Airplanes -- Turbofan engines -- Computer simulationSee also what's at your library, or elsewhere.
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Filed under: Airplanes -- Turbofan engines -- Computer simulation- Advanced detection, isolation, and accommodation of sensor failures -- real-time evaluation (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1987), by Walter C. Merrill, William M. Bruton, John C. DeLaat, and Lewis Research Center (page images at HathiTrust)
- Real-time simulation of the TF30-P-3 turbofan engine using a hybrid computer (National Aeronautics and Space Administration ;, 1974), by John R. Szuch, William M. Bruton, and Lewis Research Center (page images at HathiTrust)
- Method of discrete modeling and its application to estimation of TF30 engine variables (National Aeronautics and Space Administration ;, 1976), by Dale J. Arpasi, William M. Bruton, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
- Program for calculating linear A, B, C, and D matrices from a nonlinear dynamic engine simulation (National Aeronautics and Space Administration, Scientific and Technical Information Office, 1978), by Lucille C. Geyser (page images at HathiTrust)
- HYDES : a generalized hybrid computer program for studying turbojet or turbofan engine dynamics (National Aeronautics and Space Administration ;, 1974), by John R. Szuch and Lewis Research Center (page images at HathiTrust)
- A simple dynamic engine model for use in a real-time aircraft simulation with thrust vectoring (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Steven A. Johnson and Dryden Flight Research Facility (page images at HathiTrust)
- Real-time simulation of F100-PW-100 turbofan engine using the hybrid computer (National Aeronautics and Space Administration ;, 1975), by John R. Szuch, Kurt Seldner, and Lewis Research Center (page images at HathiTrust)
Items below (if any) are from related and broader terms.
Filed under: Airplanes -- Turbofan engines- Bird ingestion into large turbofan engines (Federal Aviation Administration Technical Center ;, 1992), by Howard Banilower, Colin Goodall, and Federal Aviation Administration Technical Center (U.S.) (page images at HathiTrust)
- Evaluation of various thrust calibration [i.e. calculation] techniques on an F404 engine (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Ronald J. Ray and Dryden Flight Research Facility (page images at HathiTrust)
- Installation effects of wing-mounted turbofan nacelle-pylons on a 1/17 scale, twin-engine, low-wing transport model (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Odis C. Pendergraft and Langley Research Center (page images at HathiTrust)
- Static internal performance of ventral and rear nozzle concepts for short-takeoff and vertical-landing aircraft (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ;, 1991), by Richard J. Re, George T. Carson, and Langley Research Center (page images at HathiTrust)
- Performance of a 1.15-pressure-ratio axial-flow fan stage with a blade tip solidity of 0.5 (National Aeronautics and Space Administration ;, 1974), by Walter Martin Osborn, Ronald J. Steinke, 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)
- Effects of tip clearance on overall performance of transonic fan stage with and without casing treatment (National Aeronautics and Space Administration ;, 1977), by Royce D. Moore, Walter Martin Osborn, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
- Terminal-shock and restart control of a Mach 2.5, axisymmetric, mixed compression inlet with 40 percent internal contraction (National Aeronautics and Space Administration ;, 1974), by Robert J. Baumbick, Robert C. Seidel, Robert E. Wallhagen, and Lewis Research Center (page images at HathiTrust)
- Noise data from tests of a 1.83-meter- (6-ft-) diameter variable-pitch 1.2 pressure-ratio fan (QF-9) (National Aeronautics and Space Administration ;, 1975), by Frederick W. Glaser, Robert Friedman, Joseph A. Wazyniak, 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)
- Measurement of gaseous emissions from a turbofan engine at simulated altitude conditions (National Aeronautics and Space Administration ;, 1974), by Larry A. Diehl, James A. Biaglow, and Lewis Research Center (page images at HathiTrust)
- Terminal-shock and restart control of a Mach 2.5, mixed-compression inlet coupled to a turbofan engine (National Aeronautics and Space Administration ;, 1974), by Robert J. Baumbick, Carl J. Daniele, Peter G. Batterton, and Lewis Research Center (page images at HathiTrust)
- Laser anemometer measurements and computations in an annular cascade of high turning core turbine vanes (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Louis J. Goldman, Richard G. Seasholtz, and Lewis Research Center (page images at HathiTrust)
- Flight Reynolds number effects on a fighter-type, circular-arc - 19 ̊conic boattail nozzle at subsonic speeds (National Aeronautics and Space Administration ;, 1974), by Roger Chamberlin 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)
- Performance of 1.15-pressure-ratio fan stage at several rotor blade setting angles with reverse flow (National Aeronautics and Space Administration ;, 1976), by George Kovich, Royce D. Moore, and United States National Aeronautics and Space Administration (page images at HathiTrust)
- Performance of low-pressure-ratio low-tip-speed fan stage with blade tip solidity of 0.65 (National Aeronautics and Space Administration ;, 1976), by George Kovich, Ronald J. Steinke, and Lewis Research Center (page images at HathiTrust)
- Performance of a low-pressure fan stage with reverse flow (National Aeronautics and Space Administration ;, 1976), by Royce D. Moore, Edward R. Tysl, George W. Lewis, 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)
- Gaseous exhaust emissions from a JT8D-109 turbofan engine at simulated cruise flight conditions (National Aeronautics and Space Administration, 1975), by Larry A. Diehl and J. D. Holdeman (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)
