The creep strength and tensile properties-were determined in vacuum for beta-quenched, derby uranium. The stresses to produce a secondary creep rate of- 0.0001 per cent per hr at 100, 250, 400, and 500 deg C were 48,000, sile strengths were 114,500, 35,100, 11,100, and 8,500 psi at temperatares of 28, 300, 500, and 700 deg C, respectively. The creep and tensile strengths decrease quite rapidly with increasing temperature in the temperatare range 250 to 400 deg C.

Report detailing values of x-ray lives and limits for trans-uranic elements. Formulas and methods are detailed throughout the report.

Report discussing trial runs of a method of recovery of uranium from salvage residue. The method involves hydrofluorination of the residue to remove large quantities of interfering silicates, followed by a fluorination treatment to remove uranium.

From Introduction: "This paper presents the results of the investigation of the wing-alone and wing-fuelage configurations employing a wing with the quarter-chord line swept back 60^o, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the free stream."

Report presenting a two-dimensional wind-tunnel investigation of a 6-percent-thick symmetrical circular-arc airfoil with leading-edge and trailing-edge high-lift devices. The purpose of the investigation was to determine the effects on maximum section lift coefficient of different leading-edge slats and drooped-nose flaps when used in combination with a plain trailing-edge flap. Results regarding slat configuration, drooped-nose-flap configurations, and a comparison of slat and drooped-nose-flap configurations are provided.

Memorandum presenting an investigation of the low-speed static stability characteristics of a canard model with a 45 degree sweptback wing and a 60 degree triangular horizontal control surface. Results regarding longitudinal stability and control and lateral stability and control are provided.

A typical inlet axial-flow compressor inlet stage, which was designed on the basis of constant total enthalpy with symmetrical velocity diagram at all radii, was investigated. At a tip speed of 1126 feet per second, a peak pressure ratio of 1.28 was obtained at an efficiency of 0.76. At a tip speed, the highest practical flow was 28 pounds per second per square foot frontal area with an efficiency of 0.78. Data for a rotor relative inlet Mach number range of from 0.5 to 0.875 indicates that the critical value for any stage radial element is approximately 0.80 for the stage investigated.

Report presenting a pressure-distribution investigation in the high-speed tunnel of a wing-fuselage configuration as part of an NACA research program to determine effects of wing geometry on aerodynamic characteristics and to explore the nature of flow over the configuration. Measurements were made on a fuselage and wing-fuselage combination for a range of Mach numbers. Results regarding accuracy, figures of pressure distributions, pressure distributions on the wing and fuselage, results at several angles of attack, section loading characteristics, normal-force characteristics, pitching-moment characteristics, pressure-drag characteristics, and fuselage skin-friction drag are provided.

Report presenting a wind-tunnel investigation to determine the low-speed longitudinal and lateral control characteristics of a model with a triangular wing with NACA 65(06)-006.5 airfoil sections, aspect ratio 2.31, and constant-chord control surfaces. The values of the hinge-moment parameters were found to be of somewhat greater magnitude than would be expected on unswept wings with the same aspect ratio.

The correlation functions and power spectra of the rolling and yawing moments on an airplane wing due to the three components of continuous random turbulence are calculated. The rolling moments to the longitudinal (horizontal) and normal (vertical) components depend on the spanwise distributions of instantaneous gust intensity, which are taken into account by using the inherent properties of symmetry of isotropic turbulence. The results consist of expressions for correlation functions or spectra of the rolling moment in terms of the point correlation functions of the two components of turbulence.

To obtain a better understanding of the mechanism involved in scaling behavior of zirconium, kinetic studies were made of the weight pickup in air after the following pretreatments; (1) exposure to oxygen or nitrogen, (2) exposure to air, oxygen or nitrogen and removal of the resulting surface compounds.

Iron containing approximately 0.01 wt. % carbon was quenched from 700°C and irradiated in the BNL reactor at 57°C for various lengths of time. The rate of decay of the Snoek internal friction peak was observed at 57°C after irradiation. After a 4-hour irradiation the rate of decay of the peak was one order of magnitude faster than the rate of decay in an unirradiated specimen. Longer irradiation times up to 48 hours caused no further acceleration of the decay rate. This observation implies that in the irradiated specimens there are ten times more precipitation nuclei than in the unirradiated specimens. This is confirmed by electron microscope studies which also show a factor of ten greater concentration of precipitate particles in specimens irradiated for 5 hours at 57°C as compared to an equivalent unirradiated specimen. Electron microscope studies also show that longer irradiation times do not increase further this number of precipitates. Although these experiments clearly demonstrate the enhancement of nucleation by neutron irradiation, it is not known why the incipient nuclei created by irradiation times of longer than 5 hours do not form observable precipitate particles.

This report describes a proposed modification to the ventilation system in the Redox Canyon Building. Detailed drawings and cost estimates are provided for three alternatives.

The solution of the monoenergetic Boltzmann equation in an infinite homogeneous, nonmultiplying medium with linearly anisotropic scattering and an isotropic plane source is given and compared with the corresponding solution for isotropic scattering. The effective source strength for the asymptotic flux turns out to be the same as that for isotropic scattering to first order in Σa/Σ.