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Turbines -- Aerodynamics

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• Turbines
• Aerodynamics

• Turbines -- Aerodynamics -- Computer programs
• Turbines -- Aerodynamics -- Computer simulation
• Turbines -- Aerodynamics -- Design and construction
• Turbines -- Aerodynamics -- Mathematical models
• Turbines -- Aerodynamics -- Measurement
• Turbines -- Aerodynamics -- Performance
• Turbines -- Aerodynamics -- Testing
• Gas-turbines -- Aerodynamics
• Steam-turbines -- Aerodynamics
• Turbines -- Blades
• Wind turbines -- Aerodynamics
• Turbines -- Blades -- Aerodynamics

• Cold-air investigation of 4 1/2-stage turbine with stage-loading factor of 4.66 and high specific work output : II - stage group performance (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1980), by Warren J. Whitney, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Crossflow effects on impingement cooling of a turbine vane (National Aeronautics and Space Administration ;, 1974), by James W. Gauntner and Lewis Research Center (page images at HathiTrust)
• Analytical and experimental investigation of stator endwall contouring in a small axial-flow turbine (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by Jeffrey E. Haas, Robert J. Boyle, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Experimental performance and analysis of 15.04-centimeter-tip-diameter, radial-inflow turbine with work factor of 1.126 and thick blading (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Kerry L. McLallin, Jeffrey E. Haas, Propulsion Laboratory (U.S.), Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Off-design performance loss model for radial turbines with pivoting, variable-area stators (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Peter L. Meitner, Arthur J. Glassman, Propulsion Laboratory (U.S.), Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Cold-air performance of compressor-drive turbine of Department of Energy upgraded automobile gas turbine engine (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Richard J. Roelke, Jeffrey E. Haas, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Propulsion Laboratory (U.S.), 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)
• Cold-air performance of a 15.41-cm-tip-diameter axial-flow power turbine with variable-area stator designed for a 75-kW automotive gas turbine engine (National Aeronautics and Space Administration ;, 1982), by Kerry L. McLallin, Robert Y. Wong, Milton G. Kofskey, United States. Dept. of Energy. Office of Vehicle and Engine Research and Development, and Lewis Research Center (page images at HathiTrust)
• Effect of cooling-hole geometry on aerodynamic performance of a film-cooled turbine vane tested with cold air in a two-dimensional cascade (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by John F. Kline, Thomas P. Moffitt, Roy G. Stabe, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Altitude test of several afterburner configurations on a turbofan engine with a hydrogen heater to simulate an elevated turbine discharge temperature (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1977), by Roy L. Johnsen, Richard R. Cullom, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Cold-air performance of a tip turbine designed to drive a lift fan : II, partial admission (National Aeronautics and Space Administration ;, 1977), by Jeffrey E. Haas, Lewis Research Center, U.S. Army Air Mobility Research and Development Laboratory, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Aerodynamic performance of a ceramic-coated core turbine vane tested with cold air in a two-dimensional cascade (National Aeronautics and Space Administration ;, 1975), by Roy G. Stabe, Curt H. Liebert, and Lewis Research Center (page images at HathiTrust)
• Pressure-loss and flow coefficients inside a chordwise-finned, impingement, convection, and film air-cooled turbine vane (National Aeronautics and Space Administration ;, 1974), by Steven A. Hippensteele and Lewis Research Center (page images at HathiTrust)
• Aerodynamic performance of a fully film cooled core turbine vane tested with cold air in a two-dimensional cascade (National Aeronautics and Space Administration ;, 1975), by Roy G. Stabe, John F. Kline, and Lewis Research Center (page images at HathiTrust)
• Cold-air investigation of a 3 1/2-stage fan-drive turbine with a stage loading factor of 4 designed for an integral lift engine (National Aeronautics and Space Administration ;, 1975), by Warren J. Whitney, Frank P. Behning, Harold J. Schum, and Lewis Research Center (page images at HathiTrust)
• Cold-air investigation of first state of 4 1/2-stage, fan-drive turbine with average stage-loading factor of 4.66 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Warren J. Whitney, Frank P. Behning, Thomas P. Moffitt, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Analysis of geometry and design point performance of axial flow turbines Part I Development of the analysis method and the loss coefficient correlation (National Aeronautics and Space Administration, 1968), by A. F. Carter, F. K. Lenber, M. Platt, Lewis Research Center, and Cambridge Northern Research and Engineering Corporation (page images at HathiTrust)
