Add to ORKGSeptember 1959Includes bibliographical references (page 27)A theoretical method to estimate the effect of axial velocity change through a cascade was investigated. The change of axial velocity was reproduced by distributing sinks and sources within the blade passages, and the conclusions are set forth in some simple formulae. Some graphs for the numerical evaluation of the performance of NACA 65 series cascades were prepared, and several examples were compared with experimental data.Under the sponsorship of: General Electric Company, Allison Division of General Motors Corporation and Westinghouse Electric Corporatio
Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1991....
May 1955Thesis written jointly by both authors: Thesis (M.S.)--Massachusetts Institute of Technology...
This paper presents an experimental investigation of effects of axially non-uniform tip clearances o...
AbstractThis paper presents comparative numerical studies to investigate the effects of blade sweep ...
A series of experimental studies were conducted in order to investigate the generation and growth of...
April 1955Includes bibliographical referencesA theory of stall propagation in a cascade of airfoils ...
Theoretical and experimental results are presented which reassure the usefulness of two-dimensional ...
A large-scale, low-speed, axial-turbine cascade was designed using a fast interactive design code an...
JUN 1954 --hand-stamped on title-page'Stall flutter phenomena in axial flow machines' terminal repor...
Abstract-- A cascade is defined as an infinite row of equidis-tant similarly aerofoil bodies. The ca...
In this computer-aided study, existing methods of determining the fluid flow in axial flow turbomach...
An investigation has been conducted to compare the performance of NACA 65-series compressor blades i...
Thesis (M.Sc.)-University of Natal, Durban, 1989.On unshrouded axial flow turbine rotors, the tip cl...
An experimental and analytical investigation was undertaken to determine the influence of asymmetric...
A 30-inch tip-diameter axial-flow compressor stage was investigated with and without rotor to determ...
Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1991....
May 1955Thesis written jointly by both authors: Thesis (M.S.)--Massachusetts Institute of Technology...
This paper presents an experimental investigation of effects of axially non-uniform tip clearances o...
AbstractThis paper presents comparative numerical studies to investigate the effects of blade sweep ...
A series of experimental studies were conducted in order to investigate the generation and growth of...
April 1955Includes bibliographical referencesA theory of stall propagation in a cascade of airfoils ...
Theoretical and experimental results are presented which reassure the usefulness of two-dimensional ...
A large-scale, low-speed, axial-turbine cascade was designed using a fast interactive design code an...
JUN 1954 --hand-stamped on title-page'Stall flutter phenomena in axial flow machines' terminal repor...
Abstract-- A cascade is defined as an infinite row of equidis-tant similarly aerofoil bodies. The ca...
In this computer-aided study, existing methods of determining the fluid flow in axial flow turbomach...
An investigation has been conducted to compare the performance of NACA 65-series compressor blades i...
Thesis (M.Sc.)-University of Natal, Durban, 1989.On unshrouded axial flow turbine rotors, the tip cl...
An experimental and analytical investigation was undertaken to determine the influence of asymmetric...
A 30-inch tip-diameter axial-flow compressor stage was investigated with and without rotor to determ...
Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1991....
May 1955Thesis written jointly by both authors: Thesis (M.S.)--Massachusetts Institute of Technology...
This paper presents an experimental investigation of effects of axially non-uniform tip clearances o...