The Online Books Page

Airplanes -- Motors -- Thrust -- Mathematical models

See also what's at your library, or elsewhere.

• Airplanes -- Motors -- Thrust
• Airplanes -- Motors -- Mathematical models

• Airplanes -- Motors -- Thrust -- Computer simulation

• Evaluation of a simplified gross thrust calculation technique using two prototype F100 turbofan engines in an altitude facility (National Aeronautics and Space Administration, Scientific and Technical Information Branch :, 1979), by Frank J. Kurtenbach, Hugh L. Dryden Flight Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (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)

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

• A Review of technologies applicable to low-speed flight of high-performance aircraft investigated in the Langley 14- by 22-foot subsonic tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1988), by John W. Paulson and Langley Research Center (page images at HathiTrust)
• Static performance of an axisymmetric nozzle with post-exit vanes for multiaxis thrust vectoring (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1988), by Bobby L. Berrier and Langley Research Center (page images at HathiTrust)
• Static investigation of a two-dimensional convergent-divergent exhaust nozzle with multiaxis thrust-vectoring capability (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by John G. Taylor and Langley Research Center (page images at HathiTrust)
• Static thrust-vectoring performance of nonaxisymmetric convergent-divergent nozzles with post-exit yaw vanes (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1991), by Robert J. Foley, Odis C. Pendergraft, and Langley Research Center (page images at HathiTrust)
• Aeropropulsive characteristics of canted twin pitch-vectoring nozzles at Mach 0.20 to 1.20 (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1991), by Francis J. Capone, Mary L. Mason, and Langley Research Center (page images at HathiTrust)
• A Preliminary investigation of the use of throttles for emergency flight control (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991), by Frank W. Burcham and Dryden Flight Research Facility (page images at HathiTrust)
• A Simulation evaluation of a four-engine jet transport using engine thrust modulation for flightpath control (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991), by Glenn B. Gilyard and Dryden Flight Research Facility (page images at HathiTrust)
• A static investigation of the thrust vectoring system of the F/A-18 high-alpha research vehicle (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Mary L. Mason, Scott C. Asbury, Francis J. Capone, and Langley Research Center (page images at HathiTrust)
• Static investigation of several yaw vectoring concepts on nonaxisymmetric nozzles (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by Mary L. Mason, Bobby L. Berrier, and Langley Research Center (page images at HathiTrust)
• Static investigation of two STOL nozzle concepts with pitch thrust-vectoring capability (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1986), by Mary L. Mason, James R. Burley, and Langley Research Center (page images at HathiTrust)
• Flight investigation of installation effects on a plug nozzle with a series of boattailed primary shrouds installed on an underwing nacelle (National Aeronautics and Space Administration ;, 1974), by Verlon L. Head 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)
• Thrust-induced effects on subsonic longitudinal aerodynamic characteristics of a vectored-engine-over-wing configuration (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by P. Frank Quinto, John W. Paulson, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Aircraft ground tests and subscale model results of axial thrust loss caused by thrust vectoring using turning vanes (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Steven A. Johnson and Dryden Flight Research Facility (page images at HathiTrust)
• Investigation of a moving-model technique for measuring ground effects (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1989), by Guy T. Kemmerly and John W. Paulson (page images at HathiTrust)
• Dynamics of high-bypass-engine thrust reversal using a variable-pitch fan (National Aeronautics and Space Administration ;, 1977), by John W. Schaefer, Edward G. Stakolich, David A. Sagerser, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• An experimental investigation of thrust vectoring two-dimensional covergent-divergent nozzles installed in a twin-engine fighter model at high angles of attack (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1990), by Francis J. Capone, Laurence D. Leavitt, Mary L. Mason, and Langley Research Center (page images at HathiTrust)
• Static internal performance of an axisymmetric nozzle with multiaxis thrust-vectoring capability (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1991), by George T. Carson, Francis J. Capone, and Langley Research Center (page images at HathiTrust)
• Longitudinal aerodynamic characteristics of a deflected-thrust propulsive-lift transport model (National Aeronautics and Space Administration ;, 1975), by Danny R. Hoad and Langley Research Center (page images at HathiTrust)
• A method for obtaining practical flutter-suppression control laws using results of optimal control theory (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by Jerry R. Newsom, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Thrust performance of isolated 36-chute suppressor plug nozzles with and without ejectors at Mach numbers from 0 to 0.45 (National Aeronautics and Space Administration ;, 1975), by Douglas E. Harrington, Stanley A. Skebe, James J. Schloemer, and Lewis Research Center (page images at HathiTrust)
• Flight evaluation of a simplified gross thrust calculation technique using an F100 turbofan engine in an F-15 airplane (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Frank J. Kurtenbach, Frank W. Burcham, Hugh L. Dryden Flight Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Static performance of a cruciform nozzle with multiaxis thrust-vectoring and reverse-thrust capabilities (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by David J. Wing, Scott C. Asbury, and Langley Research Center (page images at HathiTrust)
• Thrust performance of a variable-geometry, nonaxisymmetric, two-dimensional, convergent-divergent exhaust nozzle on a turbojet engine at altitude (National Aeronautics and Space Administration Scieentific and Technical Information Branch ;, 1983), by David M. Straight, Richard R. Cullom, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Full-scale wind tunnel tests of a low-wing, single-engine, light plane with positive and negative propeller thrust and up and down flap deflection (National Aeronautics and Space Administration, 1971), by Edward Seckel, United States National Aeronautics and Space Administration, Langley Research Center, and Princeton University (page images at HathiTrust)
• Wind tunnel performance test of coannular plug nozzles (National Aeronautics and Space Adiministration, Scientific and Technical Information Office ;, 1978), by Paul S. Staid and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (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-5982 (National Aeronautics and Space Administration :, 1970), by Milton D. McLaughlin, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Aerodynamic characteristics of a vectored-thrust V/STOL fighter in the transition-speed range (National Aeronautics and Space Administration ;, 1973), by Raymond E. Mineck, Myles F. Schwendemann, and Langley Research Center (page images at HathiTrust)
• Comparison of three thrust calculation methods using in-flight thrust data (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Donald L. Hughes, Hugh L. Dryden Flight Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Effect of free-stream Mach number on gross-force and pumping characteristics of several ejectors (National Advisory Committee for Aeronautics, 1955), by Leonard E. Stitt, Alfred S. Valerino, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Turbojet combustor performance with injection of hydrogen peroxide for thrust augmentation (National Advisory Committee for Aeronautics, 1956), by Allen J. Metzler, Jack S. Grobman, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Simulated afterburner performance with hydrogen peroxide injection for thrust augmentation (National Advisory Committee for Aeronautics, 1956), by Allen J. Metzler, Jack S. Grobman, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Thrust augmentation study of high performance ejectors (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 John E. Minardi, Hans von Ohain, Air Force Wright Aeronautical Laboratories, Air Force Flight Dynamics Laboratory (U.S.), and University of Dayton. Research Institute (page images at HathiTrust)
• Post stall maneuvers and thrust vectoring performance analysis (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1984., 1984), by L. Earl Miller, Air Force Wright Aeronautical Laboratories, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)

