Introduction. As has been shown by Post, the total power required to produce a strong, steady-state magnetic field is strongly dependent upon the temperature at which the electrical conductor of the magnet operates. The power required for operation at very low temperature can, in some cases, be much less than that required for ambient temperature operation. The power required for low temperature operation depends on many system characteristics which include the metal chosen for the electrical conductor, the purity of this metal, and efficiency of the refrigeration equipment. This paper shows the relative power requirement, as a function of temperature, of a magnet with a particular shape and with a field strength of 100,000 gauss. Data is shown for three electrical conductors: copper, aluminum, and sodium.

Abstract: The technical feasibility and economic potential of fast breeder power reactor systems cooled with boiling mercury have been investigated by American-Standard under the United States Atomic Energy Commission's New Reactor Concepts Evaluation Program.

In the decladding of stainless steel clad fuel elements with sulfuric acid (the Sulfex process), the loss of core material to the decladding solution is determined by the rate of reaction of the core material with the solution and the time of exposure if the core to the solution. Since very little was known about the effects of irradiation history on the rates at which core materials dissolve in sulfuric acid, the present study was undertaken in an effort to determine the magnitude of such effects. This report summarizes the results obtained to date. Further work is planned when materials of higher burn-up are available.

High heat flux electrical cartridge heaters were tested with direct air cooling under simulated ORR Loop conditions. The cartridges and the heater design were found to be satisfactory. A gas cooled of concentric pipe design utilizing air, water, and air-water mixtures as the coolant was also evaluated and found to be satisfactory.

A previous study has been completed on the buildup and decay of xenon poisoning in the PRTR by simulating the reactor as a single region. The results of this study indicated that a study using a more refined model of the reactor would be valuable.

This report was written to describe the instrument and test results obtained. It is understandably imperative that such alarming devices be incorporated in various areas of the plant to provide an alarm or warning for increasing dose rate from gauss radiation fields.

Abstract: A survey of the problem of reactor system contamination by radioactive material and methods that have been employed to remove the material was carried out. Following this survey, an investigation of chemical solutions was undertaken to find one which might be successfully employed in the decontamination of a stainless steel steam generator. From a preliminary screening, the most promising chemical method from the view point of minimum corrosion and maximum decontamination is a caustic permanganate treatment followed by and acid rinse.

Abstract: A decontamination procedure for a stainless steel steam generator similar to the APPR-1 using a fill-flush application of a caustic permanganate-citrate combination solution is recommended. The isolation of the steam generator is to be accomplished by means of specially designed plugs at the reactor vessel outlet and at the primary coolant pumps. Anticipated results, including corrosion rates and decontamination factors, are presented.

Abstract: "Fast neutron effects on a widely used x-ray film have been investigated. The neutron flux was provided by the (d, t) reaction of a Cockcroft-Walton accelerator. Integrated exposures to 10-10 n/cm-2 were given the film. It was found that perturbations on film that were pre-exposed to Co-60 gamma rays from 10 to 2000 r were negligible. Simultaneous exposure of neutrons plus gammas also indicated negligible effect on the film insofar as the gamma dose was concerned."

Report presenting an investigation of a pylon-mounted-store airplane configuration in the supersonic pressure tunnel at a Mach number of 1.61. Forces and moments of a complete wing-fuselage-store-pylon combination was measured for a variety of pylon-mounted store locations below the wing. Results regarding the effect of store position on the aerodynamic characteristics in pitch, effect of store position on the aerodynamic characteristics in sideslip, store fins and store tail cone, double-store installation, effect of pylon location, and relative contribution of store-pylon forces toward total force are provided.

Memorandum presenting an experimental investigation of the pressure-recovery performance of a fixed-geometry, two-cone, two-drag inlet at Mach number 2.95. Low drag was achieved by use of an internally cylindrical cowl with rapid flow turning that was within 4 degrees of the wedge angle for shock detachment. Results regarding the inlet performance and evaluation of inlet performance are provided.

