This report analyzes a procedure based on the production of acetylene from the active water, with subsequent measurement of the ionization caused by the tritium beta particle. This eliminates the troublesome absorption on the chamber walls when hydrogen is used, and provides a rapid method for the preparation of the urine samples.

The following report provides results from investigations of torsional vibration stresses in the drive shafts of two Westinghouse motor generator sets in 1952.

Report discussing a system designed to "punch binary data from an RCL pulse-height analyzer (PHA) on paper tape concurrent with the printing of decimal information."

Report presenting testing of two scale models of the Chance Vought Regulus II missile to investigate its drag characteristics for a range of Mach numbers from 0.8 to 2.2. Due to some of the differences between the observed drag values and previous testing, the exact drag level of the configuration tested is still in question. Results regarding total drag and external drag are provided.

Report presenting aerodynamic characteristics of uncambered symmetrical parabolic and double-wedge airfoils with leading-edge and trailing-edge flaps using the Busemann second-order-approximation theory. Characteristics presented include aileron effectiveness factor, rate of change of hinge-moment coefficient with aileron deflection, rate of change of the pitching-moment coefficient, and the location of the center of pressure of the airfoil-aileron combination.

Report presenting testing of the effects of the following variables on combustion performance are determined: inlet-air temperature, combustion-chamber-inlet Mach number and pressure, and fuel density and volatility.

Report discusses a procedure for estimating the wing lift coefficient for and spanwise location of the first occurrence of section stall on a swept wing. It has been modified from a method used to calculate the same information for unswept wings. The effects of split flaps, leading-edge modifications, and fences are described.

From Summary: "A determination of the dynamic characteristics of a typical turbojet engine with a centrifugal compressor, a sonic-flow turbine-nozzle diaphragm, and fixed area exhaust nozzle is presented. A generalized equation for transient behavior of the engine was developed; this equation was then verified by calculations using compressor and turbine performance charts extrapolated from equilibrium operating data and by experimental data obtained from an engine operated under transients in fuel flow."

The following report provides a geological map of the Deadhorse Flat quadrangle, Nye County, Nevada.

A series of neutron multiplication measurements with arrays of 1 by 8 by 10 in. slabs of 93.4% U235-enirched uranium metal have been made to provide data from which safety criteria for the storage of these fissile units can be established. Each slab contained 22.9 kg of U235. A maximum of 125 unites was assembled. The arrays studied were cubic lattices of the units and were usually parallelepipedal in shape.

Report discussing various reaction methods for preparing TCl₄ with hexachloropropylene, as well as various methods for drying the TCl₄ after the reaction. Experimental methods are described in detail, and experimental results are presented.

Description of Invention: Chloride-induced corrosion is a serious problem in the Purex acid recovery operation and in the evaporative concentration of process streams and waste solutions. In the case of Purex acid recovery, it has been shown that trace chloride will volatilize with the nitric acid and reflux in the acid fractionator, thus causing especially severe corrosion at that point. These traces of chloride may enter the process form several sources, i.e., as an impurity in the technical grade chemicals used in making up the various aqueous process streams, by hydrolysis or radiation decomposition of carbon tetrachloride (a promising diluent for tributyl phosphate), or by incomplete removal of the hydrochloric acid employed in some flowsheets for effecting the dissolution of certain difficulty soluble nuclear reactor fuel elements.

In connection with studies of the chemical reactivity of PuO_2 to hydrofluorination, samples were examined by X-ray diffraction for crystallite size and perfection. The PuO_2 was formed by thermal decomposition of the oralate. The reactivity of this oxide, as well as that of other solid oxides is affected by the conditions of preparation. Besides the obvious influence of surface, including lattice strain and other structural irregularities in the particles. Each particle is composed of a number of crystallites. The extent of crystallites size and perfection will be indicated by the width of a diffracted X-ray beam. Since separation of these two caus4es would require a detailed analysis, the observed broadening was interpreted on the assumption of crystallite size effects alone. However, the variable factor in preparation method was temperature, and it is to be expected that crystallite growth with annealing will occur in part at the expense of energy stored in nonequilibrium states of the crystal, i.e., imperfections. The objectives of this study were to establish a convenient method for determination of PuO_2 crystallite size and to obtain estimates of the crystallite sizes of seven given samples.

Technical report. From Abstract : "Thermal, metallographic, and vapor pressure data were obtained to establish the phase boundaries and the standard free energy, enthalpy, and entropy of formation for the compounds in the yttrium-zinc system."

From abstract: "Distillation procedures used for purifying yttrium metal, producing metal containing less than 150 ppm oxygen and lower concentrations of most of the other common impurities, are discussed. Some of the physical and mechanical properties of the distilled yttrium indicate: (1) a melting point of 1510°C, (2) a solid state transformation at 1459°C obtained from high temperature resistivity data, (3) a Rockwell H hardness of 60 and (4) improved rolling and swagging characteristics."

From abstract: "An apparatus is described which automatically separates a flow of drops into a series of equal samples."

APPR-1 is described and the various hazards are reviewed.

"Approximately 2,000 flights of rocket-propelled models have been made in which model configuration, model size, type and number of booster rockets, number of booster stages, and booster arrangements varied. A brief summary of the results obtained with some of the more unusual arrangements, descriptions of boosting hardware and techniques, and discussions of some factors responsible for the choice of these configurations are presented in this paper. The results show that unconventional boosting techniques may be used successfully when conventional tandem arrangements are unsuitable or unwieldy" (p. 1).

Report presenting an investigation at Mach number 5.20 to determine the longitudinal aerodynamic characteristics of a number of flat-bottom bodies which were investigated for possible hypersonic applications. The bodies were tested at positive and negative angles of attack to simulate flat-bottom and flat-top arrangements.

Report presenting a wind-tunnel investigation at low speeds of a thin aspect-ratio-1.85 pointed-wing-fuselage model with double slotted flaps, including the effects of a straight and delta horizontal tail on the static longitudinal stability and the effect of a delta vertical tail on the static lateral stability. Results regarding the longitudinal aerodynamic characteristics and lateral stability characteristics are provided.

Report presenting an investigation of a helicopter pressure-jet system. The effects of tip speed, fuel-air ratio, and pressure ratio on the propulsive characteristics of the pressure-jet system have been determined for a range of tip seeds, blade-root stagnation-pressure ratios, and fuel-air ratios. Results regarding tip-burner specific propulsive horsepower, propulsive horsepower per unit mean duct area, tip-burner specific fuel consumption, ratio of propulsive horsepower to equivalent air horsepower, effect of whirling on tip-unit thrust, effect of whirling on the tip-burner inlet pressure, effect of auxiliary fuel flow, power-off drag of tip units, and overall specific fuel consumption of pressure-jet system are provided.

Report presenting the effects of a movable exhaust-nozzle plug on the operational performance of a 20-inch ramjet in the altitude wind tunnel. Results were obtained at various exhaust-nozzle-plug positions over a range of fuel-air ratios, combustion-chamber-inlet velocities and static pressures, and ambient-air static pressures.

An investigation is being conducted in the Langley 20-foot free-spinning tunnel on a l/18 scale model of the Ryan X-13 airplane to determine its spin and recovery characteristics. The spin and recovery characteristics determined to date are presented in this report.

Available measurements of the derived gust velocities within thunderstorms are summarized for altitudes from 5,000 to 34,000 feet. The results indicate that the intensity of the derived gust velocity is essentially constant up to altitudes of 20,000 feet and that an approximate 10-percent reduction in the gust intensity occurs for altitudes from 20,000 to 30,000 feet.