Data were obtained in non-flowing and flowing (continuous) batch adsorption systems to serve as a guide to the operating conditions that should be used in a resin-in-pulp adsorption system for the recovery of uranium from ores.

The use of diffusion theory to attempt to reproduce the chemical data of Hicks and Stevenson for the spatial distribution of neutrons in a solid block of uranium that is bombarded by 190 Mev neutrons is described.

"The flow-field characteristics around a swept-wing airplane model at low subsonic speed are described, and the loads induced on a typical missile model while operating within these flow fields are presented. In addition, theoretical flow fields are compared with experiment and are used in first-order estimations of the resulting induced missile loads" (p. 1).

A low-speed wind-tunnel investigation has been made of some aspects of the aerodynamic problems associated with the use of air-to-air missiles when carried externally on aircraft. Measurements of the forces and moments on a missile model for a range of positions under the mid-semispan location of a 45deg sweptback wing indicated longitudinal and lateral forces with regard to both carriage and release of the missiles. Surveys of the characteristics of the flow field in the region likely to be traversed by the missiles showed abrupt gradients in both flow angularity and in local dynamic pressure. Through the use of aerodynamic data on the isolated missile and the measured flow-field characteristics, the longitudinal forces and moments acting on the missile while in the presence of the wing-fuselage combination could be estimated with fair accuracy. Although the lateral forces and moments predicted were qualitatively correct, there existed some large discrepancies in absolute magnitude.

"Theoretically derived charts and equations are presented by which tail-rotor design studies of directional trim and control response at low forward speed can be conveniently made. The charts can also be used to obtain the main-rotor stability derivatives of thrust with respect to collective pitch and angle of attack at low forward speeds. The use of the charts and equations for tail-rotor design studies is illustrated. Comparisons between theoretical and experimental results are presented. The charts indicate, and flight tests confirm, that the region of vortex roughness which is familiar for the main rotor is also encountered by the tail rotor and that prolonged operation at the corresponding flight conditions would be difficult" (p. 1).

A study of the variables involved in regeneration was undertaken to determine means of improving the regeneration efficiency and increasing the useful life of a reactor. Information gained from regeneration studies on a 4-inch-diameter by 8-foot-high column indicates that the present regeneration procedure is optimum as to quantity, concentration, and rate of addition of regenerant solution. It appears feasible to restore a plugged reactor by washing off all the silver nitrate from the packing and recoating by a normal regeneration cycle. Such a procedure could be utilized only if there is sufficient dead space in the bottom of the reactor to hold the wash solution.

It is recommended that self-concentration of Purex wastes should not be started until much more complete knowledge is obtained of the conditions and reactions in these wastes. The presently planned tests in the Semi-Works will be a practical demonstration of the problems but will be of little value on the initial Purex wastes as these tests are being run almost concurrent with the filling of the first Purex storage tank.

Report presenting the results of strength tests on thick-skin wing structures. Some of the factors that were found to have influence on the buckling behavior and strength are shown with data and the conditions under which a combination of multiweb and multipost construction may be used are discussed. Results regarding circular-arc airfoils, multiweb beams, and multipost stiffened beams are provided.

Report regarding the mathematical analysis of the exponential pile experiment using highly absorbent slugs and assuming the emitting of fast neutrons. Related theory and equations are discussed.

Report presenting methods for estimating the aeroelastic effects and structural requirements of rocket-propelled model-booster combinations that are nearly symmetrical. The methods differ principally in the manner in which booster stiffness, reference axis, and inertia loading are considered. Special conditions and accuracy for each of the three models are provided.

Report presenting testing of a medium-camber compressor rotor with particular NACA blades in a low-speed 28-inch test blower. Testing was made at solidities of 1.0 and 0.5 without guide vanes or stators over a wide range of blade-setting angles and quantity flow rates. Results regarding overall rotor performance, comparison between measured and estimated section efficiencies near design angle of attack, comparison between low-speed rotor and cascade turning angles, and detailed blade section performance are provided.

