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Tables and charts of flow parameters across oblique shocks

Description: Shock-wave equations have been evaluated for a range of Mach number in front of the shock from 1.05 to 4.0. Mach number behind the shock, pressure ratio, derivation of flow, and angle of shock are presented on charts. Values are also included for density ratio and change in entropy.
Date: August 1948
Creator: Neice, Mary M.
Partner: UNT Libraries Government Documents Department
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Redox Equipment Testing Report No. 4

Description: A report which covers progress on the testing of the General Engineering and Consulting Laboratory Turbine Pump No. 1 from June 16, 1948, to July 31, 1948.
Date: August 9, 1948
Creator: Cooper, V. R. & Allen, A. W.
Partner: UNT Libraries Government Documents Department
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Isolation of High Activities of Xe¹³⁵ at the Omega Water Boiler

Description: This report records two samples of Xe-135 that have been isolated with activities sufficient for the measurement of the cross section of Xe by the velocity spectrometer technique.
Date: August 18, 1948
Creator: Sugarman, Nathan
Partner: UNT Libraries Government Documents Department
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Supplement to Report on the Brookhaven Nuclear Reactor Prepared for Reactor Safeguard Committee of the Atomic Energy Commission

Description: This technical report provides supplementary information on the Brookhaven nuclear reactor. It details added safety systems, tests, expounds on information included in the original report, describes liquid wastes system, and describes different procedures for operating the nuclear reactor.
Date: August 30, 1948
Creator: Brookhaven National Laboratory
Partner: UNT Libraries Government Documents Department
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Cooperation with US Geological Survey

Description: This is a reference made to a memorandum about the cooperation between the Hanford Site and the US Geological Survey. The US Geological Survey was at the site to work with Hanford on geological problems the site was having. They worked together to locate the water supply wells of the site which would be coordinated with the drilling program. They also worked together on the possible contamination to the 300 and 3000 area wells. (MB)
Date: August 6, 1948
Partner: UNT Libraries Government Documents Department
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Biological Effects of Radiation

Description: No Description Available.
Date: August 10, 1948
Creator: Evans, R. D.
Partner: UNT Libraries Government Documents Department
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Some Reactor Engineering Problems

Description: No Description Available.
Date: August 10, 1948
Creator: Leverett, M. C.
Partner: UNT Libraries Government Documents Department
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Axial fatigue tests at zero mean stress of 24S-T and 75S-T aluminum-alloy strips with a central circular hole

Description: From Summary: "Axial fatigue tests at zero mean stress have been made on 0.032- and 0.064-inch 24S-T and 0.032-inch 75S-T sheet-metal specimens 1/4, 1/2, 1, and 2 inches wide without a hole and with central holes giving a range of hole diameter D to specimen width W from 0.01 to 0.95. No systematic difference was noted between the results for the 0.032-inch and the 0.064-inch specimens although the latter seemed the more consistent. In general the fatigue strength based on the minimum section d… more
Date: August 1948
Creator: Brueggeman, W. C. & Mayer, M., Jr.
Partner: UNT Libraries Government Documents Department
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Natural Icing of an Axial-Flow Turbojet Engine in Flight for a Single Icing Condition

Description: Memorandum presenting an investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. A description of the change over time in tail-pipe temperature, engine jet thrust, fuel flow, ice collection, and acceleration qualities are provided.
Date: August 12, 1948
Creator: Acker, Loren W.
Partner: UNT Libraries Government Documents Department
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Preliminary Results of Natural Icing of an Axial-Flow Turbojet Engine

Description: Memorandum presenting a flight investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. Tail-pipe temperature increased from 761 to 1065 degrees Fahrenheit and the jet thrust decreased from 1234 to 910 pounds during a period of 45 minutes in icing. No general conclusions can be reached from the data because the icing condition was relatively light.
Date: August 6, 1948
Creator: Acker, Loren W.
Partner: UNT Libraries Government Documents Department
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Icing and De-Icing of a Propeller with Internal Electric Blade Heaters

Description: "An investigation has been made in the NACA Cleveland icing research tunnel to determine the de-icing effectiveness of an experimental configuration of an Internal electric propeller-blade heater. Two atmospheric Icing conditions and two propeller operating conditions were Investigated in experiments with unheated blades and with heat applied to the blades both continuously and cyclically. Data are presented to show the effect of propeller speed, ambient air temperature and liquid-water concent… more
Date: August 1948
Creator: Lewis, James P. & Stevens, Howard C., Jr.
Partner: UNT Libraries Government Documents Department
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Mechanical Properties of Five Laminated Plastics

Description: Note presenting results of mechanical tests of several laminated plastics, including canvas laminate molded at low pressure, grade-C canvas laminate, rayon laminate, paper laminate, and glass-fabric laminate. The following tests were performed: static tension, compression, and torsion tests; long-time creep tests at different stresses on specimens loaded in tension; fatigue tests of unnotched specimens in bending; fatigue tests of notched specimens in bending; fatigue tests in bending at temper… more
Date: August 1948
Creator: Findley, William N. & Worley, Will J.
Partner: UNT Libraries Government Documents Department
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Plastic Buckling of a Rectangular Plate Under Edge Thrusts

Description: Note presenting the development of fundamental equations for the plastic buckling of a rectangular plate under edge thrusts on the basis of a new set of stress-strain relations for the behavior of a metal in the plastic range. The relations are derived for buckling from a state of uniform compression.
Date: August 1948
Creator: Handelman, G. H. & Prager, William
Partner: UNT Libraries Government Documents Department
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Compressible Flow Tables for Air

Description: "A tabulation is presented of functions of the Mach number which are frequently used in high-speed aerodynamics. The tables include values of Mach number from 0 to 10.0 in increments of 0.01 and the functions are based on the assumption that air is a perfect gas having a specific-heat ratio of 1.400" (p. 1).
Date: August 1948
Creator: Burcher, Marie A.
Partner: UNT Libraries Government Documents Department
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Bearing tests of 14S sheet and plate

Description: From Summary: "Tests were made to determine bearing yield and ultimate strengths of bare and Alclad 15S-W(exp 1) and 14S-T(exp 1) sheet and plate in thicknesses of 0.064 inch, 0.250 inch, and 0.750 inch. From the results of these tests it was concluded that the ratios of bearing to tensile properties from the with-grain direction were essentially the same as proposed in NACA TN Nos. 901, 920, 974, and 981 for other high-strength aluminum-alloy sheet and plate."
Date: August 1948
Creator: Moore, R. L.
Partner: UNT Libraries Government Documents Department
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Bearing strength of some aluminum-alloy sand castings

Description: Report presenting bearing tests made of aluminum-alloy sand casings of 195-T4, 195-T6, and 356-T6 to evaluate the bearing strength and tensile properties of the alloys. Comparisons with individually cast bars and specimens machined from slabs indicate that size and form of casing may have a significant effect on mechanical properties. Results of the tensile, compressive, and shear tests are provided in charts and include specified minimum and typical properties for comparison.
Date: August 1948
Creator: Moore, R. L.
Partner: UNT Libraries Government Documents Department
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Characteristics of Low-Aspect Ratio Wings at Supercritical Mach Numbers

Description: Note presenting experiments to study the characteristics of low-aspect-ratio wings at supercritical Mach numbers. The experiments consisted of tests of wings of aspect ratios ranging from infinity to 2. The results indicate that the detrimental effects of compressibility in the supercritical speed range on the stability and performance of aircraft are alleviated to a great degree by the use of low-aspect-ratio lifting surfaces.
Date: August 1948
Creator: Stack, John & Lindsey, W. F.
Partner: UNT Libraries Government Documents Department
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