• Analysis of geometry and design point performance of axial flow turbines Part II Computer program (National Aeronautics and Space Administration, 1968), by M. Platt, A. F. Carter, Lewis Research Center, and Cambridge Northern Research and Engineering Corporation (page images at HathiTrust)
• Investigation of a highly loaded multistage fan driven turbine (National Aeronautics and Space Administration ;, 1971), by D. C. Evans, United States National Aeronautics and Space Administration, Lewis Research Center, and General Electric Company (page images at HathiTrust)
• Analytical procedure and computer program for determining the off-design performance of axial flow turbines (National Aeronautics and Space Administration, 1967), by E. E. Flagg (page images at HathiTrust; US access only)
• Study of mean-and turbulent velocity fields in a large-scale turbine-vane passage (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by Douglas A. Bailey, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• NASA TN D-5282 (National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Albert Kaufman, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Aerodynamic evaluation of two-stage axial-flow turbine designed for Brayton-cycle space power system (National Aeronautics and Space Administration ;, 1968), by Milton G. Kofskey, William J. Nusbaum, and Lewis Research Center (page images at HathiTrust)
• Performance in air of 4-inch- (10.16-cm- ) mean-diameter single-stage axial-flow turbine for Reynolds numbers from 4900 to 188,000 (National Aeronautics and Space Administration ;, 1968), by Hugh A. Klassen, Robert Y. Wong, and Lewis Research Center (page images at HathiTrust)
• Effects of specific speed on the experimental performance of a radial-inflow turbine (National Aeronautics and Space Administration ;, 1971), by Milton G. Kofskey, William J. Nusbaum, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5928 (National Aeronautics and Space Administration :, 1970), by David G. Evans, Francis S. Stepka, Keith A. Furgalus, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Acoustic and aerodymanics performance of a variable-pitch 1.83-meter- (6-ft.) diameter 1.20-pressure-ratio fan stage (QF-9) (National Aeronautics and Space Administration ;, 1977), by Frederick W. Glaser, James G. Lucas, Richard P. Woodward, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Experimental results of varying the blade-shroud clearance in a 6.02-inch radial-inflow turbine (National Aeronautics and Space Administration ;, 1970), by Samuel M. Futral and Donald E. Holeski (page images at HathiTrust)
• NASA TN D-6605 (National Aeronautics and Space Administration ;, 1972), by Milton G. Kofskey, William J. Nusbaum, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Procedure for scaling of experimental turbine vane airfoil temperatures from low to high gas temperatures (National Aeronautics and Space Administration, 1971), by Herbert J. Gladden, John N. B. Livingood, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
• Flow through a wire-form transpiration-cooled vane (National Aeronautics and Space Administration ;, 1973), by Albert Kaufman and Lewis Research Center (page images at HathiTrust)
• Investigation of eight-stage bleed-type turbine for hydrogen-propelled nuclear rocket applications (National Aeronautics and Space Administration, 1961), by Harold E. Rohlik and Lewis Research Center (page images at HathiTrust)
• Investigation of eight-stage bleed-type turbine for hydrogen-propelled nuclear rocket applications (National Aeronautics and Space Administration, 1961), by Harold E. Rohlik and Lewis Research Center (page images at HathiTrust)
• Investigation of transonic turbine designed for zero diffusion of suction-surface velocity (National Advisory Committee for Aeronautics, 1954), by Warren J. Whitney, R. Y. Wong, Daniel E. Monroe, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• One-dimensional analysis of choked-flow turbines (National Advisory Committee for Aeronautics, 1952), by Robert E. English, Richard H. Cavicchi, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Experimental investigation of loss in an annular cascade of turbine-nozzle blades of free vortex design (National Advisory Committee for Aeronautics, 1953), by Hubert W. Allen, Richard E. Chamness, Milton G. Kofskey, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Design and experimental investigation of a high-weight-flow low-pressure-ratio turbine (National Aeronautics and Space Administration, 1959), by Donald A. Petrash, Charles A. Wasserbauer, Robert R. Nunamaker, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Research on turbine rotor-stator aerodynamic interaction and rotor negative incidence stall (Wright-Patterson Air Force Base, Ohio : Aero Propulsion Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1981., 1981), by Robert P. Dring, J. H. Wanger, H. David Joslyn, L. W. Hardin, Air Force Wright Aeronautical Laboratories, Air Force Aero Propulsion Laboratory (U.S.), and United Technologies Research Center (page images at HathiTrust)
• Low Reynold number turbine blade cascade calculations (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1996., 1996), by Richard Byram Rivir, Elizabeth Ervin, Michael Dahlstom, Rolf Sondergaard, Air Force Flight Dynamics Laboratory (U.S.), and Air Force Wright Aeronautical Laboratories (page images at HathiTrust)

