The following report discusses the development of methods for sealing the ends of metallic-cored fuel rods.

As originally installed, the primary process pump turbines in 190-B were arranged to accelerate considerably upon loss of BPA electric power supply to the Process Pump House. However, the acceleration comes too late to be of value in maintaining top of riser pressure within the first second or two, and the acceleration results only in maintaining final process water pressure and flow at values higher than needed. It is desired to limit the acceleration of the turbines to a relatively small amount in order to decrease the emergency steam demands and keep the combined steam demands of 100-B and 100-C Areas within the capacity of 184-B Boiler House, as outlined in Document HDC-2106, revised June 4, 1951. This report recommends that the desired results be obtained by simply reducing the speed setting of the turbine speed governors. No new equipment is needed. The setting of the emergency over speed trips would be left unchanged.

This document presents a nomograph from which the relationship between reactor operating parameters, tube power, and outlet temperature can be correlated with rupture rate. The index indicates the severity of the reactor climate during irradiation and does not include the metal quality parameters defined in the rupture rate equation. The general form of the Operational Severity Index Equation is OSI=P{sup 3.3}/1000{times}t{sub 0}{sup 8.7}/100, where OSI, is the unitless Operational Severity Index, P is the tube power in kW, and t{sub 0} is the tube outlet temperature, in degrees C.

Abstract: Methods are presented for calibrating a peak current gage which was developed at Sandia in the spring of 1953.

During the exploration of the possible use of an extraction process for the separation of gaseous cascade impurities from uranium hexafluoride, a number of short exploratory studies were carried out. These included (1) experimental determination of the vapor pressure and liquid density of perfluorodibutylcylicether, (2) calculation of the liquid vapor-equilibria of the systes perfluoro-n-pentane-uranium hexafluoride and 1,2-dichlorohexafluoropropane-uranium hexafluoride, and (3) derivation of equations for the estimation of activity coefficients in ternary systems from the properties of the pure components. The results of these studies are summarized in this report.

Imperial Sugar Company financial report entailing quantities of sugar, selling amounts, and fees.

"The effect of dissolved oxygen in the filter-clogging characteristics of three JP-4 and two JP-5 fuels was studied at 300 degrees to 400 degrees F in a bench- scale rig, employing filter paper as the filter medium. The residence time of the fuel at the high temperature was approximately 6 seconds" (p. 1).

From Summary: "It is demonstrated with the aid of similitude arguments that a model launched from a hypervelocity gun upstream through a special supersonic nozzle should experience aerodynamic heating and resulting thermal stresses like those encountered by a long-range ballistic missile entering the earth's atmosphere. This demonstration hinges on the requirements that model and missile be geometrically similar and made of the same material, and that they have the same flight speed and Reynolds number (based on conditions just outside the boundary layer) at corresponding points in their trajectories. The hypervelocity gun provides the model with the required initial speed, while the nozzle scales the atmosphere, in terms of density variation, to provide the model with speeds and Reynolds numbers over its entire trajectory."

The loss of strength of cast polymethyl methacrylate plastic as a result of crazing is of considerable importance to the aircraft industry. Because of the critical need for basic information on the nature of crazing and the effects of various treatments and environmental conditions on its incidence and magnitude, an investigation of this phenomenon was undertaken. The following factors were examined: (1) the effect of stress-solvent crazing on tensile strength of polymethyl methacrylate; (2) the critical stress and strain for onset of crazing at various temperatures; (3) the effect of molecular weight on crazing; and (4) the effect of multiaxial stretching on crazing of polymethyl methacrylate and other acrylic glazing materials.

Aerodynamic characteristics of rectangular platform, all-movable controls combined with slender body of revolution at Mach 3 to 6.25. The results showed that lift variations with angle of attack were somewhat nonlinear for both control-body combinations tested.

