The investigation of magnesitic-dolomite uranium ores from Union Miniere du Haute Katanga, Belgian Congo, was undertaken in order to examine the possibility of separating the uranium minerals from the carbonate minerals by Heavy Media Separation or froth flotation; thus reducing the sulfuric acid consumption during the uranium leach. In addition, the effect of carbonate leaching the whole ore and carbonate flotation products was examined.

Abstract: "A magnetically operated pump has been constructed and used successfully to pump a mixture of uranium hexafluoride and hydrogen fluoride gases at pressures up to 175 psia. and temperatures up to 100 C."

A method is described for recovery of uranium from sulfuric acid leach liquors of Congo ores using anion exchange resins. Excellent uranium recoveries were obtained in cyclic tests which indicate uranium capacities of 11 to 26 lbs. of U3O8 per cubic foot of resin per day. Preliminary tests indicate that sulfuric acid may be as effective as hydrochloric acid in providing the required acidity in the eluant.

Report documenting the suitability of Montana for plant locations to produce synthetic liquid fuels, based on raw materials, water sources, and local interest

Report documenting the suitability of New Mexico for plant locations to produce synthetic liquid fuels, based on raw materials, water sources, and local interest

Report presenting a measurement of the magnitudes of pressure fluctuations in the turbulent wakes of restrained two-dimensional airfoils at transonic speeds. Measurements indicated that the total-pressure fluctuations occurred only within the wake. Results regarding the magnitude of pressure oscillation in the wake, effect stream-angle fluctuations in the wake, and frequencies of pressure oscillation on the wing and in the wake are provided.

Leaching of high carbonite Belgian Congo uranium ores with sulfuric acid and recovery of the uranium from leach solutions by uranous phosphate precipitation are described.

From Summary: "Measurements of base pressure are presented for 29 blunt-trailing-edge wings having an aspect ratio of 3.0 and various airfoil profiles. The different profiles comprised thickness ratios between 0.05 and 0.10, boattail angles between -2.9 degrees and 20 degrees, and ratios of trailing-edge thickness to airfoil thickness between 0.2 and 1.0. The tests were conducted at Mach numbers of 1.25, 1.5, 2.0, and 3.1. For each Mach number, the Reynolds number and angle of attack were varied. The lowest Reynolds number investigated was 0.2 x 10(6) and the highest was 3.5 x 10(6). Measurements on each wing were obtained separately with turbulent flow and laminar flow in the boundary layer. Span-wise surveys of the base pressure were conducted on several wings."

Critical mass of an Oy (93.9%) sphere in graphite is given as a function of graphite tamper thickness. It was shown that approximately 20(in) of graphite is effectively infinite and that the approximately 17(in) used herein is approximately 98% infinite. Critical mass measurements of Oy (93.9%) spheres and cylinders of different diameters are given for approximately 17(in) graphite tamper, for effectively infinite paraffin tamper, and for effectively infinite water tamper. From these measurements cylindrical shape factors were computed. Both shape factors and critical masses are shown in Figs. 22 and 23 as function of the critical height to diameter rate of the cylinders.

Report presenting base pressures measured on several fin-stabilized bodies of parabolic-arc profile in free flight at a range of Mach and Reynolds numbers. The bodies varied in length but had the same afterbody ratios. Results regarding base pressure coefficients, side pressure coefficients, effect of afterbody length, and drag are provided.

A set of modified NACA 65-series blower blades designed for axial inlet velocity, high inlet Mach number, and high blade loading was investigated for trailing-edge thickness of 0.015, 0.030, and 0.045 inch to determine the effect of trailing-edge thickness on single-stage axial-flow-compressor performance. Trailing-edge thickness effects were small except at the highest tip speed investigated (915 ft/sec). Trailing-edge thickness up to 30 percent of maximum blade thickness were used without sacrifice of performance of NACA 65-series blades.

Memorandum presenting results obtained during Air Force testing of the Northrop X-4 airplane. Information is included on the stalling characteristics, the static and dynamic longitudinal and lateral-stability characteristics, and the lateral-control characteristics.

