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Cascades (Fluid dynamics)

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• Aerodynamics
• Fluid dynamics

• Cascades (Fluid dynamics) -- Computer programs
• Cascades (Fluid dynamics) -- Computer simulation
• Cascades (Fluid dynamics) -- Mathematical models

• Aerofoils in cascade
• Cascade theory (Dynamics)

• The calculation of the pressure distribution on a cascade of thick airfoils by means of Fredholm integral equations of the second kind (National Aeronautics and Space Administration; for sale by: National Technical Information Service, Springfield, Va., 1971), by Erich Martensen (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)
• Incidence loss for a core turbine rotor blade in a two-dimensional cascade (National Aeronautics and Space Administration ;, 1974), by Roy G. Stabe, John F. Kline, and Lewis Research Center (page images at HathiTrust)
• Evaluation of diffuse-illumination holographic cinematography in a flutter cascade (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1986), by Arthur J. Decker and Lewis Research Center (page images at HathiTrust)
• Experimental transient turbine vane temperatures in a cascade for gas stream temperature cycling between 922 and 1644 K (1200 ̊and 2500 ̊F) (National Aeronautics and Space Administration ;, 1974), by Daniel J. Gauntner, Albert Kaufman, 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)
• 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)
• A cascade investigation of a convection- and film-cooled turbine vane made from radially stacked laminates (National Aeronautics and Space Administration ;, 1974), by Herbert J. Gladden and Lewis Research Center (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)
• Effect on fan flow characteristics of length and axial location of a cascade thrust reverser (National Aeronautics and Space Administration ;, 1975), by Donald A. Dietrich, Gary G. Kelm, Andrew J. Crooker, 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)
• 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)
• Flow visualization study of the horseshoe vortex in a turbine stator cascade (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Raymond E. Gaugler, Louis M. Russell, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Navier-Stokes analysis of transonic cascade flow (National Aeronautics and Space Administration ;, 1990), by A. Arnone, Louis A. Povinelli, M. S. Liou, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Multigrid calculation of three-dimensional viscous cascade flows (NASA, Institute for Computational Mechanics in Propulsion, Lewis Research Center, ;, 1991), by Andrea Arnone, Louis A. Povinelli, M. S. Liou, and Lewis Research Center. Institute for Computational Mechanics in Propulsion (page images at HathiTrust)
• CAS22 - FORTRAN program for fast design and analysis of sock-free airfoil cascades using fictitious-gas concept (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by George S. Dulikravich, Helmut Sobieczy, Universities Space Research Association, DFVLR--Institute fur̈ Theoretische Strom̈ungsmechanik, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Lewis Research Center (page images at HathiTrust)
• Cascade tests of serrated leading edge blading at high subsonic speeds (National Aeronautics and Space Administration ;, 1974), by E. G. Smith, H. D. Sowers, Ames Research Center, and General Electric Company (page images at HathiTrust)
• Highly loaded multi-stage fan drive turbine : cascade test program (National Aeronautics and Space Administration ;, 1973), by D. G. Cherry, M. W. Thomas, T. K. Staley, Lewis Research Center, and General Electric Company (page images at HathiTrust)
• Finite element analysis of transonic flows in cascades : importance of computational grids in improving accuracy and convergence (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Akin Ecer, Hasan U. Akay, IUPUI (Campus), United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, 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)
• Flow of gas through turbine lattices (Langley Memorial Aeronautical Laboratory, 1956), by M. E. Deĭch, United States National Advisory Committee for Aeronautics, and Langley Aeronautical Laboratory (page images at HathiTrust)
• Flat plate cascades at supersonic speed (NACA, 1956), by Rashad M. El Badrawy and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Status of the Los Alamos Scientific Laboratory Monte Carlo intranuclear cascade calculation (1964) (Los Alamos Scientific Laboratory of the University of California ;, 1965), by Stanley L. Whetstone, R. L. Bivens, U.S. Atomic Energy Commission, and Los Alamos Scientific Laboratory (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)
• 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)
• 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)
• A variable-geometry annular cascade-type inlet at Mach numbers of 1.9 and 3.05 (National Advisory Committee for Aeronautics, 1956), by James F. Connors, Rudolph C. Meyer, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory 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)
• Design method for two-dimensional channels for compressible flow with application to high-solidity cascades (National Advisory Committee for Aeronautics, 1949), by Sumner Alpert and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Attainable circulation of airfoils in cascade (National Advisory Committee for Aeronautics, 1949), by Arthur W. Goldstein, Artur Mager, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Methods of designing cascade blades with prescribed velocity distributions in compressible potential flows (National Advisory Committee for Aeronautics, 1949), by George R. Costello and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Detailed computational procedure for design of cascade blades with prescribed velocity distributions in compressible potential flows (National Advisory Committee for Aeronautics, 1951), by George R. Costello, John T. Sinnette, Robert L. Cummings, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Flow through cascades in tandem (National Advisory Committee for Aeronautics, 1951), by William E. Spraglin 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)
• 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 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)
• Study of secondary-flow patterns in an annular cascade of turbine nozzle blades with vortex design (National Advisory Committee for Aeronautics, 1953), by Harold E. Rohlik, Howard Z. Herzig, Hubert W. Allen, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• A visualization study of secondary flows in cascades (National Advisory Committee for Aeronautics, 1953), by Arthur G. Hansen, George R. Costello, Howard Z. Herzig, 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)
• Optimum flow distribution for multicomponent isotope separation in a single cascade (Union Carbide Nuclear Company, Oak Ridge Gaseous Diffusion Plant, 1962), by J. E. Murphy, Oak Ridge Gaseous Diffusion Plant, Union Carbide Nuclear Company, and U.S. Atomic Energy Commission (page images at HathiTrust)
• A generalization of the matched abundance ratio cascade for multicomponent isotope separation (Union Carbide Nuclear Company, 1962), by A. De la Garza, Union Carbide Nuclear Company, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Parallel cascade sections (Union Carbide Nuclear Company, Oak Ridge Gaseous Diffusion Plant, 1956), by J. Shacter, W. N. Johnson, Oak Ridge Gaseous Diffusion Plant, Union Carbide Nuclear Company, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Methods of calculating U-235 outputs and charges by use of ideal cascade theory (Oak Ridge, Tennessee : United States Atomic Energy Commission, Technical Information Service Extension, 1960., 1960), by Artha Jean Snyder and U.S. Atomic Energy Commission (page images at HathiTrust)
• Calculating U-235 outputs and charges (Oak Ridge, Tennessee : United States Atomic Energy Commission, Technical Information Service Extension, 1960., 1960), by Willaim H. McVey, Gerald E. McTigue, Edwin H. Davidson, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Application of multicomponent cascade theory (Oak Ridge, Tennessee : United States Atomic Energy Commission, Technical Information Service Extension, 1961., 1961), by John E. Bigelow, Gerald E. McTigue, and U.S. Atomic Energy Commission. Division of Technical Information (page images at HathiTrust)
• An analytical method for determining the transient behavior of multiple section cascades. Part I (Oak Ridge, Tennessee : Carbide and Carbon Chemicals Company, K-25 Plant, 1952., 1952), by J. E. Rowe, Carbide and Carbon Chemicals Corporation, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Theoretical and experimental cascade flow investigations at high subsonic Mach numbers ([Washington, D.C.] : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 1959., 1959), by U. Hopkes and United States. Air Force. Office of Scientific Research (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)
• Unsteady flow around and aeroelastic vibration in turbomachine cascades (Foreign Technology Division, 1971), by G. S. Samoĭlovich (page images at HathiTrust)

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