Results of tracer studies suggest that, in tributyl phosphate extraction processes designed to recover and purify fissionable material, minimum ruthenium extraction should be obtained from feeds at least 2 M in nitric acid or at least 1 M acid-deficient. Ruthenium decontamination was decreased by preheating the feed and increased by pretreatment with reducing agents. A pretreatment using 0.06 M ferrous ion and 0.5 M urea with 1 hr simmering at 85°C should increase ruthenium decontamination about 10-fold in the 25 process. If other process considerations dictate the use of a low-acid feed, decontamination from ruthenium may be improved by using 3 M nitric acid as the scrubbing solution. Apparently, the scrubbing process is quite time-dependent; a solvent holdup time of about 15 min may be needed in the scrub section for maximum decontamination.

The study of the flame photometric method for determining the concentration of tributylphosphate (TBP) in a hydrocarbon diluent was undertaken because it showed promise of being economically competitive and subject to fewer interferences than the existing methods. The determination of TBP in the hydrocarbon solutions throughout the range 0.01 to 80 per cent TBP may be performed using the flame photometer. The principal conclusions resulting from the study found a that there was higher precision in the one to two percent TBP rang than the 45 per cent TBP level due to error in reproducing narrow slit width in the higher range, 2) nitric acid, uranyl nitrate, and thorium nitrate all interfere if present but can be eliminated by contacting the solution with water or sodium carbonate solution. 3) a single determination may be made in 15 minutes, multiple determinations can be made at a rate of one to two minutes per determination, and 4) a modification of an existing method makes possible the application of this method to the determination of TBP dissolved in aqueous samples. A relative precision of plus of minus five per cent (95 per cent confidence level) is obtained.

"General Chemistry investigations reported herein includes: (1) the Organic Coolant-Moderator Program, (2) investigations on zirconium hydride, and (3) analytical chemistry."

None

The ability of the atmosphere to disperse and diffuse smoke and gases varies widely with weather conditions. The rate of diffusion is governed mainly by the degree of atmospheric turbulence present. The latter is in itself an extremely complex air motion which acts as the mixing agent in diffusion. This turbulence, which is so fundamental in the diffusion process, depends on such quantities as wind speed, rate of change of wind speed or wind direction with height, and rate of change of air temperature with height. Since these conditions differ widely from hour to hour and day to day, there is a corresponding variation in the diffusing capacity of the atmosphere. The rate of change of temperature with height and the wind speed have the most pronounced effect on the physical appearance of smoke plumes, which in itself provides a clue to the diffusing power of the atmosphere during various atmospheric conditions. The purpose of this note is to present, in semi-technical terms, some of the basic physical concepts related to the behavior of gaseous stack effluents after release into the atmosphere, and to describe certain visible geometrical features of effluent plumes that are directly related to the physical state …

"Iodide-processed thorium foils were irradiated with 9-Mev protons at temperatures below -140 degrees C. the recover of electrical resistance upon annealing was studied in the range 0 degrees to 75 degrees where tempering curves showed rapid changes taking place. Determinations of the activation energy associated with this process were made and the mean value obtained was 1.22 ev. Correlations of this result have been made with those found previously for copper. From these comparisons, a tentative assignment of the motion of interstitial atoms in thorium has been made for this process. In addition, some evidence has been found which illustrates the corrosive action that water has on thorium at temperaturs as low as 0 degrees C."

During 1954 interest was maintained in the problem of cooling-by-boiling in a geometry similar to that of a Hanford pile. Operation of present piles and the design of future piles will benefit from basic knowledge of boiling flow. This report presents a brief compilation of data for boiling flow taken during the year on the full scale and short process tube mock-ups in 189-D. Data reported herein consists of burnout conditions for a uniform heat flux in a `C` annulus and a standard annulus and data taken with full cosine and part cosine power distribution. The data for non-uniform power distribution is meager and was taken primarily to obtain an indication of the validity of extrapolating data with uniform heat flux to conditions of non-uniform flux distribution.

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Report presenting an investigation in the pressure wind tunnel to determine the effect of an operating propeller on the aerodynamic characteristics of a model of a vertical-rising airplane with an unswept wing with an aspect ratio of 3. Lift, longitudinal force, pitch, and roll characteristics, with and without power, are presented for the complete model and various combinations of model components.

