Several operations that are important to the process as carried out in Task III (Reduction) are performed by the mixer. In order to specify the process certain tests were made to study these operations and are discussed in this report. They include: Mixing Time, Mixer Discharge Rate, Mixer Holdup, and Mixer Capacity. A description of the test, conclusions and recommendations is provided.

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.60 to determine the effects of sweep and thickness on the longitudinal characteristics of a series of wing-body combinations with cambered wings with an aspect ratio of 3.5 and taper ratio of 0.2. The results show the effects of sweep, thickness, and the horizontal canard surface on the lift, drag, and pitching-moment coefficients and lift-drag ratios. The lift-curve slope, aerodynamic-center locations, maximum lift-drag ratios, lift coefficients for maximum lift-drag ratio, and drag-rise factor are presented.

From Introduction: "Previous investigations of a number of internal configurations in the same afterburner shell are reported in reference 1 and 2. In the investigation reported herein, the performance and operational characteristics of three afterburner internal configurations were evaluated."

From Summary: "Such devices as leading- and trailing-edge flaps which are now in use on operational aircraft permit the attainment of maximum airplane lift coefficients, power-off, of the order of 2.8 (reference 1). Airfoil-section maximum lift coefficients as high as 5.5 have been obtained in wind-tunnel tests (see, for example, reference 2), and in a limited flight investigation airplane lift coefficients of 4.2 were obtained (reference 3)."

Report presenting an investigation in an altitude test chamber to evaluate the performance of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers. Reducing the engine inlet Reynolds number resulted in a reduction of corrected air flow and compressor efficiency but did not affect the compressor pressure ratio at a given corrected engine speed.

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The densiies of uranyl sulfate water solutions were measure or 12 concentrations between the temperatures of 20° and 90°C. The density range at 20°C is 1.0539 grams per cubic centimeter at 0.17 molal to 2.0059 grams per cubic centimeter at 3.9 molal.

Report presenting measurements of lift made on various rectangular-plan-form wings differing in trailing-edge thickness, profile shape, maximum thickness ratio, and aspect ratio. Experiments were conducted at a range of Mach numbers, Reynolds numbers, and wings with and without boundary-layer trips. Results regarding a comparison of experimental results with theory at moderate supersonic Mach numbers and calculations for hypersonic Mach numbers are provided.

Report presenting the design, construction, and investigation of an axial-flow compressor inlet stage with a maximum rotor relative inlet Mach number of 1.1. The rotor was designed for a high axial inlet velocity, no inlet guide vanes, and a tip speed of 1000 feet per second. Results regarding the overall performance, rotor inlet conditions, and stator exit conditions are provided.

The report includes a description of the test facilities and methods, crash configuration, layout of crash site, instrumentation, data-recording systems, and the post-crash examination procedure of the fullscale crash-fire investigation, which is part of a comprehensive study of the airplane crash-fire problem.

The preliminary results of a program designed to evaluate methods for preparing uranium hydride from the various oxides of uranium are presented. The apparatus has been designed and constructed for the purpose of carrying out batch reductions under a variety of conditions employing calcium hydride, calcium metal and magnesium metal as the reducing agents. Since the separation of the alkaline earth oxides, present as by-products in the furnace products, promises to be the most difficult problem encountered in this investigation, a major portion of thetime during this past quarterly period has been directed toward the development of a suitable leach method. No investigation of the reduction methods has been possible to date because of the inability to obtain SF materials. A brief outline of the future work is included. (auth)

Report presenting an investigation of a rocket-launched ram-jet engine with radial-burning solid fuel. Results regarding acceleration, altitude, durability of the fuel, net and gross thrust coefficients, and overall fuel specific impulse are provided.

