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Survey of Nonmetallic Liquid Coolants for Nuclear-Power Piles

Description: A comprehensive survey of the literature was made in an effort to identify nonmetallic materials of possible usefulness as liquid coolants. Materials having maximum melting points of 1000 deg F and boiling points of l200 deg F were considered, but boiling points above 2200 deg F were preferred. Melting points, boiling points, densities, heat capacities, and thermal conductivities were tabulated. Approximately 190 materials appeared to have melting and boiling temperatures in a suitable range. A… more
Date: May 26, 1950
Creator: Shaw, H.L. & Boulger, F.W.
Partner: UNT Libraries Government Documents Department
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High Energy Excitation Functions in the Heavy Region

Description: The electrostatically deflected beam of the 184-inch cyclotron has been used with the stacked foil and absorber technique to determine the excitation functions for the following reactions: Th{sup 232}(p,6n)Pa{sup 227}, Th{sup 232}(p,3n)Pa{sup 230}, Th{sup 232}(d,7n)Pa{sup 227}, Th{sup 232}({alpha},p8n)Pa{sup 227}, Th{sup 232}({alpha},p5n)Pa{sup 230}, and U{sup 238}(p,{alpha}8n)Pa{sup 227}. The data are presented graphically and discussed individually for each of the reactions. Some rough excita… more
Date: September 26, 1950
Creator: Meinke, W. W.; Wick, G. C. & Seaborg, G. T.
Partner: UNT Libraries Government Documents Department
open access

The New Element Berkelium (Atomic Number 97)

Description: An isotope of the element with atomic number 97 has been discovered as a product of the helium-ion bombardment of americium. This isotope decays with the emission of alpha-particles of maximum energy 6.72 Mev (30 percent) and it emits lower energy alpha-particles of energies 6.55 Mev (53 percent) and 6.20 Mev (17 percent). The half-life of this isotope is 4.6 hours and it decays primarily by electron capture with about 0.1 percent branching decay by alpha-particle emission. The mass number is p… more
Date: April 26, 1950
Creator: Thompson, S. G.; Ghiorso, A. & Seaborg, G. T.
Partner: UNT Libraries Government Documents Department
open access

P-10 stack monitoring

Description: On June 14, 1950, an aluminum Kanne Chamber on the 108-B vacuum discharge line was placed in operation. The vacuum pump discharge line chamber has a very poor reputation for two reasons: 1. An apparent hysteresis effect which shows as a high reading after a slug of gas has passed through it, and 2. Failure to return to background current. Cause of the hysteresis effect may be the distribution of tritium in the vacuum pump discharge gas. The rate of gas flow through the Kanne chamber is approxim… more
Date: June 26, 1950
Creator: Eisenacher, P. L.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Aerodynamic and Icing Characteristics of Water-Inertia-Separation Inlets for Turbojet Engines

Description: "The results of an investigation of several internal water-inertia-separation inlets consisting of a main duct and an alternate duct designed to prevent automatically the entrance of large quantities of water into a turbojet engine in icing conditions are presented. Total-pressure losses and icing characteristics for a direct-ram inlet and the inertia-separation inlets are compared at similar aerodynamic and simulated icing conditions. Complete ice protection for inlet guide vanes could not be … more
Date: July 26, 1950
Creator: von Glahn, Uwe & Blatz, Robert E.
Partner: UNT Libraries Government Documents Department
open access

Fabrication and Properties of Hot-Pressed Molybdenum Disilicide

Description: Report presenting an investigation of hot-pressed molbdenum disilicide bodies produced by industrial processes at a temperature of 2950 degrees and a pressure of 3000 pounds per square inch. Results regarding the short-time tensile strength, stress-rupture data, compression strength, air-corrosion resistance, hardness, coefficient of linear thermal expansion, thermal conductivity, and density are provided.
Date: May 26, 1950
Creator: Long, Roger A.
Partner: UNT Libraries Government Documents Department
open access

Numerical solution of equations for one-dimensional gas flow in rotating coolant passages

Description: Report presenting a theoretical analysis of the air flow through the blade coolant passages in an air-cooled turbine rotor. The simultaneous effects of area change, compressibility, wall friction, heat transfer, and rotation were included.
Date: June 26, 1950
Creator: Brown, W. Byron & Rossbach, Richard J.
Partner: UNT Libraries Government Documents Department
open access

Supplementary analysis of the dynamic lateral stability characteristics of the Bell X-2 airplane as affected by variations in mass and aerodynamic parameters

