind tunnel data report (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1971., 1971), by T. W. Tsukahira, B. G. Franco, W. F. Wong, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Northrop Corporation. Aircraft Division (page images at HathiTrust)
• Supersonic inlet investigation. Volume II, Air induction sysem dynamic simulation model (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1971., 1971), by Nasim F. Amin, Gordon R. Hall, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Northrop Corporation. Aircraft Division (page images at HathiTrust)

More items available under broader and related terms at left.