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Axial flow compressors -- Blades -- Testing

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• Axial flow compressors -- Blades
• Compressors -- Blades -- Testing
• Axial flow compressors -- Testing
• Blades -- Testing

• Investigation of an impulse axial-flow compressor rotor over a range of blade angles (National Advisory Committee for Aeronautics, 1950), by Wallace M. Schulze, Willard R. Westphal, John R. Erwin, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Design, over-all performance and stall characteristics (National Advisory Committee for Aeronautics, 1954), by George W. Lewis, G. K. Serovy, Francis C. Schwenk, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)

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

• 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)
• Some methods of analyzing the effect of basic design variables on axial-flow-compressor performance (National Advisory Committee for Aeronautics, 1947), by John T. Sinnette, United States National Advisory Committee for Aeronautics, and Flight Propulsion Research Laboratory (page images at HathiTrust)
• Preliminary investigation of hollow-bladed turbines having closed and open blade tips (National Advisory Committee for Aeronautics, 1955), by Gordon T. Smith, Robert O. Hickel, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Performance of compressor blade cascades at high Mach numbers (National Advisory Committee for Aeronautics, 1947), by Seymour M. Bogdonoff, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• NACA 65-series compressor rotor performance with varying annulus-area ratio, solidity, blade angle, and Reynolds number and comparison with cascade results (National Advisory Committee for Aeronautics, 1953), by Wallace M. Schulze, George C. Ashby, John R. Erwin, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• A comparison of typical National Gas Turbine Establishment and NACA axial-flow compressor blade sections in cascade at low speed (National Advisory Committee for Aeronautics, 1953), by A. Richard Felix, James C. Emery, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Two-dimensional low-speed cascade investigation of NACA compressor blade sections having a systematic variation in mean-line loading (National Advisory Committee for Aeronautics, 1953), by John R. Erwin, James C. Emery, Melvyn Savage, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Experimental investigation of an axial-flow supersonic compressor having sharp leading-edge blades with an 8-percent mean thickness-chord ratio (National Advisory Committee for Aeronautics, 1955), by Theodore J. Goldberg, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Analysis of aerodynamic blade-loading-limit parameters for NACA 65-(C[sub zeta]₀A₁₀) 10 compressor-blade sections at low speeds (National Advisory Committee for Aeronautics, 1955), by Melvyn Savage, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Experimental and theoretical distribution of flow produced by inlet guide vanes of an axial-flow compressor (National Advisory Committee for Aeronautics, 1949), by Harold B. Finger, Howard A. Buckner, Harold J. Schum, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Analysis of the effects of design pressure ratio per stage and off-design efficiency on the operating range of multistage axial-flow compressors (National Advisory Committee for Aeronautics, 1950), by Melvyn Savage, Willard R. Westphal, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Analysis of an axial compressor stage with infinitesimal and finite blade spacing (National Advisory Committee for Aeronautics, 1951), by H. J. Reissner, L. Meyerhoff, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Application of a channel design method to high-solidity cascades and tests of an impulse cascade with 90° of turning (National Advisory Committee for Aeronautics, 1952), by John D. Stanitz, Leonard J. Sheldrake, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Experimental investigation of a transonic compressor cascade and test results for four blade sections (National Aeronautics and Space Administration, 1960), by James C. Emery, Willard R. Westphal, James C. Dunavant, and United States National Aeronautics and Space Administration (page images at HathiTrust)

• Influence of wall boundary layer upon the performance of an axial-flow fan rotor (National Advisory Committee for Aeronautics, 1947), by Emanuel Boxer, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)

• Resonant frequency tester : a machine using measurement of frequency decay for quality evaluation of axial flow compressor blades (Union Carbide Nuclear Company, Oak Ridge Gaseous Diffusion Plant, 1960), by E. R. Taylor, C. H. Mahoney, C. R. Lay, Oak Ridge Gaseous Diffusion Plant, Union Carbide Nuclear Company, and U.S. Atomic Energy Commission (page images at HathiTrust)

• Effects of inlet-guide-vane configuration and relative blade velocity on noise from axial-flow compressors (National Aeronautics and Space Administration ;, 1970), by David Chestnutt, Lorenzo R. Clark, and Langley Research Center (page images at HathiTrust)

• Compressor-blade vibration and performance in a J47-23 turbojet engine under conditions of rotating stall (National Advisory Committee for Aeronautics, 1955), by Morgan P. Hanson, Andre J. Meyer, Donald F. Johnson, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Compressor-blade vibration of a J57-P-1 turbojet engine during exploratory operation with inlet-pressure distortions (National Advisory Committee for Aeronautics, 1955), by Morgan P. Hanson, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)

• Off-design correlation for losses due to part-span dampers on transonic rotors. (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by William B. Roberts, Donald M. Sandercock, James E. Crouse, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Overall and blade-element performance of a 1.20-pressure-ratio fan stage at design blade setting angle (National Aeronautics and Space Administration ;, 1974), by George W. Lewis, Edward R. Tysl, and Lewis Research Center (page images at HathiTrust)
• Overall and blade element performance of a 1.20-pressure-ratio fan stage with rotor blades reset -5 ̊ (U.S. National Aeronautics and Space Administration ;, 1976), by George W. Lewis, Royce D. Moore, Walter Martin Osborn, and Lewis Research Center (page images at HathiTrust)
• Overall and blade element performance of a 1.20 pressure ratio fan stage with rotor blades reset -7 ̊ (U.S. National Aeronautics and Space Administration ;, 1976), by George W. Lewis, George Kovich, and Lewis Research Center (page images at HathiTrust)