Report presenting aerodynamic forces for an external-store installation on the Douglas D-558-II research airplane. Store-pylon, pylon-alone, and fin loads were determined during angle-of-attack and angle-of-sideslip maneuvers over a range of Mach numbers. Results regarding the side-force coefficients, normal-force coefficients, external-store-load parameters, external-store fin loads, and wing-panel aerodynamic loads are provided.

Report presenting preliminary flight surveys of noise inside fuselages and in the fuselage boundary layer, which were obtained in order to determine the magnitude of the noise and relative importance of engine noise and noise due to the boundary layer. Results indicated that the sound-pressure level continued to increase with airspeed to the highest airspeed obtained, although the rate of increase at supersonic speeds was less than at subsonic speeds. Testing occurred on the B-47A and D-558-II airplanes.

Report presenting the results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration without analysis over a range of Mach numbers. Data are presented for various combinations of the body, canard, wings, and vertical tail at 0 and 5 degrees of sideslip over a range of angles of attack and canard deflection angles.

The following report describes studies of thermodynamic equilibria of vanadium in aqueous systems as applied to the interpretation of the Colorado Plateau ore deposits.

This report summarizes experimental results obtained for the General Electric Company under terms of Design, Development and Research Contrast DDR-33. A discussion of the results, the manner in which they were obtained and their probable accuracy are included. Suggested improvements or modifications of properties of this nature be contemplated.

Report presenting an experimental investigation of a rectangular swept scoop inlet designed for and tested at a free-stream Mach number of 3.1 to determine the effect of inlet aspect ratio on the minimum inlet starting concentration ratio and the resulting inlet total-pressure recovery. Results regarding the determination of the starting contraction ratio, effect of inlet aspect ratio on the inlet starting characteristics, total-pressure recovery and mass-flow variations, and effects of inlet aspect ratio on the maximum total-pressure recovery are provided.

A brief investigation of a target-type thrust reverser on a single-engine fighter model has been conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.20 to 1.05. At Mach numbers of 0.80, 0.92, and 1.05, a hydrogen peroxide turbojet-engine simulator was operated with the thrust reverser extended. The angle of attack was varied from 0 degrees to 5 degrees at these Mach numbers.

Memorandum presenting a five-stage rocket-propelled model flown up to a Mach number of 10.9 and a corresponding free-stream Reynolds number of 6.57 x 10(exp 6) based on nose diameter. Temperatures were measured at 16 stations on the inside of a flat-faced cylinder made of copper. Results regarding the flight test, wall temperatures, heat-transfer data, measurement repeatibility and effects of angle of attack, comparison of measured and theoretical stagnation-point heating rates, and measured and theoretical heating rates over the front and side of the nose are provided.

Report presenting pressures measured during a free-flight test at zero angle of attack over a rocket model with a modified Von Karman nose in combination with a cylindrical center section and a 10 degree half-angle flare.

Report on an investigation to determine the erect and inverted spin and recovery characteristics of a model of the North American FJ-4 airplane. The testing found that either a flat-type of steep-type spin may be obtained when the airplane is spinning erect. The optimum recovery technique from inverted spins was full rudder reversal with simultaneous movement of the ailerons to full with the stick maintained full forward.

"The degree of cleanliness is defined, and the methods and materials to be used are outlined for carbon and low alloy steels, 300 and 400 series ferritic and austenitic stainless steels, special Ni-Cr base heat-resistant hard-facing and high-temperature brazing alloys, and some non-ferrous materials."

Memorandum presenting the effect of free-stream Reynolds number, engine installation, and model scale on inlet stability limits and on the amplitude and frequency of buzz. The data were taken at a free-stream Mach number of 2.0 and angles of attack from 0 to 6 degrees. Results regarding free-stream Reynolds number effect, model scale, and effect of engine on stability are provided.

Report presenting the effect of free-stream Reynolds number, engine installation, and model scale on inlet stability limits and on the amplitude and frequency of buzz. The data was obtained at mach number 2.0 and a range of angles of attack. Results regarding the free-stream Reynolds number effect, model scale, and effect of engine on stability are provided.