BS>The use of a lead-bismuth alloy as a coolant in the removal of heat from power-generating nuclear reactors was considered with the possibility that its ternary alloy with uranium or plutonium might be of use in a reactor of the circulating-liquid-fuel type. Information collected from the literature covering phase-equilibrium studies, physicalproperty data, and reactivity of this alloy toward other substances is presented. (auth)

Report presenting an investigation at subsonic and transonic speeds to determine the aerodynamic characteristics of three geometrically similar wings with 42 degree sweepback of the leading edge, aspect ratio 4, taper ratio 0.625, and NACA 64(sub)1-112 airfoils. The lift, drag, and pitching-moment characteristics are provided.

A report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for nine radial stations of the NACA 10-(3)(049)-033 propeller.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Price Daniel, regarding a legal question submitted for clarification: Several questions relative to the procedure to be followed to discharge patients from State hospitals.

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Report presenting an investigation of the low-speed longitudinal stability and control characteristics of a scale model of a Bell X-5 airplane design with various leading-edge slat and trailing-edge flap arrangements. A marked increase in stability with increasing sweep angle at low lift coefficients was noted. Results regarding the basic longitudinal characteristics, leading-edge slats, trailing-edge flaps, and longitudinal control are provided.

"At the request of the Air Materiel Command an investigation was made in the Langley free-flight tunnel to determine the static longitudinal stability and control characteristics of models coupled together in a tandem configuration proposed by All American Airways, Inc. Force tests were made using 1/20-scale models of B-29 end F-80 airplanes to determine the effects of coupling the fighter to the tail of the bomber. The results of the investigation showed that for the bomber alone the aerodynamic center was 0.21 mean aerodynamic chord behind the center of gravity (stable) but that for the tandem configuration the aerodynamic center was 0.09 mean aerodynamic chord forward of the center of gravity, of the combination (unstable)" (p. 1).

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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.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Price Daniel, regarding a legal question submitted for clarification: The exemption of dentists employed by the Veterans Administration or the U.S. Public Health Service from Texas license and registration requirements.

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.

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"An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel to determine the static lateral stability characteristics of a supersonic aircraft configuration at Mach numbers of 1.40 and 1.59. The model had a 40 degree sweptback wing with 10-percent-thick circular-arc sections normal to the quarter-chord line. The results of the investigation indicated high directional stability that decreased with increasing Mach number and positive effective dihedral that was essentially invariant with lift coefficient and Mach number" (p. 1).

A solution of Pu was prepared for use in a re-investigation of the present 49 titration method. Three 500 microliter portions of the sample were dried and ignited to PuO{sub 2}. From the weight of the residue and the impurity analysis, the concentration, in g/l, of the solution was found to be 222.2, 221.5, and 222.5; average of 222.0. The six samples submitted to the control laboratory in Bldg. 231 were reported as: 219.3, 223.6, 221.5, 220.9, 222.3, and 228.2 (re-run 229.3); average of 222.6 g/l. The 234-5 Laboratory reported: 228.2, 233.3, 220.2, 236.1, 225.2 (re-run 220.6), and 227.9; average of 227.3 g/l. Since the standardization was carried out on April 13, the 231 Lab received its samples on May 11, and the 234-5 Lab received their samples on May 23, a correction for increase in concentration due to decomposition of the water by alpha particles and evaporation was calculated. It was determined that the results reported by the 231 Lab were very consistent (except for one determination) and that the average value agreed with the gravimetric determination. The average results from the 234-5 Lab are 2% higher than the gravimetric results. Further studies are being made on the chemical …

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"An investigation has been made in the Langley 9- by 12-inch super-sonic blowdown tunnel at Mach numbers of 1.62 and 1.96 of a partial-span body with one tail surface, designed for use on the Hughes Falcon (MX-904) missile. The present paper extends the work reported in NACA-RM-SL50E10. Force and moment data including elevator hinge moment were obtained for the conditions of the tail in the presence of a small segment of the fore-shortened body, in the presence of a semi-span body and attached to a semi-span body, and for the condition of the foreshortened semi-span body alone" (p. 1).

"A method of distributing fuel equally to a plurality of spray nozzles in a gas-turbine engine by means of balanced-diaphragm fuel distributors is presented. The experimental performance of three of eight possible distributor arrangements are discussed. An analysis of all eight arrangements is included. Criterions are given for choosing a fuel-distributor arrangement to meet specific fuel-system requirements of fuel-distribution accuracy, spray-nozzle pressure variations, and fuel-system pressures" (p. 1).

Report presenting an exploratory free-flight investigation at zero lift of several rocket-powered drag-research models with tapered 4-percent-thick wings for a range of Mach numbers. Wings with an aspect ratio of 3.11 and trailing-edge thickness of 0, 1/3 maximum thickness, 2/3 maximum thickness, and 3/3 maximum thickness were tested.

Data are presented showing the penetration characteristics of liquid jets directed approximately perpendicular to a high-velocity air stream for jet-nozzle-throat diameters from 0.0135 to 0.0625 inch, air stream densities from 0.0805 to 0.1365 pound per cubic foot, liquid jet velocities from 168.1 to 229.0 feet per second and a liquid jet density of approximately 62 pounds per cubic foot. The data were analyzed and a correlation was developed that permitted the determination of the penetration length of the liquid jet for any operation condition within the range of variables investigated.

"An investigation of the nature of the flow field behind a rectangular wing of circular arc cross section has been conducted in the Langley 9-inch supersonic tunnel. Pitot- and static-pressure surveys covering a region of flow behind the wing have been made together with detailed pitot surveys throughout the region of the wake. In addition, the flow direction has been measured by means of a weathercocking vane. Theoretical calculations have been made to obtain the variation of both downwash and sidewash with angle of attack by using the superposition method of Lagerstrom, Graham, and Grosslight" (p. 1).

"An investigation of the nature of the flow field behind a rectangular circular-arc wing has been conducted in the Langley 9-inch supersonic tunnel. Pitot- and static-pressure surveys covering a region of flow behind the wing have been made together with detailed pitot surveys throughout the region of the wake. In addition, the flow direction has been measured using a weathercocking vane measurements. Theoretical calculations of the variation of both downwash and sidewash with angle of attack using Lagerstrom's superposition method have been made" (p. 1).

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Price Daniel, regarding a legal question submitted for clarification: Eligibility of a ward of Waco State Home for tuition exemption at Texas A.&M. College under the facts submitted.

Report presenting the damping-in-roll characteristics of three wings with an aspect ratio of 4, a taper ratio of 0.6, an NACA 65A006 airfoil section, and three different sweep angles at a range of Mach numbers and angles of attack. The data were obtained in the 7- by 10-foot tunnel transonic bump by utilizing the twisted-wing technique. Results regarding the damping-in-roll parameter, angle of attack, and lift-curve slope are provided.

This report, compiled by Mr. W. R. Lewis of the Pile Technology Division, is a revision of Document HW-15516 (January 5, 1950) in consideration of new knowledge obtained during the past year. The document discusses the technical factors involved in attaining higher power levels in the various Hanford Piles. The purpose of this presentation is to summarize the present operating limitations and the possibilities of increased production rates. The limitations discussed are: A. Reactivity and flattening; B. Aluminum thimbles; C. Graphite temperature considerations; D. Boiling or vapor binding considerations; E. Tube and slug jacket corrosion; F. Effluent water activity; G. Distortion of the biological shields; H. Radiation considerations; and I. Pile control system capacity.