Abstract: "Thorium tubes were cold drawn from extruded tube stock and also from drilled hot-rolled rod. Total reductions up to approximately 85 per cent were accomplished by conventional tube-drawing methods, without an intermediate anneal. The hard-drawn tubes had high tensile strength, but the ductility, as indicated by flaring and flattening tests, was low."

From abstract: "The stability of polystyrene and phenolic ion-exchange resins to radiation from a Co60 source and from absorbed Ce144-PR144 was investigated. Sulfonated polystyrene cation-exchange resins lost 10 to 20% of their capacity per watt-hour of radiation absorbed per gram of oven-dry resin, while the quaternary amine anion-exchange polystyrene resins lost about 40%. Phenolic cation-exchange resins lost only 1%."

Abstract: "The valve-actuated pulse column is employed to give phase separation on each half cycle in the countercurrent flow cycle and provides independent control over each step in the cycle. The dependence on temperature of operation, on pulse frequency and amplitude, and on plate design and spacing has been studied for extraction and stripping of uranium with tributyl phosphate in a hydrocarbon diluent. It is found that the efficiency increases quite significantly as the temperature is raised regardless of the direction of transfer and this increased efficiency is accompanied by greater operational freedom. A decrease in hole size, decrease in plate separation and increase in frequency all lead to higher efficiency in agreement with the concept that small drops continually formed coalesced and reformed, lead to maximum interphase transfer. The high extraction efficiency of the column is probably aided further by the relatively sharp pulse produced."

Introduction: "In connection with conducting neutron experiments in a pit with earth and concrete walls, it was proposed that the background flux of neutrons might be reduced by lining the walls of the pit with a neutron absorber such as boron. To determine how much liner material would be desirable and what diminution in the neutron background could be expected, the following measurements were undertaken."

Report discussing tests conducted in an attempt to adapt a micromanometer for use in measuring variations of about 0.003 mm Hg in atmospheric pressure. Additionally, a method for making full use of the micromanometer sensitivity and extending its range is described.

Weekly report discussing the state of the raw sugar market, including details for prices and market fluctuations related to weights in tons, regions, distribution, years, and figures.

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Daily cash report for Imperial Sugar Company including a list of large withdrawals for the months surrounding the date showing the daily expenses and estimated balance for each entry.

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Report presents the results of an investigation conducted to determine the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA rm-10 without fins) at Mach number of 1.61 and over a Reynolds number range from 2.5 x 10(6) to 35 x 10(6). The maximum cooling of the model used in these tests corresponded to a temperature ratio (ratio of model-surface temperature to free-stream temperature) of 1.12, a value somewhat higher than the theoretical value required for infinite boundary-layer stability at this Mach number. The maximum heating corresponded to a temperature ratio of about 1.85. Included in the investigation was a study of the effects of surface irregularities and disturbances generated in the airstream on the ability of heat transfer to influence boundary-layer transition.

Report presenting testing of the transonic longitudinal characteristics of a model of the McDonnell XF3H-1 airplane. The model had a center-of-gravity location of 28.5 percent of the mean aerodynamic chord and a stabilizer setting of -5.91 degrees relative to the wing chord plane with extensible rocket racks. Results regarding Reynolds number, rocket-rack program, flight time history, trim, lift, drag, longitudinal stability, directional stability, and inlet pressure recovery are provided.

Memorandum presenting steady-state and transient characteristics of the J34-WE-32 turbojet engine with electronic power regulator as obtained in the altitude wind tunnel to determine the effects of engine and control limits on the performance. Limits on the fuel valve and exhaust nozzle area influence any schedule of speed and temperature. Results regarding the effect of limits on operating schedule, effect of altitude on safe operating range, effect of minimum fuel flow settings on transient performance, and some potential problems are provided.

Report presenting testing of two rocket-propelled research models to determine the effect of the intersection of thin aerodynamic surfaces and the effect of moderate sweepback of thick aerodynamic surfaces on low-lift buffeting. Results regarding trim changes and drag are also provided. It was discovered that low-lift buffeting may be induced at high subsonic speeds by interference due to the intersection of thin aerodynamic surfaces.