• Computer code for off-design performance analysis of radial-inflow turbines with rotor blade sweep (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Peter L. Meitner, Arthur J. Glassman, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• A Fortran IV program to estimate the off-design performance of radial-inflow turbines (National Aeronautics and Space Administration ;, 1969), by Carroll A. Todd, Samuel M. Futral, and Lewis Research Center (page images at HathiTrust)

• FORTRAN program for predicting off-design performance of radial-inflow turbines (National Aeronautics and Space Administration ;, 1975), by Charles A. Wasserbauer, Arthur J. Glassman, and Lewis Research Center (page images at HathiTrust)

• Experimental investigation of partial- and full-admission characteristics of a two-stage velocity-compounded turbine (National Aeronautics and Space Administration, 1960), by Thomas P. Moffitt, Frederick W. Klag, and Lewis Research Center (page images at HathiTrust)

• Exact analytical solution to a transient conjugate heat-transfer problem (National Aeronautics and Space Administration ;, 1973), by James Sucec and Lewis Research Center (page images at HathiTrust)

• Velocity surveys in a turbine stator annular-cascade facility using laser Doppler techniques (National Aeronautics and Space Administration ;, 1976), by Louis J. Goldman, Kerry L. McLallin, Richard G. Seasholtz, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)

• Experimental investigation of partial- and full-admission characteristics of a two-stage velocity-compounded turbine (National Aeronautics and Space Administration, 1960), by Thomas P. Moffitt, Frederick W. Klag, and Lewis Research Center (page images at HathiTrust)

• Experimental investigation of the partial- admission performance characteristics of a single-stage Mach 2 supersonic turbine (National Aeronautics and Space Administration, 1959), by Thomas P. Moffitt, Frederick W. Klag, and Langley Research Center (page images at HathiTrust)
• Design and experimental investigation of a single-stage turbine with a rotor entering relative Mach number of 2 (National Advisory Committee for Aeronautics, 1958), by Thomas P. Moffitt, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)