- Study and development of acoustic treatment for jet engine tailpipes (National Aeronautics and Space Administration, 1971), by M. D. Nelsen, Langley Research Center, Boeing Company. AVCO Corporation. Systems Division, and United States National Aeronautics and Space Administration (page images at HathiTrust)
- Design, fabrication and acoustic tests of a 36 inch (0.914 meter) statorless turbotip fan (National Aeronautics and Space Administration ;, 1975), by E. G. Smith, W. R. Uhl, D. L. Stempert, Ames Research Center, and General Electric Company (page images at HathiTrust)
- Highly loaded multi-stage fan drive turbine : performance of initial seven configurations (National Aeronautics and Space Administration ;, 1974), by G. W. Wolfmeyer, M. W. Thomas, Lewis Research Center, and General Electric Company (page images at HathiTrust)
- The Influence of wing loading on turbofan powered STOL transports with and without externally blown flaps (National Aeronautics and Space Administration ;, 1973), by R. L. Morris, Langley Research Center, and Boeing Company. Wichita Division (page images at HathiTrust)
- Use of potential flow theory to evaluate subsonic inlet data from a simulator-powered nacelle at cruise conditions (National Aeronautics and Space Administration ;, 1974), by Lawrence J. Bober and Lewis Research Center (page images at HathiTrust)
- A brief study of the effects of turbofan-engine bypass ratio on short- and long-haul cruise aircraft (National Aeronautics and Space Administration ;, 1975), by Arvid L. Keith and Langley Research Center (page images at HathiTrust)
- NASA TN D-6178 (National Aeronautics and Space Administration ;, 1971), by Edward J. Rice, Loren W. Acker, Charles E. Feiler, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
- Wing-surface-jet interaction characteristics of an upper-surface blown model with rectangular exhaust nozzles and a radius flap (National Aeronautics and Space Administration ;, 1976), by Alvin M. Bloom, William C. Sleeman, William C. Hohlweg, and United States National Aeronautics and Space Administration (page images at HathiTrust)
- Low-speed jet noise from a 1.83-meter (6-ft) fan for tubrofan engines (U.S. National Aeronautics and Space Administration ;, 1971), by Gene L. Minner, Charles E. Feiler, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
- Research turbine for high-temperature core engine application (National Aeronautics and Space Administration ;, 1974), by Edward M. Szanca and Lewis Research Center (page images at HathiTrust)
- Noise measurements for a three-engine turbofan transport airplane during climbout and landing approach operations (U.S. National Aeronautics and Space Administration ;, 1971), by W. Latham Copeland, Lorenzo R. Clark, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
- Longitudinal aerodynamic characteristics of an externally blown flap powered-lift model with several propulsive system simulators (National Aeronautics and Space Administration ;, 1974), by Danny R. Hoad and Langley Research Center (page images at HathiTrust)
- A Study of turbofan-engine compressor-noise-suppression techniques (National Aeronautics and Space Administration, 1968), by Alan H. Marsh (page images at HathiTrust; US access only)
- Code for hail ingestion in engine inlets. (FAA Technical Center ;, 1995), by N. Gopalaswamy, S. N. B. Murthy, Purdue Research Foundation, and Federal Aviation Administration Technical Center (U.S.) (page images at HathiTrust)
- Bird ingestion into large turbofan engines (Federal Aviation Administration Technical Center ;, 1995), by Howard Banilower, Colin Goodall, and Federal Aviation Administration Technical Center (U.S.) (page images at HathiTrust)
- Propulsion system integration and test program (steady state) (U) summary (U). Part I. Integration technique and test activities (Wright-Patterson Air Force Base, Ohio : Air Force Aero Propulsion Laboratory, Air Force Systems Command, United States Air Force, 1969., 1969), by Robert H. Johnson, United Aircraft Corporation. Pratt & Whitney Aircraft Division, North American Rockwell Corporation, General Motors Corporation. Allison Division, United States. Air Force. Systems Command, and Air Force Aero Propulsion Laboratory (U.S.) (page images at HathiTrust)
- Propulsion system integration and test program (steady state) (U) summary (U). Part II. Vehicle analysis studies (U) (Wright-Patterson Air Force Base, Ohio : Air Force Aero Propulsion Laboratory, Air Force Systems Command, United States Air Force, 1969., 1969), by Robert H. Johnson, North American Rockwell Corporation, General Motors Corporation. Allison Division, United States. Air Force. Systems Command, and Air Force Aero Propulsion Laboratory (U.S.) (page images at HathiTrust)
Filed under: Airplanes -- Turbofan engines -- Afterburners- NASA TN D-6297 (National Aeronautics and Space Administration:, 1971), by Frank W. Burcham (page images at HathiTrust; US access only)
- 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)
Filed under: Airplanes -- Turbofan engines -- Automatic control- Preliminary flight evaluation of an engine performance optimization algorithm (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991), by Heather H. Lambert and Dryden Flight Research Facility (page images at HathiTrust)
- NASA TM X-3105 (National Aeronautics and Space Administration, 1975), by David S. Cwynar, Peter G. Batterton, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
- Design and evaluation of a sensor fail-operational control system for a digitally controlled turbofan engine (National Aeronautics and Space Administration ;, 1975), by Frank J. Hrach, Dale J. Arpasi, William M. Bruton, and Lewis Research Center (page images at HathiTrust)
- A preliminary evaluation of an F100 engine parameter estimation process using flight data (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Trindel A. Maine, Heather H. Lambert, Glenn B. Gilyard, and Dryden Flight Research Facility (page images at HathiTrust)
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