• Design and performance of a high-pressure-ratio, highly loaded axial-flow transonic compressor space (National Aeronautics and Space Administration ;, 1974), by George W. Lewis, Edward R. Tysl, Lonnie Reid, 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)
• Performance of a transonic compressor rotor with an aspect ratio of 6.5 (National Aeronautics and Space Administration ;, 1974), by Lonnie Reid, Edward R. Tysl, and Lewis 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)

• Development and testing of a pneumatic scraper blade for conveyor belt cleaning (U.S. Dept. of the Interior, Bureau of Mines, 1989), by C. A. Rhoades, T. L. Hebble, and S. G. Grannes (page images at HathiTrust)
• Surface pressure measurements at two tips of a model helicopter rotor in hover (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1980), by R. B. Gray, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Development and testing of a pneumatic scraper blade for conveyor belt cleaning (U.S. Dept. of the Interior, Bureau of Mines, 1989), by C. A. Rhoades, T. L. Hebble, and S. G. Grannes (page images at HathiTrust)

• Effect of hole geometry and electric-discharge machining (EDM) on airflow rates through small-diameter holes in turbine-blade material (National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1980), by Steven A. Hippensteele and Reeves P. Cochran (page images at HathiTrust)
• Flow visualization of discrete-hole film cooling with a spanwise injection over a cylinder (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by Louis M. Russell, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Gas turbine ceramic-coated-vane concept with convection-cooled porus metal core (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Albert F. Kascak, Lewis Research Center, Propulsion Laboratory (U.S.), and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Turbine engine diagnostics system study (FAA Technical Center ;, 1991), by Barbara K. McQuiston, Ronald L. De Hoff, Inc Systems Control Technology, and Federal Aviation Administration Technical Center (U.S.) (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)

• Fluctuating pressures on fan blades of a turbofan engine : static and wind-tunnel investigations (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by James A. Schonester, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Langley Research Center (page images at HathiTrust)

• Stagnation region gas film cooling : spanwise angled injection from multiple rows of holes (National Aeronautics and Space Administration ;, 1981), by D. W. Luckey, M. R. L'Ecuyer, Lewis Research Center, Purdue University. Thermal Sciences and Propulsion Center, United States National Aeronautics and Space Administration, and United States. Office of Naval Research (page images at HathiTrust)

• An evaluation of three oxidation-resistant alloy claddings for IN 100 and WI 52 superalloys (National Aeronautics and Space Administration ;, 1969), by Michael A. Gedwill, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
• A nickel-base alloy, NASA WAZ-16, with potential for gas turbine stator vane application (National Aeronautics and Space Administration ;, 1974), by William J. Waters, John C. Freche, and Lewis Research Center (page images at HathiTrust)
• Factors affecting miniature Izod impact strength of tungsten-fiber-metal-matrix composites (National Aeronautics and Space Administration ;, 1973), by Edward A. Winsa, Donald W. Petrasek, and Lewis Research Center (page images at HathiTrust)
• Stress-rupture strength and microstructural stability of tungsten-hafnium-carbon-wire-reinforced superalloy composites (National Aeronautics and Space Administration ;, 1974), by Donald W. Petrasek, Robert A. Sigorelli, and Lewis Research Center (page images at HathiTrust)

• Nonlinear, three-dimensional finite-element analysis of air-cooled gas turbine blades (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1980), by Albert Kaufman, Raymond E. Gaugler, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Durability of zirconia thermal-barrier ceramic coatings on air-cooled turbine blades in cyclic jet engine operation (National Aeronautics and Space Administration ;, 1976), by Lewis Research Center, Curt H. Liebert, and United States National Aeronautics and Space Administration (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)
• Performance evaluation of modified jet-flap rotor blade. (National Aeronautics and Space Administration, 1971), by H. G. Lueders, United States National Aeronautics and Space Administration, Lewis Research Center, and General Motors Corporation (page images at HathiTrust)
• Performance evaluation of plain rotor blade with plow type vortex generators (National Aeronautics and Space Administration, 1969), by H. G. Lueders (page images at HathiTrust)
• Experimental investigation of advanced concepts to increase turbine blade loading : II. performance evaluation of plain rotor blade (National Aeronautics and Space Administration, 1968), by H. G. Lueders (page images at HathiTrust; US access only)
• Performance evaluation of jet-flap rotor blade (National Aeronautics and Space Administration, 1970), by H. G. Lueders, United States National Aeronautics and Space Administration, Lewis Research Center, and General Motors Corporation (page images at HathiTrust)
• Performance evaluation of modified tandem rotor blade (National Aeronautics and Space Administration, 1970), by H. G. Lueders, United States National Aeronautics and Space Administration, Lewis Research Center, and General Motors Corporation (page images at HathiTrust)
• Performance evaluation of a two-stage turbine designed for a ratio of blade speed to jet speed of 0.146 (National Aeronautics and Space Administration, 1960), by Milton G. Kofskey, Lewis Research Center, and United States National Aeronautics and Space Administration (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)

More items available under broader and related terms at left.