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Airplanes -- Turbojet engines -- Compressors -- Testing

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• Airplanes -- Turbojet engines -- Compressors
• Airplanes -- Turbojet engines -- Testing
• Compressors -- Testing

• Static sea-level performance of an axial-flow-compressor turbojet engine with an air-cooled turbine (National Advisory Committee for Aeronautics, 1955), by Reeves P. Cochran, Robert P. Dengler, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Evaluation of a compressor bleed system for rim cooling the turbine wheel of a turbojet engine (National Advisory Committee for Aeronautics, 1954), by C. R. Morse, R. H. Kemp, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)

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

• 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)
• An experimental investigation of compressor stall using an on-line distortion indicator and signal conditioner (National Aeronautics and Space Administration ;, 1975), by William G. Costakis, Leon M. Wenzel, 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)
• 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)
• Internal flow characteristics of a multistage compressor with inlet pressure distortion (National Aeronautics and Space Administration ;, 1977), by Claude E. DeBogdan, Willis M. Braithwaite, John E. Moss, and United States National Aeronautics and Space Administration (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)
• Performance of a 1.57-pressure-ratio transonic fan stage with a screen-induced 90 ̊circumferential inlet flow distribution (National Aeronautics and Space Administration ;, 1976), by Nelson L. Sanger and Lewis Research Center (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)
• Performance of J33 turbojet engine with shaft-power extraction [Part] 2, Compressor (National Advisory Committee for Aeronautics, 1948), by Albert O. Ross, J. Cary Nettles, J. R. Easterly, United States National Advisory Committee for Aeronautics, and Flight Propulsion Research Laboratory (page images at HathiTrust; US access only)
• Investigation of the performance of a turbojet engine with variable-position compressor inlet guide vanes (National Advisory Committee for Aeronautics, 1955), by Ray E. Budinger, Harold R. Kaufman, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Effect of annular inlet baffles on rotating stall, blade vibration, and performance of an axial-flow compressor in a turbojet engine (National Advisory Committee for Aeronautics, 1955), by Johnson,Donald F., Morgan P. Hanson, Andre J. Meyer, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (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)
• Inlet noise of 0.5-meter-diameter NASA QF-1 fan as measured in an unmodified compressor aerodynamic test facility and in an anechoic chamber (National Aeronautics and Space Administration ;, 1975), by Thomas F. Gelder, Richard F. Soltis, and Lewis Research Center (page images at HathiTrust)

• Hot-flow tests of a series of 10-percent-scale turbofan forced mixing nozzles (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1984), by Verlon L. Head, William H. Gerstenmaier, Louis A. Povinelli, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Design and cold-air test of single-stage uncooled core turbine with high work output (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1980), by Thomas P. Moffitt, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Noise generated by quiet engine fans : III - fan C (U.S. National Aeronautics and Space Administration ;, 1976), by Francis J. Montegani, Ralph F. Schmiedlin, John W. Schaefer, and Lewis Research Center (page images at HathiTrust)
• Mach 4 free-jet tunnel-starting experiments for a hypersonic research engine model causing high blockage (National Aeronautics and Space Administration ;, 1976), by George T. Carson, Raymond E. Midden, and United States National Aeronautics and Space Administration (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)
• Altitude calibration of an F100, S/N P680063, turbofan engine (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)
• Performance of a J85-13 compressor with clean and distorted inlet flow (National Aeronautics and Space Administration ;, 1975), by Edward J. Milner, Leon M. Wenzel, and Lewis Research Center (page images at HathiTrust)
• Performance of two tangential jet blades (National Aeronautics and Space Administration ;, 1970), by James L. Bettner, Lewis Research Center, and General Motors Company (page images at HathiTrust)
• Exhaust emission calibration of two J-58 afterburning turbojet engines at simulated high-altitude, supersonic flight conditions (U.S. National Aeronautics and Space Administration ;, 1976), by J. D. Holdeman and Lewis Research Center (page images at HathiTrust)
• Turbine for a low-cost turbojet engine (National Aeronautics and Space Administration ;, 1974), by Milton G. Kofskey, U.S. Army Air Mobility Research and Development Laboratory, and Lewis Research Center (page images at HathiTrust)
• Investigation of acceleration characteristics of a single-spool turbojet engine (National Advisory Committee for Aeronautics, 1953), by Frank L. Oppenheimer, George J. Pack, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Experimental cooling-air impeller performance and turbine rotor temperatures in modified J33 split-disk rotor up to speeds of 10,000 RPM (National Advisory Committee for Aeronautics, 1952), by Alfred J. Nachtigall, Robert R. Ziemer, Charles F. Zalabak, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Simulated altitude performance of two annular combustors with continuous axial openings for admission of primary air (National Advisory Committee for Aeronautics, 1950), by Eugene V. Zettle, Herman Mark, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Transient operating characteristics of a turbojet engine when subjected to step changes in fuel flow (National Advisory Committee for Aeronautics, 1950), by Arthur H. Bell, J. Elmo Farmer, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Over-all engine performance (National Advisory Committee for Aeronautics, 1948), by J. C. Nettles, J. R. Easterly, United States National Advisory Committee for Aeronautics, and Flight Propulsion Research Laboratory (page images at HathiTrust; US access only)
• Performance and windmilling drag characteristics (National Advisory Committee for Aeronautics, 1948), by William A. Fleming, United States National Advisory Committee for Aeronautics, and Flight Propulsion Research Laboratory (page images at HathiTrust)
• Natural icing of an axial-flow turboject engine in flight for a single icing condition (National Advisory Committee for Aeronautics, 1948), by Loren W. Acker, United States National Advisory Committee for Aeronautics, and Flight Propulsion Research Laboratory (page images at HathiTrust)
• Performance of J33 turbojet engine with shaft-power extraction [Part] 2, Compressor (National Advisory Committee for Aeronautics, 1948), by Albert O. Ross, J. Cary Nettles, J. R. Easterly, United States National Advisory Committee for Aeronautics, and Flight Propulsion Research Laboratory (page images at HathiTrust; US access only)