• Thrust augmenting ejectors (Ames Research Center, 1979), by Workshop on Thrust Augmenting Ejectors (1978 : Ames Research Center), A. E. Lopez, Air Force Flight Dynamics Laboratory (U.S.), Naval Air Development Center, and Ames Research Center (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)
• Measurement effects on the calculation of in-flight thrust for an F404 turbofan engine (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1989), by Timothy E. Conners and Dryden Flight Research Facility (page images at HathiTrust)
• NASA TN D-6297 (National Aeronautics and Space Administration:, 1971), by Frank W. Burcham (page images at HathiTrust; US access only)

• Flight propulsion control coupling for thrust vectoring fighter aircraft. Volume III, Phase II (Wright-Patterson Air Force Base : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1980., 1980), by Frederick C. Glaser, Douglas Aircraft Company, and Air Force Flight Dynamics Laboratory (U.S.) (page images at HathiTrust)

• Multiaxis control power from thrust vectoring for a supersonic fighter aircraft model at Mach 0.20 to 2.47 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1987), by Francis J. Capone, E. Ann Bare, and Langley Research Center (page images at HathiTrust)
• Pressure distribution on a vectored-thrust V/STOL fighter in the transition-speed range (National Aeronautics and Space Administration ;, 1974), by Raymond E. Mineck, Richard J. Margason, and Langley Research Center (page images at HathiTrust)

• Estimation of attainable leading-edge thrust for wings at subsonicaand supersonic speeds (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by Harry W. Carlson, Raymond L. Barger, Robert J. Mack, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Evaluation of a simplified gross thrust calculation technique using two prototype F100 turbofan engines in an altitude facility (National Aeronautics and Space Administration, Scientific and Technical Information Branch :, 1979), by Frank J. Kurtenbach, Hugh L. Dryden Flight Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Large-scale low-speed wind-tunnel tests of a delta winged supersonic transport model to determine aerodynamic effects of forward or reverse thrust (National Aeronautics and Space Administration, 1964), by William H. Tolhurst, Kiyoshi Aoyagi, and Ames Research Center (page images at HathiTrust)

• Development and verification of real-time, hybrid computer simulation of F100-PW-100(3) turbofan engine (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1977), by John R. Szuch, David S. Cwynar, Kurt Seldner, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Generation of linear dynamic models from a digital nonlinear simulation (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by Carl J. Daniele, Susan M. Krosel, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Lewis Research Center (page images at HathiTrust)

More items available under broader and related terms at left.