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100 Areas weekly report, February 24, 1955
No Description Available.
215 MWD/Ton batch size limits and control in the Bismuth Phosphate Plant
No Description Available.
The absorption, distribution, and excretion of tritium in men and animals
A series of experiments on exposure of man and rats to tritium gas (HT) or tritiated water (HTO) are reported. In one human experiment 3 millicuries of HTO was administered in 200 milliliters of water by ingestion. Absorption into the blood stream was linear with time and complete in about 45 minutes. Body water turnover was measured over a period of six days by weighing all food and fluid intake and all excretory output. For four days water turnover was kept near normal (2.7 liters per day). During the last two days water turnover was increased to 12.8 liters per day. Tritium excretion rates was determined on eight other human subjects in which water turnover in which measured less precisely. The biological half-life of HTO in nine human subjects varied from 9 to 14 days on ad libitum and was reduced to 2 1/2 days in one subject on high water intake. The tritium activity in sweat, expired water vapor, septum and urine was found to be essentially the same as that in water from the blood. Rats were continually exposed to various concentrations of tritium in inspired air (0.000001 to 0.03 microcuries per ml) for periods up to 145 hours. Inhaled tritium appeared in the animal as HTO apparently being converted thus in the body.
Adams disassembly procedure for Bldg. 10, Nevada Test Site
The disassembly of the `Adams` primary was scheduled for April 28, 29, and 30, 1959. The method of disassembly is provided as a procedure to be accomplished in order and the time and initials of the person accomplishing each step recorded.
Addendum to HW-34882: Technical appraisal of Redox ruthenium problems and their resolution
In the light of Redox Plant performance since the start-up on 2-3-55, coupled with a review of the technological factors involved in the current flowsheet, a departure from the process program outlined in HW-34882 is herewith presented as an addendum to that document which will also serve to detail the corresponding items in the latest Redox Test Program, HW-35069. The purposes of this document are to: (1) Discuss the need for modifications of the program given in HW-34882, and (2) Present the details of the proposed revisions.
Additional results of an investigation at transonic speeds to determine the effects of a heated propulsive jet on the drag characteristics of a series of related afterbodies
From Introduction: "Presented in this report are the basic data obtained from investigation. The data are presented with limited analysis in order to expedite their availability to those concerned with jet-exit-afterbody design."
Aerodynamic Characteristics of a 45 Degree Swept Wing Fighter Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53
Report discussing tests to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane and to determine the loads on attached stores and detached missiles. An investigation into aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications of aerodynamic characteristics was also carried out at various Mach numbers. Results are presented, but caution is provided in regards to extrapolating results from the model onto a full-scale aircraft.
Aerodynamic Characteristics of a 45 Degree Swept-Wing Fighter-Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53
Memorandum presenting an investigation in the Unitary Plan wind tunnel to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane, and to determine the loads on attached stores and detached missiles in the presence of the model. Results also included a determination of aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications on model aerodynamic characteristics. The results are presented with minimum analysis.
Aerodynamic characteristics of a canard and an outboard-tail airplane model at a Mach number of 2.01
From Introduction: "In order to obtain some insight into the relative merits of canard and outboard-tail control systems at supersonic speeds, a preliminary investigation of a generalized canard and outboard-tail model has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 and the results are presented herein."
Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic bump method
From Introduction: "This paper presents the results of the investigation of the wing-alone and wing-fuselage configurations employing a wing with the quarter-chord line swept back 60^o, aspect ratio 2, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the free stream."
Aerodynamic characteristics of several jet-spoiler controls on a 45 degree sweptback wing at Mach numbers of 1.61 and 2.01
Report presenting an investigation in the supersonic pressure tunnel at two Mach numbers to determine the aerodynamic characteristics of several jet-spoiler controls on a wing having a 45 degree sweepback of the quarter-chord line, an aspect ratio of 3.5, a taper ratio of 0.3, and an NACA 65A005 airfoil section. Testing indicated that the jet-spoiler effectiveness increased with increasing angle of attack and correlated well with the momentum of jet flow.
The Aerodynamic Characteristics of Two Series of Lifting Bodies at Mach Number 6.86
From Introduction: "This paper presents the results of an investigation conducted in the Langley 11-inch hypersonic tunnel to evaluate methods of increasing maximum lift-drag ratio."
Aerodynamic Loads on an External Store Adjacent to a 60 Degree Delta Wing at Mach Numbers From 0.75 to 1.96
Report presenting an investigation to determine separately the aerodynamic characteristics of a Douglas Aircraft Company store and a semispan delta-wing-fuselage configuration in the presence of one another. The store was located at the 50-percent-semispan station with the store nose both ahead of and behind the wing leading edge for two longitudinal and three vertical positions.
