The Online Books Page

Compressors -- Blades -- Testing

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

Broader terms:

Narrower term:

Axial flow compressors -- Blades -- Testing

Filed under: Compressors -- Blades -- Testing

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)

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: Compressors -- Blades

Improved resistance to engine bird ingestion : final report : prepared for U.S. Dept. of Transportation, Federal Aviation Administration, Systems Research and Development Service (Dept. of Transportation, Federal Aviation Administration, Systems Research and Development Service ;, 1977), by Herbert B. Kaehler, Avco Corporation. Avco Lycming Division, and United States. Federal Aviation Administration. Systems Research and Development Service (page images at HathiTrust)
Computed moisture interception on helicopter rotor blades (Cornell Aeronautical Laboratory, Inc., 1958), by Charles E. Treanor and Marcia J. Williams (page images at HathiTrust)
Aerodynamic performances of three fan stator designs operating with rotor having tip speed of 337 meters per second and pressure ratio of 1.54 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1980), by Thomas F. Gelder, Genevieve M. Esgar, James F. Schmidt, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust; US access only)
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)
Effects of tip clearance on overall performance of transonic fan stage with and without casing treatment (National Aeronautics and Space Administration ;, 1977), by Royce D. Moore, Walter Martin Osborn, 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)
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)
Performance of low-pressure ratio fan stage at two off-design blade setting (National Aeronautics and Space Administration ;, 1977), by George Kovich, Royce D. Moore, Edward R. Tysl, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Laser anemometer measurements in an annular cascade of core turbine vanes and comparison with theory (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Louis J. Goldman, Richard G. Seasholtz, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
Analytic investigation of effect of end-wall contouring on stator performance (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Robert J. Boyle, Louis J. Goldman, Harold E. Rholik, and Lewis Research Center (page images at HathiTrust)
Performance comparisons of high mach number compressor rotor blading (National Aeronautics and Space Administration ;, 1968), by J. P. Gostelow, L. H. Smith, K. W. Krabacher, Lewis Research Center, General Electric Company, and United States National Aeronautics and Space Administration (page images at HathiTrust)
Some observations of the effects of radial distortions on performance of a transonic rotating blade row (National Aeronautics and Space Administration ;, 1974), by Donald M. Sandercock, Nelson L. Sanger, and Lewis Research Center (page images at HathiTrust)
Effects of long-chord acoustically treated stator vanes on fan noise (National Aeronautics and Space Administration ;, 1975), by James H. Dittmar and Lewis Research Center (page images at HathiTrust)
NASA TN D-5506 (National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Walter Martin Osborn, George W. Lewis, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Two-dimensional analytical and experimental performance comparison for a compressor stator section with d-factor of 0.47 (National Aeronautics and Space Administration ;, 1973), by Nelson L. Sanger and Lewis Research Center (page images at HathiTrust)
Effect of several porous casing treatments on stall limit and on overall performance of an axial-flow compressor rotor (National Aeronautics and Space Administration ;, 1971), by Walter Martin Osborn, Laurence J. Heidelberg, George W. Lewis, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
NASA TN D-6264 (National Aeronautics and Space Administration:, 1971), by Nelson L. Sanger (page images at HathiTrust; US access only)
Effects of increased leading-edge thickness on performance of a transonic rotor blade (National Aeronautics and Space Administration ;, 1973), by Lonnie Reid, Donald C. Urasek, and Lewis Research Center (page images at HathiTrust)
NASA TN D-6321 (National Aeronautics and Space Administration ;, 1971), by William J. McCroskey, U.S. Army Air Mobility Research and Development Laboratory, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
Performance of a straight stator and a tilted stator tested with a high-solidity high-pressure-ratio transonic rotor (National Aeronautics and Space Administration, 1959), by Ralph L. Schacht, Arthur W. Goldstein, Richard R. Cullom, and Lewis Research Center (page images at HathiTrust)
Some effects of blade trailing-edge thickness on performance of a single-stage axial-flow compressor (National Advisory Committee for Aeronautics, 1951), by J. J. Moses, G. K. Serovy, 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)
Preliminary engine investigation (National Advisory Committee for Aeronautics, 1949), by Andre J. Meyer, Howard F. Calvert, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
Dynamic investigation (National Advisory Committee for Aeronautics, 1949), by Andre J. Meyer, Howard F. Calvert, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
Comparison of experimentally and analytically determined windmilling characteristics of a compressor with low over-all pressure ratio (National Advisory Committee for Aeronautics, 1958), by James E. Hatch, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Comparison of NACA 65-series compressor-blade pressure distributions and performance in a rotor and in cascade (National Advisory Committee for Aeronautics, 1951), by Willard R. Westphal, William R. Godwin, 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)
Low-speed cascade investigation of loaded leading-edge compressor blades (National Advisory Committee for Aeronautics, 1956), by James C. Emery, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
Two-dimensional compressible flow in centrifugal compressors with logarithmic-spiral blades (National Advisory Committee for Aeronautics, 1951), by Gaylord O. Ellis, John D. Stanitz, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Effect of Mach number on the flow and application of compressibility corrections in a two-dimensional subsonic-transonic compressor cascade having varied porous-wall suction at the blade tips (National Advisory Committee for Aeronautics, 1952), by William B. Briggs and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
Die casting of compressor blades (Doehler-Jarvis Division, National Lead Company, Research and Engineering Dept., 1962), by G. F. Hodgson, National Lead Company. Doehler-Jarvis Division, Goodyear Atomic Corporation, and U.S. Atomic Energy Commission (page images at HathiTrust; US access only)
Improved resistance to engine bird ingestion (Dept. of Transportation, Federal Aviation Administration, Systems Research and Development Service ;, 1977), by Herbert B. Kaehler, Aviation Manufacturing Corporation. Lycoming Division, and United States. Federal Aviation Administration. Systems Research and Development Service (page images at HathiTrust)