Report presenting the performance of a side inlet with a fixed 12 degree two-dimensional compression surface for a range of Mach numbers, angles of attack, and yaw. The effects of several methods of compression-surface boundary-layer removal were investigated as well as a solid ramp.

Report presenting the results of force and moment tests at a range of Mach numbers on two rectangular-plan-form, all-movable controls in combination with a slender body of revolution are presented and compared with the predictions of theory. The results showed that lift variations with angle of attack were somewhat nonlinear for both control-body combinations tested.

Stresses on the root fastenings of turbine blades were appreciably reduced by redesign of the root. The redesign consisted in curving the root to approximately conform to the camber of the airfoil and elimination of the blade platform. Full-scale jet-engine tests at rated speed using cermet blades of the design confirmed the improvement.

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Report discussing "the effect on the multiplication constant of using graphite of various density." Results are tabulated and plotted.

Neutron multiplication measurements were performed on two identical finite Pu-metal slab assemblies separated and reflected by plexiglas. (auth)

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Abstract: "The complete freezing point diagram for the system uranium hexafluoride-hydrogen fluoride has been determined. In addition, liquid-liquid solubilities of these compounds have been measured up to the consolute temperature of 101 C. A miscibility gap starts at 61.2 C. over the compositions range 10 to 80 mole per cent uranium hexafluoride. The lowest melting point of this binary system under its own pressure, i.e. the eutectic, is -85 C."

In view of the increasing number of methods for determining plutonium in terms of weight rather than radioactivity, a need has arisen for a plutonium compound that can be used as a gravimetric standard. An easily prepared compound that dissolves readily in nitric acid is desirable. The present study was made to determine the feasibility of using plutonium triflouride as a plutonium standard. The preparation, composition, stability, and ignition of the compound are discuss, as are certain properties of the plutonium dioxide resulting from ignition of the trifluoride.

Report presenting an investigation in the altitude test chamber to determine the altitude performance of the J71-A-2(600-D1) turbojet engine. The engine was equipped with two-position inlet guide vanes and compressor acceleration bleeds. Results regarding the compressor performance, combustor performance, turbine performance, and effect of altitude on engine performance are provided.

Memorandum presenting an analysis of liquid methane, ethene, and propane along with normally liquid hydrocarbon fuels. The lower molecular weight hydrocarbons are superior to current JP-type fuels as heat sinks and that the more volatile fuels may be required with cooled-turbine engines.

From Summary: "The results of an experimental investigation of the hinge-moment characteristics of a constant-chord control surface oscillating at high frequency is presented. The control surface was mounted on an aspect-ratio-2 triangular wing. The aerodynamic restoring-moment coefficient and damping-moment coefficient were determined at a frequency of 260 cycles per second for a Mach number range of 0.6 to 0.8 and 1.3 to 1.9 at angles of attack of 5 degrees and 10 degrees. The test results showed linear theory to be a reliable guide to the prediction of the trend of the restoring-moment coefficient with Mach number for the supersonic speed range of the investigation but overestimated the magnitude of the coefficient."

Unsteady shock-induced separation of the ramp boundary layer was reduced and stabilized more effectively by external perforations than by external or internal slots. At Mach 2.0 peak total-pressure recovery was increased from 0.802 to 0.89 and stable mass-flow range was increased 185 percent over that for the solid ramp. Peak pressure recovery occurred just before instability. The 7 and one-third-diameter duct ahead of the engine reduced large total-pressure distortions but was not as successful for small distortions as obtained with throat bleed. By removing boundary-layer air the bypass nearly recovered the total-pressure loss due to the long duct.

"The drag and pressure recovery of an NACA submerged-inlet model and an NACA series I nose-inlet model were investigated in the transonic flight range. The tests were conducted over a mass-flow-ratio range of 0.4 to 0.8 and a Mach number range of about 0.8 to 1.10 employing large-scale recoverable free-fall models. The results indicate that the Mach number of drag divergence of the inlet models was about the same as that of a basic model without inlets" (p. 1).