Report presenting a study of the pressure-drag reduction obtained by projecting a high-energy jet of air from the nose of a prolate spheroid at transonic speeds. Results regarding the pressure distribution on the body, pressure drag, shadowgraphs, and some notes regarding the slope of the body and level of shear at the jet exit are provided.

A vector study of the partial-differential equation of steady linearized supersonic flow is presented. General expressions which relate the velocity potential in the stream to the conditions on the disturbing surfaces, are derived. In connection with these general expressions the concept of the finite part of an integral is discussed. A discussion of problems dealing with planar bodies is given and the conditions for the solution to be unique are investigated. Problems concerning nonplanar systems are investigated, and methods are derived for the solution of some simple nonplanar bodies. The surface pressure distribution and the damping in roll are found for rolling tails consisting of four, six, and eight rectangular fins for the Mach number range where the region of interference between adjacent fins does not affect the fin tips.

Abstract: Mesas 1 1/2 and II 1/2 were investigated in October 1951, to determine the extent and degree of uranium mineralization in the Salt Wash sandstone. Carnotite-vanoxite-type minerals are sufficiently concentrated to recommend 14,600 feet of drilling.

The altitude-ignition limits of a condenser-discharge ignition system installed on a turbojet engine were determined at a flight Mach number of 0.6 using 1.1-pound Reid vapor pressure fuel. Ignition was possible up to an altitude of 55,000 feet with 4.8 joules per spark and 6 sparks per second.

Memorandum presenting the results of an experimental investigation to determine the effects of Reynolds number on the flow characteristics over a delta wing at a Mach number 2.41. The wing streamwise airfoil sections are based on the NACA 00-thickness series with the maximum thickness varying from 4 percent at the root section to 6.24 percent at the 90-percent spanwise station. Results regarding force data and pressure-distribution data are provided.

Testing occurred using the NACA wing-flow method at a range of Mach numbers to determine the effect on aerodynamic characteristics of reversing a triangular wing with a 6-percent-thick biconvex section. Results regarding the lift characteristics, drag characteristics, and pitching-moment characteristics are provided.

Report presenting the low-speed lateral control and hinge-moment characteristics of a 20-percent-chord plain aileron on a 47.7 degree sweptback wing of aspect ratio 5.1 in the pressure tunnel. The tests were performed with and without high-lift and stall-control devices. Results regarding the basic aileron data, rolling-moment characteristics, and pitching-moment characteristics are also provided.

Report presenting an investigation of the longitudinal characteristics of a wing with 45 degree sweepback of the quarter-chord line, an aspect ratio of 8, a taper ratio of 0.45, and NACA 63(sub)1A012 airfoil sections. The results were obtained from force measurements and distribution measurements for a range of Reynolds numbers. Information regarding lift and pitching-moment characteristics, drag characteristics, and loading characteristics is provided.

An experimental investigation of a highly loaded two-stage turbine with a downstream stator revealed that (1) at equivalent design work and speed the brake internal efficiency was 0.81 and the maximum efficiency obtained was 0.85, and (2) the downstream stator left very little energy in the form of tangential velocity in the gas and, in general, performed well with 0.78 recovery being obtained at equivalent design work and speed.

Report presenting a large wind tunnel that has been converted to transonic operation by means of slots in the boundary extending in the direction of flow. The usefulness of a slotted wind tunnel has been augmented by devising a slot shape with which a supersonic test region with excellent flow quality can be produced.

An air-cooled turbine blade with a capped leading edge was investigated in a modified commercial turbojet engine over a range of engine speed from 4000 to 11,350 rpm. The cooling performance of the caped-leading-edge configuration was superior to all leading-edge cooling modifications previously investigated.

Fundamental flame velocities are reported for pentane air, ethylene-air, and propylene-air mixtures for the concentration range 60 to 130 percent of stoichiometric. A form of the Tanford and Pease equation, which includes a small constant velocity term independent of diffusion, will predict the observed changes in flame velocity.