Report issued by the APDA over studies conducted on hypothetical fast reactor meltdown accidents. As stated in the summary, "the purpose of this study is to investigate the technical feasibility of conducting fast reactor meltdown experiments to determine a more realistic maximum accident and to provide a better evaluation of fast reactor safety" (p. 7). This report includes tables, and illustrations.

Abstract: "Dissolution of carnotite in several readily liquefiable gases, including ammonia, sulfur dioxide, chlorine, and nitrogen dioxide, was found to be negligible, even in the presence of uranium complexing agents. No low-boiling liquids have been found which will dissolve carnotite directly. Treatment with various sulfur chloride will convert carnotite to a form soluble in water or in certain organic solvents. Also, carnotite can be readily dissolved in HCl-acidified ethanol, methanol, or acetone. Amenability tests on nine western ores with HCl-methanol solvent indicated that uranium extractions greater than 90 per cent could be obtained if sufficient acid was used to insure some free acidity in the pregnant liquor. Temple Mountain and Sinbad-Muddy River ores were exceptions to this, uranium extractions being only about 50-60 per cent. Vanadium extractions were invariably lower than uranium extractions. Chemical analyses are presented for nine western ores."

This report follows an investigation made on the welding of Ames thorium by the inert-gas-shielded tungsten-arc process as the first part of a program on the joining of thorium. This program is part of a broader research program to develop the technology of thorium.

Report presenting an investigation of the performance of a diffuser static-pressure-ratio control with a normal shock-positioning limit on a ramjet engine installed in an altitude free-jet facility. Testing occurred at Mach numbers of 2.35 and 2.50, altitudes of 50,000, 60,000 and 65,000 feet, and angles of attack of 0 and 7 degrees. Results regarding the effects of control constants, effects of disturbance size and operating point, effects of flight conditions, and control limitations and possible improvements are provided.

From abstract: "The reaction between hydrogen and oxygen with the aid of various catalysts (especially platinum on aluminua) has been studied, and the operating variables such as flow rates, space velocity, temperature, and gas composition have been examined rather extensively. It has been found that hydrogen and oxygen in stoichiometric proportions and mixed with either steam or helium may be made to react to the extent of 99.5% or greater at space velocities up to 30,000 hr-1, or even higher, at temperatures from 100[degrees] to 900[degrees]C, and with mixtures ranging from less than 1% hydrogen to mixtures containing 12% hydrogen and 6% oxygen. Richer mixtures, including undiluted electrolytic gas (H2 + 1/2 O2) have been used with catalysts less active than platinum (e.g. copper, silver, nickel and V2O5) but here the gas mixture is explosive and care must be taken to prevent explosions. The thermal reaction between hydrogen and oxygen diluted with steam has also been investigated at temperatures between 500[degrees] and 800[degrees]C."

From introduction: This report reviews the Susie program (particularly reactor dosimetry and data analysis) as well as other items that represent a smaller share of the total effort.

From introduction: Included is a summary of the work on five of the eighteen specific development programs in progress.

From introduction: "The purpose of this report is to summarize some of the information obtained to date on the distribution of the uranium in the mineral phases of the phosphate rocks and shale."

Injection techniques for fluorine, oxygen, and heptane in 200-pound thrust rocket engine.

"A 1/13-scale model of the forebody of the Republic F-105 with twin-duct wing-root inlets was tested in the Langley 4- by 4-foot supersonic pressure tunnel through a range of angle of attack from -4 deg to 15 deg at a Mach number of 2.01 and a Reynolds number of approximately 3.4 x 10(exp 6) per foot. The tests were made with four configurations which incorporated varying amounts of sweep and stagger of the inlet leading edges, modifications to the areas of the boundary-layer diverter floor plate, and modifications to the area of the boundary-layer diverter bleed slots. The highest overall pressure recovery at an angle of attack of 0 deg (average total-pressure recovery, 0.84 mass-flow ratio, 0.98) was achieved with configuration having an inlet leading-edge sweep angle of 58 deg with no leading-edge stagger" (p. 1).

From Introduction: "The feasibility of closed-loop control of ram-jet-engine thrust is demonstrated in references 1 and 2. The dynamic behavior of a 28-inch-diameter ram-jet engine designed to operate in Mach number range of 2.35 to 2.70 is evaluated herein."