"An investigation was conducted in the Lewis altitude wind tunnel to evaluate the performance and operational characteristics of the J40-WE-8 afterburner. A brief program of minor modifications to the flame holder, diffuser, and fuel system was undertaken to improve at a burner-inlet pressure level of 620 pounds per square foot. At this pressure level, modifications to the fuel system resulted in an increase in maximum net thrust from 1500 to 1600 pounds and a reduction in specific fuel consumption in the stoichiometric region from 3.70 to 3.15 pounds of fuel per hour per pound of net thrust" (p. 1).

Memorandum presenting the aerodynamic characteristics of a model of an air-to-air missile employing variable-incidence cruciform wings of rectangular plan form and a fixed cruciform tail of rectangular plan form, an the characteristics of its body-wing and body-tail components, as determined from a wind-tunnel investigation for Mach numbers of 1.4 and 1.9. The results include normal-force, pitching-moment, and axial-force data for the body-wing-tail, body-wing, and body-tail combinations, and normal-force, hinge-moment, and axial-force data for the individual panels.

Report presenting an investigation of the performance of a 20-inch-diameter ramjet engine with a high-heat-release pilot burner conducted at zero angle of attack in a free-jet test facility at a Mach number of 3.0. Two flame-holder configurations were used in conjunction with the high-heat-release pilot burner over a range of altitudes. Results regarding the performance of the high-heat-release pilot burner and performance of combustion-chamber configurations are provided.

"A metal-ceramic composition containing approximately 80 percent chromium plus 20 percent aluminum oxide (Al(sub 2)O(sub 3)) by weight has been investigated for possible gas-turbine blade use. The results of modulus-of-rupture, thermal-shock, and blade-performance studies indicate that this material may have adequate thermal-shock resistance; however, the strength for the application appears marginal" (p. 1).

Memorandum presenting tests of two airplane models with trapezoidal wings of aspect ratio 2 and taper ratios of 0.33 and 0.20. For each model, a fuselage with a fineness ratio of 12.5, a thin, triangular, vertical tail with a constant-chord rudder, and a thin, unswept, all-movable horizontal tail was used. Tests of the wing-fuselage vertical-tail configuration and of the complete airplane model were made for both models.

Report presenting the aerodynamic characteristics of three wing-body combinations with wings of aspect ratio 2 and rectangular, swept-back, and triangular plan form and a comparison at subsonic and supersonic speeds. All three wings had 3-percent-thick airfoil sections and were investigated with biconvex and rounded-nose airfoil sections. Results regarding the effects of wing plan form, effects of airfoil-section thickness distribution, and effects of Reynolds number are provided.

Memorandum presenting an investigation of the evaporation and spreading of isooctane sprays over a range of inlet-air conditions common in ram-jet engines. The total and liquid fuel distribution across the duct were determined. Over the specified ranges in the investigation, expressions were obtained which related the evaporation rate and degree of spreading of the sprays to the experimental variables.

From Summary: "An air-launched cone-cylinder test vehicle designed to obtain data at Mach numbers above 4.0 was rocket boosted from a release Mach number of 5.18. The vehicle was launched at an altitude of 35,000 feet and reached peak velocity of 5150 feet per second at 28,500 feet. The total-drag coefficient (based on maximum cross-sectional area) decreased gradually from 0.31 at a Mach number of 1.75 to 0.145 at a Mach number of 5.18, while the Reynold's number (based on body length) increased from 31 x 10 to the 6th power to 107 x 10 to the 6th power."

From Summary: "Current NACA research on the subject of jet effects on the flow over afterbodies in a supersonic stream is briefly summarized. Several jet nozzle types installed in various afterbody configurations are considered for a wide range of operating conditions."

Report presenting specimens of five different root designs, proportioned in accordance with the design surveys, and specimens of a conventional fir-tree turbine root were fabricated from a titanium carbide cement bonded with nickel. Comparative strengths were determined by short-term tensile tests at 1200 degree Fahrenheit. Results regarding blade root evaluation and rotor-segment evaluation are provided.

From Summary: "Ignition delays of several propellant combinations obtained with a modified open-cup apparatus and with a small-scale rocket engine of approximately 50-pounds thrust were compared to study any correlations that might exist between the two methods of ignition-delay determination. The results were used in determining the relative utility of each apparatus."