None

Report presenting an investigation to determine the longitudinal stability, lift, and drag characteristics of a rocket-powered model of a canard configuration with a 45 degree sweptback wing of aspect ratio 6.0, taper ratio of 0.6, and NACA 65A009 airfoil section. The variations with Mach number of lift, drag, and longitudinal stability were compared with a tailless and a conventional model with the same wing.

The problem of a blast wave propagating through an inhomogeneous atmosphere is set up for computation by the CRC LORA. Previous treatments of this problem have used various simplifying assumptions such as that of purely radial flow. Since, however, pressure gradients in this situation will not in general be in the direction of rays from the blast center, non-radial flow will exist, and there is reason to believe that for large distances this effect will play a prominent role. Therefore, a program was set up for the numerical calculation (on the CRCLORA) of the propagation of a blast wave from a ground burse with altitude effects and possible tangential flow taken into account. With initial conditions known, the program is designed to give the pressure, density, radial and tangential flow velocities after successive time intervals at 16 equally spaced positions on each of 16 straight rays emanating from the point of burst. These positions are shifted with time to keep up with the shock front. Rehmeyer's and Van Neumann's method is used to handle the discontinuous shock front. In this method an artificial viscosity term is introduced in the the equations of motion in order to smooth out the discontinuity, …

"For each of two inlet-boundary-layer thicknesses, performance and boundary-layer characteristics have been determined for a 12 degree, 10-inch-inlet-diameter diffuser, a 12 degree, 21-inch-inlet-diameter diffuser, and a 23 degree, 21-inch-inlet-diameter diffuser. The investigation covered an inlet Mach number range from about 0.10 to coking. The corresponding inlet Reynolds number, based on inlet diameter, varied from about 0.5 x 10(6) to 7.5 x 10(6)" (p. 1013).

Abstract: The design and testing of experimental equipment for remotely joining stainless steel tubing by heliarc welding is described. This apparatus consists of a modified heliarc welding torch which is hydraulically controlled to maintain constant arc voltage. A suitable arc voltage sensing and control amplifier circuit was developed for this application.

Letter opinion issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, John Ben Shepperd, regarding a legal question submitted for clarification; Do railroad refunding bonds under submitted facts constitute a novation? Does subparagraph 7 of Sec. 20(a) Chapter 1 of Title 49 of U.S.C. supersede Art. 6257 V.C.S. in any part?

Report presenting an investigation of the effects of leading-edge camber without twist on an aspect-ratio-3 delta wing of thickness ratio 3, a body with an ogive nose, and a cylindrical afterbody. Results regarding the base pressures and body characteristics and wing-body combinations are provided.

Report presenting experimental results showing the static longitudinal-stability and -control characteristics of a model of a fighter airplane with a low-aspect-ratio unswept wing and an all-movable horizontal tail. The investigation was made over a Mach number range from 0.60 to 0.90 and from 1.35 to 1.90. Results regarding the pitching moment at zero lift, longitudinal stability, and longitudinal control are provided.

A method is developed for the calculation of the effect of Doppler broadening of the absorption of the neutrons by a resonance absorber. Numerical values are given for the correction factors required in the interpretation of transmission experiments and self-indication experiments and for the self-shielding factors for slabs, spheres, cylinders, and homogeneous mixtures. (auth)

Report presenting an investigation of the effect of reducing the static stability by a practical center-of-gravity shift in swept-wing airplanes of low aspect ratio with no horizontal tail. Results regarding relocating the center of gravity, the effect of lift due to elevator deflection, the effect of increased total elevator effectiveness, and the effect of response characteristics over long time periods are provided.

None

Report presenting two-dimensional aerodynamic lift and moment flutter derivatives for moderate and high angles of attack for several airfoil profiles varying in thickness and thickness distribution. The results indicate that the variables angle of attack, airfoil profile, reduced frequency, and Mach number all have significant interdependent effects.

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Pressure recovery in adjustable supersonic inlet combined with J34 turbojet engine up to Mach 2.0.

Report presenting an investigation of an annular nose inlet equipped with a remotely controlled translating spike and variable bypass in the supersonic wind tunnel. The inlet performance was explored with the airflow controlled by an operating J34 engine and with the engine simulated by a choked plug. Results regarding the performance of the inlet, corrective action that should be applied to avoid pulsing, performance of the subsonic portion of the diffuser, supersonic performance, radial-flow profiles, and other flow profiles are provided.