This technical report is the second of a series which concerns the separation of ions by solvent extraction with trialkyl phosphine oxides (TOPO). This investigation has consisted in the extraction of various ions from acidic solutions with extractants that are representative of these ore specific phosphine oxides - triphenylphosphine oxide (THPO) and tris-2-ethylhexylphosihine oxides (TEHPO). In general it is observed that: (a) the order of increasing capacity of extraction is THPO > TOPO >TEHPO. (b) No ion is extracted by THPO or TEHPO that is not extracted by TOPO under certain conditions. (c) The effect of hydrogen ion concentration is greater in TEHPO systems than it is in the other two, which indicated greater selectivity of extraction with TEHPO.

Memorandum presenting an investigation made in the stability tunnel with a 2.3-scale spinning model of a typical mortar shell. The tests were made to measure the aerodynamic forces and moments acting on a typical spinning mortar shell. Results regarding the basic configuration, effect of changes in tail configuration, effect of changes in the nose configuration, and comparison of mortar shell and antisubmarine rocket are provided.

Techniques are described for determining U-235 abundance by measurement of the intensity of 0.18 Mev gamma radiation. One method involves measurement of the ratio of the intensity of 0.18-Mev radiation to that of 0.1 Mev radiation. The preferred technique consists of chemical separation of uranium followed by direct counting of 0.18-Mev photons. Application has been made in analysis of uranium samples of abundances in the range of 0.05% to 93%. Accuracy appears to be better than 3% if the abundance is between 0.7% and 100%. Findings in the self-absorption of 0.18 Mev radiation in uranium oxide are presented.

Memorandum presenting an investigation to determine the performance of the J65-B-3 turbojet engine with JP-4 and gaseous-hydrogen fuels. With JP-4 fuel, the maximum altitude for stable combustion was from about 60,000 to 65,000 feet, and the ultimate blowout limit was at an altitude of about 75,000 feet. The steady-state performance with either fuel decreased considerably with increasing altitude.

Report presenting an investigation to determine the performance of the J65-B-3 turbojet engine with JP-4 and gaseous-hydrogen fuels. With JP-4 fuel, the maximum altitude for stable combustion was from about 60,000 to 65,000 feet and the ultimate blowout limit was at an altitude of about 75,000 feet. Combustion with hydrogen was found to be stable up to the facility altitude limit of 89,000 feet.

.Recalculations were made of HRT cell pressures in the event of a simultaneous rupture of the reactor core vessel and the fuel and blanket heat exchangers. These calculations will be applicable after the replacement fuel heat exchanger is installed. The pressure rise in the cell is plotted as a function of time. A maximum cell pressure of 34 psig is achieved ~7 sec after rupture.

A letdown valve design is described which reduces erosion of the sealing surfaces. It also provides for water flushing of the sealing surface before closing.

From Introduction: "The present report is concerned with the characteristics of a body in the two-dimensional flow field of a circular-arc wing of rectangular plan form."

Report presenting wind-tunnel testing to evaluate the effects of wing fences and a tail on the longitudinal characteristics of a highly swept wing in combination with a fuselage. The model, which had a cambered and twisted wing with a leading-edge sweepback of 63 degrees and an aspect ratio of 3.5, was tested with fences of various shapes and swept and unswept horizontal tails. Results regarding exploratory tests, final-configuration tests, static longitudinal stability factors, and maximum lift-drag ratios are provided.

"Presented in this report is a summary of local and net angle-of-attack wing-panel loads measured in flight on six airplanes. In addition, a comparison of these loads measured in flight with calculations based on simple theory is presented" (p. 1).

Memorandum presenting a procedure for reducing the interference pressure drag of the root and tips of sweptback wings. Experimental and theoretical pressure-drag values over a range of Mach numbers for configurations designed by the method were compared with the values of two similar configurations designed by the transonic and supersonic area-rule methods. Results regarding total drag, pressure drag, and drag comparison are provided.

Thesis presenting data taken on experimental nuclear magnetic moments for beta spectra of the mirror nuclei with A-19 to 39.

Report presenting pressure distribution associated with the stable combustion of aluminum borohydride about a body of revolution in a wind tunnel at Mach number 2.47. Pressure increases on the cylindrical and base surfaces of the model were measured. Results regarding the burning and associated flow phenomena, axial and meridional static-pressure data obtained during combustion, and base-pressure data during combustion are provided.

From Summary: "Nine divergent-shroud ejector configurations were investigated to determine the effect of shroud divergence angle on ejector internal performance. Unheated dry air was used for both the primary and secondary flows. The decrease in the design-point thrust coefficient with increasing flow divergence angle (angle measured from primary exit to shroud exit) followed very closely a simple relation involving the cosine of the angle. This indicates that design-point thrust performance for divergent-shroud ejectors can be predicted with reasonable accuracy within the range investigated."

From Summary: "Use of a normal-shock positioning control was demonstrated at Mach numbers of 1.8 and 2.0 for a translating-spike supersonic inlet in combination with a J34 turbojet engine. Stable operation of the control was obtained which can be partly attributed to a nonlinearity in the servo valve in the null region."

Static tests were made on the compatibility of liquid fluorine with several nonmetallic materials at -3200 F and at pressures of 0 and 1500 pounds per square inch gage. The results are compared with those from previous work with gaseous fluorine at the same pressures, but at atmospheric temperature. In general, although environmental effects were not always consistent, reactivity was least with the low-temperature, low-pressure liquid fluorine. Reactivity was greatest with the warm, high-pressure gaseous fluorine.