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Abstract: Horse Mesa is in the Navajo Indian Reservation directly on the Arizona-New Mexico state line. Uranium-vanadium deposits in the Salt Wash sandstone which caps the Mesa are fairly widespread and small tonngges have been shipped from two mines. The deposits lie 60 to 75 feet above the base of the Salt Wash formation and possibly trend northwest parallel to ore trends on King Tutt Mesa, a mile northeast. Carnotite and vanoxite are the principal ore minerals. About 6,000 feet of wagon drilling is recommended to test two favorable areas. Continued exploration should be governed by results of this first stage drilling.

Graphite burnout and chemical studies include: carbon dioxide - graphite reaction, controlled gas atmospheres, cyclotron irradiation, graphite - carbon dioxide - helium reaction kinetics. Physical properties studies include: hot test hole irradiation, surface studies, stored energy, physical expansion annealing. The experimental graphite program is discussed to include thermal conductivity and thermal expansion measurements. Also reported are: pile sampling, thermal conductivity of gases, irradiations in the MTR at Arco, in-pile controlled atmosphere program, heat generation in graphite, induction heater, mechanical properties programs and damage mechanism studies.

This report discusses the the surface characteristics of virgin and irradiated artificial graphites and the changes which occur upon irradiation.

In a previous paper a method of measuring the equilibrium constants at various temperatures for the titular reaction has been described. This report applies the method to an investigation of the corresponding reaction of americium, representing a part of a systematic program of investigation of the thermodynamic properties of analogous reactions of lanthanide and actinide elements.

"A qualitative investigation of the low-speed directional behavior of a swept planing-tail hull was made in the Langley tank no. 2 in still water and still air with the use of a free self-propelled model. The configuration was directionally unstable over a range of low speed. It was, however, directionally controllable at all speeds by use of the rudder and elevator. Several modifications that were investigated did not improve the controllability" (p. 1).

The trajectories of droplets in the air flowing past an NACA 651-212 airfoil at an angle of attack of 40 were determined. The collection efficiency, the area of droplet impingement, and the rate of droplet impingement were calculated from the trajectories and are presented herein.

Report presenting an investigation to determine the performance characteristics of a side inlet with boundary-layer control operating in the presence of laminar and turbulent initial boundary layers at a free-stream Mach number of 2.93. Results regarding mass-flow and total-pressure referencing, visual-flow observations, inlet performance, and boundary-layer-scoop performance are provided.

Models of the Hermes A-3B missile were tested in the Ames supersonic free-flight wind tunnel to determine the static-longitudinal-stability characteristics at a Mach number of 5.0 and a Reynolds number based on body length of 10 million. The results indicated that the model center of pressure was 45.3 percent of the body length aft of the nose and the lift-curve slope based on body frontal area was 0.064 per degree. Estimates indicated that the effect on these characteristics of aeroelastic twisting of the model fins was small but important if a precise location of center of pressure is required. A comparison of the test results with predictions based on available theory showed that the theory was useful only for rough estimates, The drag coefficient at zero lift, based on body frontal area, was found to be 0.155.

Report presenting estimates of downwash angles determined from an analysis of pressures measured on the horizontal tail of a supersonic aircraft configuration. The results are compared to an approximate application of linearized theory and force-test results for the same configuration.

Report presenting an investigation of the principal variables affecting the excitation of a propeller for vibration at a frequency of twice propeller speed using a conventional propeller with solid aluminum-alloy blades operating in the wake of a wing. The drag of the wing and spacing between the flap trailing edge and propeller plane were all adjustable. Results regarding wing drag data, vibratory stresses, damping, and theoretical considerations of wake excited blade stresses are provided.

"An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/20-scale model of the Consolidated Vultee XFY-1 airplane with a windmilling propeller simulated to determine the effects of control setting and movements upon the erect spin and recovery characteristics for a range of airplane-loading conditions. The effects on the model's spin-recovery characteristics of removing the lower vertical tail, removing the gun pods, and fixing the rudders at neutral were also investigated briefly. The investigation included determination of the size parachute required for emergency recovery from demonstration spins" (p. 1).