• Cold-air study of the effect on turbine stator blade aerodynamic performance of coolant ejection from various trailing-edge slot geometries (National Aeronautics and Space Administration ;, 1974), by Herman W. Prust, Wayne M. Bartlett, and Lewis Research Center (page images at HathiTrust)
• Cold-air annular-cascade investigation of aerodynamic performance of cooled turbine vanes (National Aeronautics and Space Administration ;, 1974), by Louis J. Goldman, Kerry L. McLallin, and Lewis Research Center (page images at HathiTrust)
• Method of predicting radiation heat transfer in turbine-cooling test facilities (National Aeronautics and Space Administration ;, 1975), by Herbert J. Gladden, Curt H. Liebert, and Lewis Research Center (page images at HathiTrust)
• An observation on tone cut-off in static test data from jet engine fans (National Aeronautics and Space Administration ;, 1975), by Marcus F. Heidmann and Lewis Research Center (page images at HathiTrust)
• Effect of free-stream turbulence on film cooling (National Aeronautics and Space Administration ;, 1975), by Cecil J. Marek, Robert R. Tacina, and Lewis Research Center (page images at HathiTrust)
• Aerodynamic performance of 0.5-meter-diameter, 337-meter-per-second tip speed, 1.5-pressure-ratio, single-stage fan designed for low noise aircraft engines (National Aeronautics and Space Administration ;, 1974), by Thomas F. Gelder, George W. Lewis, and Lewis Research Center (page images at HathiTrust)
• NASA TN D-5783 (National Aeronautics and Space Administration :, 1970), by Robert L. Dreshfield, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-6702 (National Aeronautics and Space Administration :, 1972), by Arthur J. Glassman, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Coolant pressure and airflow distribution in a strut-supported transpiration-cooled vane for a gas turbine engine (National Aeronautics and Space Administration ;, 1972), by Albert Kaufman, Hadley T. Richards, David J. Poferl, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
• Effect of a reduction in blade thickness on performance of a single-stage 20.32-centimeter mean-diameter turbine (National Aeronautics and Space Administration ;, 1973), by William J. Nusbaum, Milton G. Kofskey, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
• Flow measurement in base cooling air passages of a rotating turbine blade (National Aeronautics and Space Administration ;, 1974), by Curt H. Liebert, Frank G. Pollack, and Lewis Research Center (page images at HathiTrust)
• Effect of pressure ratio and inlet pressure on performance of experimental gas turbine at inlet temperature of 800 degrees R (National Advisory Committee for Aeronautics, 1948), by Robert C. Kohl, Robert G. Larkin, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Cooling of gas turbines [Part] 2, effectiveness of rim cooling of blades (National Advisory Committee for Aeronautics, 1947), by L. Wolfenstein, John S. McCarthy, Gene L. Meyer, United States National Advisory Committee for Aeronautics, and Aircraft Engine Research Laboratory (page images at HathiTrust)
• Cooling of gas turbines [Part] 4, Calculated temperature distribution in the trailing part of a turbine blade using direct liquid cooling (National Advisory Committee for Aeronautics, 1947), by W. Byron Brown, William R. Monroe, United States National Advisory Committee for Aeronautics, and Aircraft Engine Research Laboratory (page images at HathiTrust)
• Cooling of gas turbines [Part] 8, Theoretical temperature distributions through gas turbine with special blades and cooling fins on the rim (National Advisory Committee for Aeronautics, 1948), by W. Byron Brown, John N. B. Livingood, United States National Advisory Committee for Aeronautics, and Flight Propulsion Research Laboratory (page images at HathiTrust)
• Cooling of gas turbines [Part] 5, Effectiveness of air cooling of hollow blades (National Advisory Committee for Aeronautics, 1947), by L. Wolfenstein, John S. McCarthy, Robert L. Maxwell, United States National Advisory Committee for Aeronautics, and Aircraft Engine Research Laboratory (page images at HathiTrust)
• Cooling of gas turbines [Part] 3, Analysis of rotor and blade temperatures in liquid-cooled gas turbines (National Advisory Committee for Aeronautics, 1947), by W. Byron Brown, John N. B. Livingood, United States National Advisory Committee for Aeronautics, and Aircraft Engine Research Laboratory (page images at HathiTrust)
• The use of nickel-base alloys in the rotating parts of gas turbines for aerospace applications (Columbus, Ohio : Battelle Memorial Institute, Defense Metals Information Center, 1962., 1962), by C. H. Lund and Defense Metals Information Center (U.S.) (page images at HathiTrust)
• Flow transition in gas turbine airfoil boundary layers: fundamentals and empiricisms (Wright-Patterson Air Force Base, Ohio : Aero Propulsion Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1985., 1985), by Gregory S. West, Lit S. Han, Air Force Wright Aeronautical Laboratories, and University of Dayton. Research Institute (page images at HathiTrust)

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