Calculations are presented regarding the effect of delayed neutrons in reactors fueled with mixtures of Pu²³⁹ and U²³⁵. Results are plotted to illustrate the change in thermal flux as a function of time for various positive or negative step changes in reactivity.

The basic investigation of transistor feedback amplifiers has proven mathematically simple and of great practical value. The behavior of single-stage common-emitter amplifiers is described and provides a building block with which cascaded feedback amplifiers can be analyzed and designed. From the results of this analysis the conditions for minimum drift for cascaded single-stages and cascaded loops have been derived.

An improved continuous ether extractor is described. The modifications include a means of safely disposing of the active raffinate and a means of positivity checking the raffinate for completeness of uranium extraction. The results obtained on synthetic samples and on dissolver solutions are given. This work was undertaken because of a need for the determination of uranium in dissolver solutions with an accuracy of 0.1 per cent. After a review of available methods it was decided that a gravimetric determination would meet the requirements of precision and accuracy.

Pressure-recovery characteristics of a nacelle-type-spike inlet in combination with a vertical-wedge auxiliary scoop are presented for a free-stream Mach number of 1.9 at zero angle of attack. The auxiliary scoop provided 17 percent additional air flow with a drop in critical pressure recovery from 0.86 to 0.81. However, in terms of inlet-engine matching, the pressure recovery of the undersized spike inlet operating at a specified corrected air flow increased with the scoop open, for example, from 0.69 to 0.81.

Report presenting calculations of the dynamic lateral stability characteristics of a mock-up configuration of the Douglas X-3. The oscillations were found to be stable for all calculations investigated but would not meet the Air Force damping requirements for the majority of the conditions. The use of an autopilot was found to greatly improve oscillation damping.

Memorandum presenting a screening of various hydroxides for use in nuclear reactors as possible coolant moderators for operation at temperatures of about 1500 degrees Fahrenheit. The hydroxides that appear stable at a pressure of about 1 atmosphere are those of sodium, potassium, rubidium, lithium, barium, and strontium. Results regarding the core uranium investments and reflector savings are provided.

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.

"An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a l/19-scale model of the North American T-28C airplane to determine the spin and recovery characteristics. The T-28C airplane is similar to the T-28B airplane except for slight modifications for the arresting hook. The lower rear section of the fuselage was cut out and, consequently, the lower part of the rudder was removed to make a smooth fairing with the fuselage" (p. 1).

Report presenting an investigation in the 20-foot free-spinning tunnel on a scale model to determine the spin and recovery characteristics of the Douglas F4D-1 airplane equipped with external fuel tanks. Results regarding erect spins, inverted spins, and parachute results are provided.

Memorandum presenting an investigation in the 20-foot free-spinning tunnel on a scale model to determine the spin and recovery characteristics of the Douglas F4D-1 airplane with external wing fuel tanks installed. The results indicated that any fully developed erect spin obtained on the airplane with tanks installed will be satisfactorily terminated by rudder reversal accompanied by moving the ailerons to full with the spin.

The performance of MIL-F-5624A fuels, grades JP-3 and JP-4, was investigated in an axial-flow turbojet engine over a range of altitude conditions of 10,000 to 55,000 feet. Examination of the fuel flow, combustion efficiency, and net thrust specific fuel consumption showed the grade JP-4 fuel to be slightly inferior to the grade JP-3 fuel, although the altitude ignition limits were essentially equal for the two fuels over a range of flight Mach numbers and fuel-inlet temperatures.

The following report discusses laboratory investigations of the suitability of some commercially available limestone for neutralization of slightly acidic distillates.

Technical report detailing expansion of the Aircraft Nuclear Propulsion at the Oak Ridge National Laboratory. Major facilities completed at this time were the Shielding Rector, the ANP Critical Facility, and the 86-in. Cyclotron. Outlines further need for radiation damage studies. [From Summary]