Description: Report presenting the application of an estimation of the derivative of yawing moment due to rolling to the dynamic lateral stability characteristics of the Bell X-2. Results regarding the airplane with flaps and gear retracted and airplane with flaps and gear lowered are provided.
Date: June 26, 1950
Creator: Michael, William H., Jr. & Queijo, M. J.
Partner: UNT Libraries Government Documents Department
open access

The effects of compressibility on the pressures on a body of revolution and on the aerodynamic characteristics of a wing-nacelle combination consisting of the body of revolution mounted on a swept-back wing

Description: Memorandum presenting an investigation of the effects of compressibility on the forces, pitching moments, and surface pressures on a wing-nacelle combination. The leading edge of the wing was swept back 37.25 degrees and the nacelle was a body of revolution with a fineness ratio of 6.5. The effects of compressibility on the surface pressures and on the drag of a body of revolution similar to the nacelle were also determined.
Date: July 26, 1950
Creator: Boltz, Frederick W. & Beam, Benjamin H.
Partner: UNT Libraries Government Documents Department
open access

Wing-dropping characteristics of some straight and swept wings at transonic speeds as determined with rocket-powered models

Description: Report presenting data gathered on a lateral-trim change or wing dropping that involves a rapid change of lateral trim with Mach number, which has occurred on several rocket-powered models used in roll investigations at transonic speeds. The data in this report demonstrates that straight wings with airfoil sections 9 percent thick or greater are susceptible to wing dropping between Mach numbers of 0.9 and 1.0. Results for straight, sweptback, and delta wings are provided.
Date: May 26, 1950
Creator: Stone, David G.
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Measurements of Wing Loads at Mach Numbers Up to 0.87

Description: Report presenting flight measurements of the aerodynamic wing normal force, bending moment, and pitching moment using strain gains on the D-558-II airplane at Mach numbers up to 0.87 and angles of attack up to 38 degrees. Results regarding Mach number effects and normal-force-coefficient effects are provided.
Date: December 26, 1950
Creator: Mayer, John P.; Valentine, George M. & Swanson, Beverly J.
Partner: UNT Libraries Government Documents Department
open access

Investigation of a 42.7 Degree Sweptback Wing Model to Determine the Effects of Trailing-Edge Thickness on the Aileron Hinge-Moment and Flutter Characteristics at Transonic Speeds

Description: Report presenting an investigation in the high-speed tunnel of a 42.7 degree sweptback wing model to determine the effects of aileron trailing-edge thickness on aileron hinge moments and one-degree-of-freedom aileron flutter. Results regarding the hinge-moment characteristics and free-floating characteristics are also provided.
Date: December 26, 1950
Creator: Thompson, Robert F.
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of the Aileron Characteristics of the Douglas D-558-I Airplane (BuAero No. 37972) at Mach Numbers Between 0.6 and 0.89

Description: "Abrupt, rudder-fixed aileron rolls have been made with the Douglas D-558-I airplane (BuAero No. 37972) at Mach numbers between 0.6 and 0.89. Rolls were made at aileron deflections between one-eighth and one-half the maximum available deflection. The results obtained indicate that the aileron effectiveness is independent of Mach number and deflection within the range investigated" (p. 1).
Date: May 26, 1950
Creator: Thompson, Jim Rogers; Roden, William S. & Eggleston, John M.
Partner: UNT Libraries Government Documents Department
open access

Downwash in Vortex Region Behind Rectangular Half-Wing at Mach Number 1.91

Description: Results of an experimental investigation to determine downwash and wake characteristics in region of trailing vortex system behind a rectangular half-wing at Mach number 1.91 are presented. The wing had a 5-percent thick symmetric diamond cross section beveled to a knife edge at the tip. At small angles of attack, downwash angles were in close agreement with predictions of linearized theory based on the assumption of an undistorted vortex sheet. At higher angles of attack, the flow was greatly … more
Date: October 26, 1950
Creator: Cummings, John L. & Haefeli, Rudolph C.
Partner: UNT Libraries Government Documents Department
open access

Advanced Seminar in Reactor Physics

Description: The following report provides equations that result from a seminar in reactor physics.
Date: July 26, 1950
Creator: Smith, Nicholas M.
Partner: UNT Libraries Government Documents Department
open access

Tributyl Phosphate as an Alternate Solvent for Extraction of "25" from spent MTR Fuel Assemblies

Description: Technical report showing how, on a laboratory scale, a one-cycle solvent extraction process using tributyl phosphate (TBP) can be used for the recovery and decontamination of uranium 235 from spent Materials Testing Reactor fuel assemblies.
Date: September 26, 1950
Creator: Runion, T. C.; Bamberg, I. L. & Fowler, V. L.
Partner: UNT Libraries Government Documents Department
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