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Axial flow compressors -- Testing

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Filed under: Axial flow compressors -- Testing

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)

Filed under: Axial flow compressors -- Testing -- Statistics

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)

Filed under: Axial flow compressors -- 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.

Filed under: Axial flow compressors

Preliminary study of three-dimensional rotating stall (Wright Air Development Center, Air Research and Development Command, United States Air Force, Wright-Patterson Air Force Base, 1959), by F. K. Moore, Armed Services Technical Information Agency (U.S.), and Wright Air Development Center (page images at HathiTrust)
Effects of reset stators and a rotating, grooved stator hub on performance of a 1.92-pressure-ratio compressor stage (National Aeronautics and Space Administration ;, 1977), by George W. Lewis, Lonnie Reid, Donald C. Urasek, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Effect of casing treatment on overall performance of axial-flow transonic fan stage with pressure ratio of 1.75 and tip solidity of 1.5 (National Aeronautics and Space Administration ;, 1977), by Walter M. Osborn, Royce D. Moore, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Effect of damper on overall and blade-element performance of a compressor rotor having a tip speed of 1151 feet per second and an aspect ratio of 3.6 (National Aeronautics and Space Administration ;, 1974), by George W. Lewis, Roy D. Hager, and Lewis Research Center (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)
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 inlet stage of transonic compressor (National Aeronautics and Space Administration ;, 1976), by Donald C. Urasek, George W. Lewis, Ronald J. Steinke, and Lewis Research Center (page images at HathiTrust)
Research and development of high-performance axial-flow turbomachinery (National Aeronautics and Space Administration, 1968), by J. T. McCabe, P. W. Curwen, P. Bolan, United States National Aeronautics and Space Administration, Lewis Research Center, and Pratt & Whitney Aircraft Company (page images at HathiTrust)
NASA CR-1456 (National Aeronautics and Space Administration ;, 1969), by A. F. Carter, F. K. Lenherr, United States National Aeronautics and Space Administration, Lewis Research Center, and Northern Research and Engineering Corporation (page images at HathiTrust)
Experimental and theoretical investigation of three-dimensional turbulent boundary layers and turbulence characteristics inside an axial flow inducer passage (National Aeronautics and Space Administration ;, 1977), by A. K. Anand, B. Lakshminarayana, Pennsylvania State University, and United States National Aeronautics and Space Administration (page images at HathiTrust)
NASA TN D-2481 (National Aeronautics and Space Administration :, 1964), by James E. Crouse, Donald M. Sandercock, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
NASA TN D-2482 (National Aeronautics and Space Administration :, 1964), by David L. Block, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Effects of four inlet and outlet tip-annulus-area blockage configurations on the performance of an axial-flow fan rotor (National Aeronautics and Space Administration ;, 1976), by Walter Martin Osborn, Roy D. Hager, and Lewis Research Center (page images at HathiTrust)
Stalled and stall-free performance of axial-flow compressor stage with three inlet-guide-vane and stator-blade settings (National Aeronautics and Space Administration ;, 1977), by Donald C. Urasek, Walter S. Cunnan, Ronald J. Steinke, and Lewis Research Center (page images at HathiTrust)
Computer program for definition of transonic axial flow compressor blade rows (National Aeronautics and Space Administration ;, 1974), by James E. Crouse and Lewis Research Center (page images at HathiTrust)
NASA TN D-3089 (National Aeronautics and Space Administration ;, 1966), by John N. Dickson, Richard H. Brolliar, George C. Marshall Space Flight Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Graphite-polyimide composite for application to aircraft engines (National Aeronautics and Space Administration ;, 1974), by Morgan P. Hanson, C. C. Chamis, and Lewis Research Center (page images at HathiTrust)
Determination of surge and stall limits of an axial-flow turbojet engine for control applications (National Advisory Committee for Aeronautics, 1953), by Ross D. Schmidt, Edward W. McGraw, George Vasu, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
Performance of supersonic axial-flow compressors based on one-dimensional analysis (National Advisory Committee for Aeronautics, 1949), by Linwood C. Wright, John F. Klapproth, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (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)
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)
Investigation of an impulse axial-flow compressor (National Advisory Committee for Aeronautics, 1950), by John R. Erwin, Wallace M. Schulze, Langley Aeronautical Laboratory, and United States. National Adviosry 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)
Isolated and cascade airfoils with prescribed velocity distribution (National Advisory Committee for Aeronautics, 1947), by John M. Riebs, Meyer Jerison, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
NACA Wartime Reports. Series E. (National Advisory Committee for Aeronautics, 1944), by John T. Sinnette, J. Austin King, Oscar W. Schey, Aircraft Engine Research Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Research on rotating stall in axial flow compressors. Part II, On the separation of the unsteady laminar boundary layer (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1959., 1959), by R. A. Hartunian, F. K. Moore, Wright Air Development Center, United States. Air Force. Air Research and Development Command, and Armed Services Technical Information Agency (U.S.) (page images at HathiTrust)
Experiments on laminar separation from a moving wall (Wright-Patterson Air Force Base, Ohio : Wright Air Development Center, Air Research and Development Command, United States Air Force, 1959., 1959), by Robert J. Vidal, Wright Air Development Center, and United States. Air Force. Air Research and Development Command (page images at HathiTrust)
Experimental investigation of a supersonic compressor cascade (Wright-Patterson Air Force Base, Ohio : Aerospace Research Laboratories, Air Force Systems Command, United States Air Force, 1975., 1975), by Sanford Fleeter, George T. Sinnet, Robert B. McClure, Robert L. Holtman, Aerospace Research Laboratories (U.S.), and General Motors Corporation. Detroit Diesel Allison Division (page images at HathiTrust)

Filed under: Axial flow compressors -- Aerodynamics

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)
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)
Laser anemometer measurements in a transonic axial-flow fan rotor (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1989), by Anthony J. Strazisar and Lewis Research Center (page images at HathiTrust)
Modifications to MacCormack's 2-D Navier-Stokes compression ramp code for application to flows with axes of symmetry and wall mass transfer (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1981., 1981), by Richard G. Hindman, Edward J. Marquart, Bob L. Uselton, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
Numerical stability analysis of a compressor model (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1982., 1982), by K. C. Reddy, Yeng-Yung Tsui, University of Tennessee (System). Space Institute, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)

Filed under: Axial flow compressors -- Altitude, Influence of

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)

Filed under: Axial flow compressors -- Blades

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)

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