Filed under: Compressors -- Blades -- Aerodynamics

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)

Filed under: Compressors -- Blades -- Computer simulation

Estimation of deviation angle for axial-flow compressor blade sections using inviscid-flow solutions (National Aeronautics and Space Administration ;, 1974), by Max J. Miller and Lewis Research Center (page images at HathiTrust)

Filed under: Compressors -- Blades -- Materials

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)

Filed under: Compressors -- Blades -- Mathematical models

Differential analysis for the turbulent boundary layer on a compressor blade element (including boundary-layer separation) (National Aeronautics and Space Administration ;, 1974), by James F. Schmidt, Carroll A. Todd, and Lewis Research Center (page images at HathiTrust)

Filed under: Compressors -- Blades -- Noise

LF336 lift fan modification and acoustic test program (National Aeronautics and Space Administration ;, 1971), by S. B. Kazin, L. J. Volk, Ames Research Center, and General Electric Company (page images at HathiTrust)

Filed under: Compressors -- Blades -- Statistics

Aerodynamic performance of a 1.25-pressure-ratio axial-flow fan stage (National Aeronautics and Space Administration ;, 1974), by Royce D. Moore, Ronald J. Steinke, and Lewis Research Center (page images at HathiTrust)

Filed under: Compressors -- Blades -- Vibration

Friction and wear under fretting conditions of materials for use as wire friction dampers of compressor blade vibration (National Aeronautics and Space Administration ;, 1968), by Max A. Swikert, Robert L. Johnson, and Lewis Research Center (page images at HathiTrust)
Preliminary engine investigation (National Advisory Committee for Aeronautics, 1949), by Andre J. Meyer, Howard F. Calvert, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
Dynamic investigation (National Advisory Committee for Aeronautics, 1949), by Andre J. Meyer, Howard F. Calvert, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
Effect of centrifugal force on flutter of uniform cantilever beam at subsonic speeds with application to compressor and turbine blades (National Advisory Committee for Aeronautics, 1949), by Alexander Mendelson 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)

More items available under broader and related terms at left.

Help with reading books -- Report a bad link -- Suggest a new listing

Home -- Search -- New Listings -- Authors -- Titles -- Subjects -- Serials

Books -- News -- Features -- Archives -- The Inside Story

Edited by John Mark Ockerbloom (onlinebooks@pobox.upenn.edu)
OBP copyrights and licenses.