• Experimental evaluation of a Mach 3.5 axisymmetric inlet (National Aeronautics and Space Administration ;, 1975), by J. Syberg, J. L. Koncsek, Ames Research Center, and Boeing Commercial Airplane Company (page images at HathiTrust)
• NASA TN D-3929 (National Aeronautics and Space Administration ;, 1967), by Jimmy M. Cawthorn, Clyde Hayes, Garland J. Morris, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)

• Fluctuating pressures on fan blades of a turbofan engine : flight test investigation (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by James A. Schoenster and Langley Research Center (page images at HathiTrust)

• Performance of a short modular turbojet combustor segment using ASTM-A1 fuel (National Aeronautics and Space Administration ;, 1971), by Richard W. Niedzwiecki, Harry M. Moyer, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
• Combustion stability of single swirl-can combustor modules using ASTM-A1 liquid fuel (National Aeronautics and Space Administration ;, 1969), by Richard W. Niedzwiecki, Robert E. Jones, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
• Performance of a 48-module swirl-can turbojet combustor segment at high temperatures using ASTM-A1 fuel (National Aeronautics and Space Administration ;, 1969), by Richard W. Niedzwiecki, Harry M. Moyer, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)

• Performance of short length turbojet combustor insensitive to radial distortion of inlet airflow (National Aeronautics and Space Administration ;, 1970), by Francis M. Humenik, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)

• Experimental investigation of external water-spray cooling in a turbojet engine utilizing several injection configurations including orifices in the rotor-blade bases (National Advisory Committee for Aeronautics, 1955), by Roy A. McKinnon, John C. Freche, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Fabrication and endurance of air-cooled strut-supported turbine blades with struts cast of X-40 alloy (National Advisory Committee for Aeronautics, 1956), by Eugene F. Schum, Robert E. Oldrieve, Francis S. Stepka, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Analytical and experimental investigation of a forced-convection air-cooled internal strut-supported turbine blade (National Advisory Committee for Aeronautics, 1954), by Eugene F. Schum, Francis S. Stepka, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)

• Static sea-level performance of an axial-flow-compressor turbojet engine with an air-cooled turbine (National Advisory Committee for Aeronautics, 1955), by Reeves P. Cochran, Robert P. Dengler, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)

• Development of acoustically lined ejector technology for multitube jet noise suppressor nozzles by model and engine tests over a wide range of jet pressure ratios and temperatures (National Aeronautics and Space Administration ;, 1974), by J. Atvars, Lewis Research Center, and Boeing Commercial Airplane Company (page images at HathiTrust)

• NASA TN D-3929 (National Aeronautics and Space Administration ;, 1967), by Jimmy M. Cawthorn, Clyde Hayes, Garland J. Morris, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)

• NASA TN D-4141 (National Aeronautics and Space Administration ;, 1967), by Terrell W. Feistel, Robert C. Innis, United States National Aeronautics and Space Administration, and Ames 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)
• Experimental performance of a 16.10-centimeter-tip-diameter sweptback centrifugal compressor designed for a 6:1 pressure ratio (National Aeronautics and Space Administration ;, 1977), by Hugh A. Klassen, Lawrence F. Schumann, Jerry R. Wood, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Performance of a tandem-rotor/tandem-stator conical-flow compressor designed for a pressure ratio of 3 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Jerry R. Wood, Lawrence F. Schumann, Albert Kimsey Owen, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (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)
• Design and tests of a six-stage axial-flow compressor having a tip speed of 550 feet per second and a flat operating characteristic at constant speed (National Advisory Committee for Aeronautics, 1958), by Willard R. Westphal, John W. Maynard, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Rotating stall investigation of the 0.72 hub-tip ratio single-stage compressor (National Advisory Committee for Aeronautics, 1954), by Robert W. Graham, Vasily D. Prian, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• NACA Wartime Reports. Series E. (National Advisory Committee for Aeronautics, 1944), by J. Austin King, Owen W. Regan, Aircraft Engine Research Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)

More items available under broader and related terms at left.