-PDF Download- Survey Of Portions Of The Chromium Cobalt Nickel Molybdenum Quaternary System At 1200 C EBOOK

Survey of Portions of the Chromium-cobalt-nickel-molybdenum Quaternary System at 1200° C

Author: Sheldon Paul Rideout

Publisher:

Published: 1952

Total Pages: 90

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A survey was made of portions of the Chromium-cobalt-nickel-molybdenum quaternary system at 1200 degrees C by means of microscopic and x-ray diffraction studies. Since the face-centered cubic (alpha) solid solutions form the matrix of almost all practically useful high-temperature alloys, the solid solubility limits of the quaternary alpha phase were determined up to 20 percent molybdenum. The component cobalt-nickel-molybdenum, chromium-cobalt-molybdenum, and chromium-nickel-molybdenum ternary systems were also studied. The survey of these systems was confined to the determination of the boundaries of the face-centered cubic (alpha) solid solutions and of the phases coexisting with alpha at 1200 degrees C.

Technical Note - National Advisory Committee for Aeronautics

Author: United States. National Advisory Committee for Aeronautics

Publisher:

Published: 1953

Total Pages: 1254

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Report

Author: United States. National Advisory Committee for Aeronautics

Publisher:

Published: 1953

Total Pages: 48

ISBN-13:

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Annual Report of the National Advisory Committee for Aeronautics

Author: United States. National Advisory Committee for Aeronautics

Publisher:

Published: 1953

Total Pages: 1138

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Includes the Committee's Reports no. 1-1058, reprinted in v. 1-37.

Report - National Advisory Committee for Aeronautics

Author: United States. National Advisory Committee for Aeronautics

Publisher:

Published: 1953

Total Pages: 1246

ISBN-13:

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The Effect of Blade-section Thickness Ratios on the Aerodynamic Characteristics of Related Full-scale Propellers at Mach Numbers Up to 0.65

Author: A. J. Eggers

Publisher:

Published: 1953

Total Pages: 286

ISBN-13:

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Experimental Investigation of a 90 Degree Cascade Diffusing Bend with an Area Ratio of 1.45:1 and with Several Inlet Boundary Layers

Author: Daniel Friedman

Publisher:

Published: 1952

Total Pages: 804

ISBN-13:

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An experimental investigation was conducted in order to determine the performance of a 90 degree cascade diffusing bend with an area ratio of 1.45:1 and a 19-inch square inlet with several inlet-boundary-layer shapes and thicknesses. The maximum mean inlet Mach number was 0.41 and the corresponding airfoil Reynolds number was 950,000. The experimental results seem to indicate that, when the duct configuration requires a bend, a certain amount of diffusion can be obtained without an appreciable rise in the total-pressure losses. If length is important, this configuration requires much less space than the usual diffuser-bend combination.