Report discussing a study testing features of the absorption spectra of different oxidation states of neptunium and perchloric acid concentration's effects on the spectra. Data regarding a disproportionation reaction present in neptunium(V) solutions in concentrated acid is included.

The following report analyzes experiments on urinary samples of personnel who were exposed to radioactive materials. This report describes the procedure employed for this assay, and data to show its performance and reasons for its present course are presented.

The following document describes observations from tests on neptunium metal and their reactions to different room temperatures.

Radioactive decay data are used to calculate the atomic masses of the heavy isotopes, A> 203. The four radioactive families are then connected by means of neutron binding energies known from reactions on various isotopes. Finally all the masses are collectively adjusted for the best fit with mass spectrographic information available in this region. The masses so calculated are presented. Differences between masses of isotopes are estimated to have an of (plus/minus) 0.00020 mas units or about 200 Kev; the position of the masses taken collectively is in doubt by about 1.5 Mev.

Technical report on the geological investigation of the Green River desert area, Utah, studying uranium deposits in the area.

Report discussing some methods for predicting the carbon-forming propensity of turbojet-engine fuels from results of simple laboratory tests of the fuels. The prediction of carbon deposition from fuel characteristics including aromatic content, hydrogen-carbon ratio, distillation temperatures, gravity, and aniline point from several empirical laboratory carbon-deposition tests are provided. Results regarding fuel composition and volatility, related fuel properties, empirical laboratory tests, a comparison of methods predicting carbon-deposition characteristics of fuels, and application of fuel quality control methods are provided.

Report presenting an investigation to determine some of the basic problems and effects involved in a change of solidity accomplished by a change in the number of blades in an axial-flow-compressor rotor row and in a complete stage. Results regarding rotor performance and complete stage performance are provided.

Report presenting flight tests to determine the pressure distribution over the wing of a swept-wing jet-propelled airplane over the flight range of lift coefficients for Mach numbers up to 1.11. Results regarding the section characteristics, load distribution, and trailing-edge loads are provided.

Report presenting an investigation in the 16-foot transonic tunnel to determine the effect of leading-edge chord-extensions on the aerodynamic characteristics of a sweptback wing-fuselage combination at several Mach numbers. Results regarding the effect of chord-extensions on longitudinal stability for wing-normal configuration, effect of chord extensions on lift for wing-normal configurations, effect of chord-extensions on drag and lift-drag ratios of wing-normal configurations, effect of chordwise fences on the aerodynamic characteristics of a wing-normal configuration, and effect of chord-extensions on the pitching moment and lift characteristics of a wing-art configuration are provided.

Corrosion rates of present reactor grade uranium were measured in boiling distilled water and were found to have higher values almost by a factor of two then previously reported corrosion rates of uranium. Mallinckrodt biscuit metal showed corrosion rates in the same medium somewhat lower than reactor grade uranium, and high purity metal prepared at Argonne National Laboratory corroded considerably less rapidly than the biscuit metal.

Report presenting cold-flow free-flight tests at zero lift to investigate the possibility of flutter of simulated wing-ram-jet-nacelle configurations which were 1/9-scale models of the wing and ramjet nacelles of the Grumman XSSM-N-6a missile. Testing was performed on three different configurations. Results regarding Mach number, velocity, aerodynamic density, and flutter are provided.

Results are presented, in graphical and tabular form, from a wind tunnel investigation of the lift, drag, and pitching moment characteristics of thin, low-aspect-ratio wings in combination with a body at Mach numbers from 0.25 to as high as 1.9. The following are analyzed and compared with existing theoretical results: 1. Effects of aspect ratio on 3-percent-thick triangular wings; 2. Effects of plan form on 3-percent-thick triangular, sweptback, and unswept wings of aspect ratios 2 and 3; 3. Effects of wing thickness on triangular wings of aspect ratio 2; 4. Effects of profile shape on triangular, sweptback, and unswept wings; and 5. Effects of camber and twist on triangular wings of aspect ratios 2 and 4.

Report discussing measurements of thermal conductivity and heat capacity for uranium-chromium and uranium-iron eutectic alloys at room temperature. The resulting values were intended for use in design calculations until more accurate data at other temperatures was obtained.

Report presenting an investigation of the validity of application of the simplified-radial-equilibrium equation to axial-flow turbomachines. Two different types of equations were used. Results regarding the interpretation of the data, single stages, middle and end stages of the multistage compressor, application of the radial-equilibrium equation, and the solution for the velocity distributions are provided.

Report presenting a wind-tunnel investigation to determine the effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin symmetrical NACA 4-digit-series airfoil sections. The variations with Mach number of the lift, drag, and pitching moment for a 4-percent-chord-thick airfoil section are not significantly affected by a change of leading-edge radius from 0.18 to 0.53 percent of the chord.

"The following is an evaluation of a modified Zircaloy-2 ingot melted at WAPD using the non-consumable electrode melting technique. The nominal composition of the alloy is 0.5% tin, 0.1% iron, 0.1% chromium, and 0.5% nickel."

From Summary: "A 1/5-scale, rocket-propelled model of the Convair F-102 configuration was tested in free flight to determine zero-lift drag at Mach numbers up to 1.34 and at Reynolds numbers comparable to those of the full-scale airplane. This large-scale model corresponded to the prototype airplane and had air flow through the duct. Additional zero-lift drag tests involved a series of small equivalent bodies of revolution which were launched by means of a helium gun."

Report presenting an experimental investigation in the blowdown tunnel to determine the balancing effects of a detached tab on a constant-chord trailing-edge control mounted on a 60 degree delta wing for a range of Mach numbers. Control hinge moments, rolling moments, and lift effectiveness of the semispan wing-body combination are provided.

Report presenting a program to investigate the aerodynamic characteristics of thin delta wings with symmetrical double-wedge sections in the hypersonic tunnel at a Mach number of 6.9. A family of 5-percent-thick lifting wings with semiapex angles were tested over a range of angles of attack. Results regarding lift and drag characteristics, center of pressure and moment coefficient, Schileren photographs, and surface film flow studies are provided.

From abstract: "The Safety Program of the University of California Radiation Laboratory at Livermore, California, is discussed in terms of the functions of the six independent safety groups that comprise the laboratory's primary safety organization, namely, Industrial Safety, Medical Safety, Fire Prevention and First Aid, Health Chemistry, Health Physics, and High-Explosive Safety Groups."

In support of an in-reactor thermocouple stability testing program now in progress, laboratory studies were made relative to the stability of thermocouple bundles similar to those projected for in-reactor use. Two sets of chromel-alumel, copper-constantan and iron-constantan thermocouples were held for extended periods at 300 C in successive atmospheres of 75% helium-25% carbon dioxide. 100% carbon dioxide and air. Thermocouple stability was verified by measuring emf's at the freezing point of lead. The results of these tests are to be used to evaluate data obtained from like thermocouples subjected to condition similar to the laboratory tests with the added facet of reactor irradiation.