Report presenting an investigation to study some factors affecting the drag of relatively large nonlifting bodies of revolution at transonic speeds in the 8-foot transonic tunnel. Drag and surface pressure measurements were made for two geometrically similar bodies of revolution of 8-inch and 4-inch maximum diameter at zero angle of attack through a range of Mach numbers.

Report presenting a low-speed wind-tunnel investigation to determine the high-lift characteristics of a thin delta wing equipped with a single and double slotted trailing edge flap. Results regarding the lift, drag, and pitching-moment characteristics of the plain wing and various flap configurations are provided. The maximum lift coefficient of the model could be increased from 1.45 for the plain wing to 1.86 when the double slotted flap was deflected to 50 degrees.

Report presenting an experimental investigation to determine some of the characteristics of an inset tab as an aerodynamic balance in the Mach number range between 0.7 and 1.4 using a zero-lift rocket-propelled model in free flight. Results regarding the variation of the aileron floating angle, the wing-tip helix, the balancing effect, and the penalty occurred throughout the Mach number range are provided.

Report presenting an investigation of the hydrodynamic characteristics of a model of a 130,000-pound transonic flying-boat design with a high length-beam ratio planing-tail hull, sweptback gull wings with wing-tip floats, and wing-root jet-power-plant installation. Results regarding the aerodynamic, hydrostatic, and hydrodynamic qualities are provided.

Memorandum presenting an investigation of the stability and controllability in space of an arrangement comprising a man standing on a small platform which is rigidly connected to a jet nozzle with its thrust axis perpendicular to the platform and its thrust opposed to the pull of gravity. Results regarding the initial flights with the platform, flights with landing gear, flights with landing gear and inertia, flights with landing gear and gyroscope, flights with landing gear and control stick, flights with landing gear and seat, and discussion of the balancing process are provided.

Report presenting an investigation in the 7- by 10-foot tunnel to determine the transonic aerodynamic characteristics of a wing with a spanwise variation in thickness ratio. The wings investigated had 45 degrees of sweepback, aspect ratio 8, taper ratio 0.45, and airfoil sections tapered from an NACA 63A010 section at the root chord to an NACA 63A006 section at the tip chord. Results regarding lift characteristics, drag characteristics, and pitching-moment characteristics are provided.

An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel at Mach numbers 1.40 and 1.59 to determine the effect of aileron profile on the aerodynamic characteristics of a complete model of a supersonic aircraft configuration. The model had a 40 degree sweptback tapered wing with 10-percent-thick circular-arc sections normal to the quarter-chord line. The ailerons were 20-percent chord and were located on the outboard 50 percent of the wing semispans. The various ailerons investigated included the basic circular-arc profile and three flat-sided ailerons having ratios of trailing-edge thickness to hinge-line thickness t of 0, 0.5, and 1.0. Low aileron effectiveness was obtained with the circular-arc and t = 0 profiles. Increasing the trailing-edge thickness (t = 0.5 and 1.0) resulted in increased effectiveness as well as increased hinge moments with only a slight increase in drag.

From Summary: "A theoretical analysis is presented that permits estimation of the changes in piston-temperature distribution induced by variations in the crown thickness, the ring-groove-pad thickness, and the undercrown surface heat-transfer coefficient. The analysis consists of the calculation of operating temperatures at various points in the piston body on the basis of the experimentally determined surface heat-transfer coefficients and boundary-region temperatures, as well as arbitrarily selected surface coefficients."

Memorandum presenting a corrosion investigation conducted with molten sodium flowing at a velocity of 25 feet per second in a toroid of AISI type 347 stainless steel with an insert consisting of seven Globeiron tubes in parallel at the hot zone. A 500-hour test was run at a nominal outer wall temperature of 500 degrees Fahrenheit with a temperature difference between the hot and cold sections of 40 degrees.

Introduction: The effects of temperature on the mechanical properties of Zircaloy-2 containing up to 7.5 wt % niobium and 3500-ppm oxygen were studied and are presented herein.

A report describing a the results of a fluorimetric and volumetric method for the determination of fluoride. This method was developed for the determination of ionizable fluorine in gases in the range of 1-500ppm. This method was chosen because the determination depends on the generation of a color rather than the bleaching effect or on a change of color.

Work performed during the quarter is summarized by: direct measurement of fission gas pressure, loop operations, performance of UO2 fuel, UO2 grain growth and melting studies.

"This report covers mainly the work completed since the last interim report, HNL Log No. 0-4714. This report includes results from studies of the rare earth distribution in bismuth-uranium and fused chloride and studies of fused chloride behavior."