Abstract: "A method has been developed for the determination of sodium monoxide in sodium which depends upon the reaction between sodium and n-butyl bromide in hexane solution. The sodium monoxide does not react with the reagent and can be determined, after the addition of water, by titration. The method is comparatively rapid, requires only the simplest of equipment, and it has the advantage that both oxygen and other impurities can be determined on the same sample."

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From abstract: "Data obtained in laboratory studies of the 'fumelses dissolving' of irradiated uranium are presented. Procedures for handling dissolver off-gases are proposed."

Procedures for the handling and recovery of nitrogen oxides and rare-gas fission products from the nitric acid dissolution of irradiated uranium are described. (C.J.G.)

Report discussing the use of a small-source approximation for engineering calculation of thermal piles. Explanation for how this type of approximation is more appropriate in certain problematic situations where a homogenization approximation would be doubtful is given.

The following report provides value tables of resonance intervals for various elements and materials.

Final approval of a flow-pressure characteristic curve and orifice pattern for C Pile is desired as soon as possible to allow the completion of orifice assemblies and parallit instrumentation. The presentation of a recommended flow-pressure curve and an orifice pattern has been delayed by a lack of experimental flow data on the C Pile flow system. Discussion with members of the C-431-B working committee and Pile Technology Unit personnel indicated that the use of flows higher than those recommended by the Reactor Unit, in HDC-2327, was desirable on the basis that the costs of supplying more water to C Pile than required by present outlet temperature limits will be small compared to the probable saving that can be made in reduction of corrosion and slug rupture frequency. Using this agreement as well as previous data and the assumption of low enrichment as a basis, a preliminary recommendation of a higher flow curve is presented.

Report presenting an investigation of liquid-film cooling at a variety of air temperatures and Reynolds numbers. Results regarding the effect of coolant flow per circumferential length on liquid-cooled length, correlation of heat transfer from hot gas to liquid film for constant coolant flow per circumferential length, and generalized plot of film-cooling data based on heat-transfer correlation at constant coolant flow per circumferential length are provided.

Report presenting the lateral-control characteristics of two spans of spoiler and flap-type ailerons on an unswept wing with an aspect ratio of 2.5 and hexagonal airfoil sections. Measurements of rolling moments, yawing moments, aileron hinge moments, normal forces, and balance-camber pressures for various configurations of the wing.

Report discussing the refractory properties of pure uranium dioxide, as well as methods for forming the compound. Health hazards of uranium dioxide are briefly mentioned.

Attention is now being drawn to the refractory properties of the pure dioxide of uranium, which make it suitable for special applications, such as the melting of pure uranium. Properties of uranium dioxide are described as they relate to fabrication. Forming of UO{sub 2} refractories by pressing and slip casting is discussed, as well as the firing of urania refractories and the properties of fired ware. Health hazards pertaining to UO{sub 2} are briefly described.

Report presenting an investigation of the aerodynamic interference effects associated with a missile configuration, consisting of a pointed body of revolution with one or two ramjet engines strut-mounted in a vertical plane through the center line of the body, at several engine locations relative to the body and a range of angles of attack. The experimental data indicated increases in slope of the normal force curve with outward movement of the engines. Results regarding the characteristics of isolated components, characteristics of representative configurations, interference effects, and effect of engine location on lift-drag ratio are provided.

Memorandum presenting an investigation conducted to explore the characteristics of metal-hydrocarbon combustion, to determine the effect of fuel-air ratio on the combustion efficiency, and to determine how the metal and hydrocarbon separately contribute to the overall combustion of several slurries. Results regarding an evaluation of the sampling method, combustion efficiency, effective metal weight fraction, effective hydrogen-carbon ratio, and heat of combustion per pound of air are provided.

Memorandum presenting a 10-stage axial-flow compressor designed for use as a research unit in which the problems associated with the compounding of high performance stages could be studied. The overall performance characteristics of the compressor, as determined experimentally, are included.

Report presenting experimental data from force and pressure tests on a large-scale, semispan, wing-fuselage model. Longitudinal force and moment characteristics are given for the model with various combinations of slat spans. The wing had 45 degrees of sweepback, an aspect ratio of 6, a taper ratio of 0.5, and an NACA 64A010 section normal to the quarter-chord line of the unswept panel and had partial-span slats, aileron, and double-slotted flaps equipped.

Report presenting testing of an impulse-type supersonic compressor rotor with stators tested in Freon-12 over a range of equivalent tip speeds and weight flows. A static pressure ratio of 1.83 and an efficiency of 84.7 percent were obtained at 69.1 percent of the design speed of 1604 feet per second in air.

Report describing the temperature in the Brookhaven concrete shield proposed for the X reactor. The report details the methods and equations used to find the values that determined that the effect of the gun barrel assembly in cooling the concrete is negligible.

From Introduction: "Because of the unusual nature of this equipment, and because it is proving to be very useful for certain kinds of aerodynamic research, this report has been prepared. It contains a description of the equipment and its use to obtain aerodynamic coefficients. The imperfections in the wind-tunnel air stream and their effect on model tests are also discussed."

Memorandum presenting a description of the Ames supersonic free-flight wind tunnel, which is a new piece of equipment for aerodynamic research at high supersonic Mach numbers. It has a wide Mach number range extending from low supersonic speeds to Mach numbers in excess of 10. The air stream in the tunnel is imperfect, mainly due to a symmetrical pair of oblique shock waves which reflect down the test section.

The study was undertaken with the objective of observing the distribution in the rat of organic compounds of phosphorus labelled with the P32 isotope as tracer. The fate of several of these compounds was studied in animals bearing tumors. The distribution of inorganic phosphate in animal tissues is well known but was included in this work for comparison with the organic phosphorus compounds.

Report presenting an investigation of the drag of spherically blunted conical models of fineness ratio 3 at a range of Mach and Reynolds numbers. Results of the tests showed that slightly blunted models had less drag than cones of the same fineness ratio through the Mach number range. Results regarding the total drag, wave drag, and viscous effects are provided.

Purpose and scope: The purpose of this report is to present an analysis and evaluation of the airborne radioactivity survey of the Blanding, Utah district conducted by The Texas Company on behalf of the Atomic energy Commission. Within the scope of the report, only the results of the airborne survey and the data used in its evaluation are presented. No attempt is made to discuss the details of the survey or of the drilling program conducted in the area. A separate report by P. 1. Melanoon, on the drilling program is in preparation.

Report presenting the total drag coefficients of 60 degree cone cylinders of fineness ratio 2.07 measured in free flight from Mach numbers of 1.5 to 8.2. Results regarding the smooth 60 degree cone cylinder, rifled models, and discontinuity lines in the shadowgraph pictures are provided.

From Summary: "The aerodynamic characteristics in pitch of an F-94C airplane, with the primary attention given to its drag characteristics, have been evaluated at low speed in the Ames 40- by 80-foot wind tunnel. The increments of drag due to various surface irregularities, ports, and component parts of the production airplane were determined. Wing-wake surveys were taken to determine the section drag coefficients at midsemispan for the smooth and the production wing. Base-pressure and internal drags of the air-induction system were measured at low inlet-velocity ratios. The characteristics of the airplane in the landing configuration are also included."