Average record data listings taken during aerial gamma-ray and magnetic surveys of the Nulato quadrangle in Alaska.

Delta-stabilized plutonium can be welded to itself or almost any other metal using the inert-gas metal-arc process. Equipment and procedures suitable for the welding of delta-stabilized plutonium under various conditions are described.

In accordance with a request of the Bureau of Aeronautics, Navy Department, tests were performed in the Langley 20-foot free-spinning tunnel to determine the spin and recovery characteristics of a 1/24 scale model of the Grumman XTB3F-1 airplane. The airplane is a two-place, midwing torpedo bomber equipped with a tractor propeller and an auxiliary jet engine. The effect of control setting and movement on the erect and inverted spin and recovery characteristics of the model were determined for the normal loading.

Discussing a detailed reconnaissance of the uranium possibilities carried out to provide information for the individuals engaged in prospecting in and around the area.

Discussing major joint trends in the Circle Cliffs area, in Garfield County, Utah.

"Results are presented of an investigation that has been undertaken to develop theoretical methods of treating the motions of hydrofoil systems and to determine some of the important parameters. Variations of parameters include three distributions of area between the hydrofoils, two rates of change of downwash angle with angle of attack, three depths of immersion, two dihedral angles, two rates of change of lift with immersion, three longitudinal hydrofoil spacings, two radii of gyration in pitching, and various horizontal and vertical locations of the center of gravity. Graphs are presented to show locations of the center of gravity for stable motion, values of the stability roots, and motions following the sudden application of a vertical force or a pitching moment to the hydrofoil system for numerous sets of values of the parameters" (p. 1).

Memorandum presenting an investigation to determine the combustion performance characteristics of gaseous hydrogen fuel in a single tubular turbojet combustor. The combustor was operated over a range of inlet-air pressures from 3.3 to 14.3 inches of mercury absolute. Results regarding stability limits and combustion efficiency are provided.

The following report describes the electron spectrum of protactinium derived from 23 minute thorium 233 that was produced by neutron capture in stable thorium.

This report analyzes Parian and Teflon that were exposed to solutions of 1AX, 1AS, and 1AF, ANL June 1, 1948 Flowsheet, under conditions described in the following report.

"An investigation of the cooling of an 18-cylinder, twin-row, radial, air-cooled engine in a high-performance pursuit airplane has been conducted for variable engine and flight conditions at altitudes ranging from 5000 to 35,000 feet in order to provide a basis for predicting high-altitude cooling performance from sea-level or low altitude experimental results. The engine cooling data obtained were analyzed by the usual NACA cooling-correlation method wherein cylinder-head and cylinder-barrel temperatures are related to the pertinent engine and cooling-air variables. A theoretical analysis was made of the effect on engine cooling of the change of density of the cooling air across the engine (the compressibility effect), which becomes of increasing importance as altitude is increased" (p. 267).

A comparison of the simple impact theories of line broadening by electrons with the detailed computations of Kivel, Bloom, and Margenau.

A lightweight instrument that utilizes resistance-wire electric strain gases to measure propeller-shaft thrust has been developed. A wind-tunnel investigation on a propeller installed, on a single-engine pursuit airplane showed that the instrument gave a reliable indication of propeller-shaft thrust to an accuracy of +/-2 percent within its calibrated range. No attempt was made to determine the relation of indicated shaft thrust to net propeller thrust.

Technical report. From "3. Methods of Preparation" : "Pivadehyde cyanohydrin can be prepared by the reaction of pivadehyde with anhydrous HCN2 or by the sodium bisulfite process. Trimethyllactamide can be prepared by hydrolysis of pivaldehyde cyanohydrin with cold concentrated sulfuric acid. The procedure described here differs in the scale of preparation an in the use of cold fusing hydrochloric acid for hydrolizing the cyanohydrin."

Prevailing dimensional tolerance for sintered UO₂ reactor fuel components to be enclosed in metal jackets are expensively small. For instance, the PWR fuel pellet, as of November, 1955, consisted of a centerless ground UO₂ cylinder 0.3560" (+0.0005", -0.000") in diameter and 0.3527" (±0.0008") long. This pellet was designed to fit in a Zircaloy tube 0.3585" (+0.0005", -0.0000") inside diameter. The use of UO₂ shapes as pressed, or extruded, and sintered with diameter variations controlled to a tolerance of ±0.003" to ±0.005" would represent a fabrication cost saving worth considering. It is reasonable to assume that the annulus between a sintered UO₂ shape and its container will vary as a function of time of irradiation. Shrinkage from the can walls occurs with relatively low density (i.e., 85% of theoretical) sintered irradiation (cf. MTR Test GEH-4-3C). Contrary to this effect, the thermal expansion coefficient of UO₂ is about twice that of Zircaloy. Of possibly greater significance is the inevitable fractuce of dense UO₂ due to thermal stress. Such cracking effectively relocates the annular heat transfer gap to the interior of the oxide where the higher temperatures enhance the heat transfer coefficient. Thus, possibly the worst condition, with respect to heat transfer, is …

Report presenting the specific impulse of liquid diborane and liquid oxygen over a range of mixture ratios in a 100-pound-thrust rocket engine operating at a combustion-chamber pressure of 300 pounds per square inch absolute. A faired curve through the experimental data had approximately the same shape as the theoretical curve.

The data given in this report covers the explosive limits of hydrocarbon fuels. Incidental to the purpose of the investigation here reported, the explosive limits will be found to be expressed for the condition of constant pressure, in the fundamental terms of concentrations (partial pressures) of fuel and oxygen.

Report presents the results of a full-scale investigation conducted in the NACA 20-foot tunnel to determine the pressure difference available for cooling with cowling flaps. The flaps were applied to an exit slot of smooth contour at 0 degree flap angle. Flap angles of 0 degree, 15 degrees, and 30 degrees were tested. Two propellers were used; propeller c which has conventional round blade shanks and propeller f which has airfoil sections extending closer to the hub. The pressure available for cooling is shown to be a direct function of the thrust disk-loading coefficient of the propeller.

The purpose of this report is to describe the nuclear power plant for the N.S. Savannah and the program in progress for the analysis of potential hazards associated with the operation of a nuclear merchant vessel. Particular emphasis is given to the safety features embodied both in the design and operation of the plant.

This report describes the design procedure for a reflectometer or directional coupler to replace the probe part of the D07-1020 assembly used at the Brookhaven Alternating Gradient Synchrotron linac. Mathematical treatment and diagrams of various reflectometers are included.

Use of the Smith chart in studying stub tuners is demonstrated. Several properties of the tuners are shown, and charts for various wave length spacings, tuning trajectories, and admittances are included.

Report discusses the results of testing to determine the low-speed longitudinal stability characteristics and spanwise distribution of load of a wing model with the leading edge swept back 63 degrees, an aspect ratio of 3.5, and a large amount of twist and camber. The results are compared to tests of a model of an untwisted and uncambered wing of identical plan form. Measurements of force, pressure-distribution, and comparison of theoretical and experimental span loading are described.