Amplifier Design for Proportional Ionization Chambers
This paper presents the requirements of a nuclear amplifier of short resolving time, designed to accept pulses of widely varying amplitudes. Data are given which show that a proportional ionization chamber loaded with a 1,000-ohm resistor develops pulses of 0.5 microsecond duration and several volts amplitude. Results indicate that seven basic requirements are imposed on the amplifier when counting soft beta and gamma radiation in the presence of alpha particles, without absorbers. It should, (1) have a fast recovery time, (2) have a relatively good low frequency response, (3) accept pulses of widely varying heights without developing spurious pulsed, (4) have a limiting output stage, (5) preserve the inherently short rise time of the chamber, (6) minimize pulse integration, and (7) have sufficient gain to detect the weak pulses well below the chamber voltage at which continuous discharge takes place. The results obtained with an amplifier which meets these requirements is described. A formula is derived which indicates that redesign of the proportional ionization chamber might eliminate the need for an amplifier. This may be possible if the radioactive particles are collimated parallel to the collecting electrode.
An analog study of the relative importance of various factors affecting roll coupling
From Introduction: "In this study wide variations in many of the pertinent aerodynamic were investigated at subsonic and supersonic speeds. The effects of large changes in principal axis inclination and mass distribution are also included. The primary purpose of this paper is to summarize the information obtained from the analog calculations and to compare the results with the trends predicted from a slightly modified version of reference 2."
Analysis of a Nuclear Incident in a Redox Dissolver
Since the start of E-metal processing in December, 1958, critical mass control in the Redox dissolvers has been provided by a combination of administrative controls, revised dissolver charging procedures, and new dissolving processes and operation control procedures. These were all based on a maximum allowable charge of E-Metal to the dissolvers which was equivalent to 45 percent of the minimum critical mass.
Analysis of Fluorine Addition to the Vanguard First Stage
Memorandum presenting an analysis of the effect of adding fluorine to the Vanguard first-stage oxidant. An increase in specific impulse of 5.74 percent may be obtained with 30 percent fluorine. Charts are provided regarding the vehicle performance increases for a zero-drag vertical trajectory.
Analysis of fluorine addition to the vanguard first stage
From Introduction: "This report presents data pertinent to the problem of boosting rocket performance by adding up to 30 percent liquid fluorine to the liquid oxygen of an existing oxygen-hydrocarbon rocket engine."
Analysis of the effects of wing interference on the tail contributions to the rolling derivatives
From Introduction: "This report presents calculations of the angularity of the air stream with respect to the vertical tail for a rolling airplane, the interference effects of the wing being taken into account. A discussion of the factors which enter into the calculations is given and equations for applying the side-wash results to the determination of the tail contributions to the rolling-stability derivatives are included. The results are compared with some available experimental data."
Analytical and Autoradiographic Methods for Polonium 210
No Description Available.
ANP Chemistry Section Progress Report for February and March, 1956
This report addresses the progress report of ANP chemistry for February and March 1956.
Application of supersonic vortex-flow theory to the design of supersonic impulse compressor- or turbine-blade sections
From Introduction: "The purpose of this paper is to present an analytical method for the design of two-dimensional related selection of a blade for particular rotor conditions may be made quickly and easily and its performance deduced from tests of representative sections in cascade."
APPR Meeting Held at Oak Ridge National Laboratory on April 3, 4, and 5, 1956
This report talks about APPR Meeting Held at Oak Ridge National Laboratory on April 3, 4, and 5.
Axial-Slot Air Admission for Controlling Performance of a One-Quarter-Annual Turbojet Combustor and Comparison With Complete Engine
"An investigation of a single-annulus turbojet combustor with slot-type air admission was conducted to demonstrate the application of certain design principles to the control of outlet-gas temperature distributions. Comparisons of performance of a one-quarter-annulus combustor (duct-type installation) and a full-annulus combustor (obtained in a full-scale turbojet engine) are presented to indicate the applicability of results obtained from combustion studies conducted in duct-type installations. A reasonable correlation existed between the performance of the one-quarter-annulus and full-annulus combustors except for temperature distribution" (p. 1).
Behavior of Some Materials and Shapes in Supersonic Free Jets at Stagnation Temperatures Up to 4,210 Degrees F, and Descriptions of the Jets
Report presenting testing of a number of materials and shapes in two supersonic free jets at stagnation temperatures of up to 4,210 degrees Fahrenheit. Some testing was conducted in a supersonic chemical jet and some was conducted in a ceramic-heated air jet. Materials tested included aluminum alloy, copper, Inconel, magnesium, mild steel, molybdenum, stainless steel, titanium, alumina, zirconia, graphite, bakelite, and nylon.
Bevatron Operation and Development. V
A considerable number of major improvements have been made in experimental facilities this quarter. These include four targets, three air locks, a deep well, and several thin windows for beam extraction in the target area. Simultaneous operation of up to five experiments has been achieved with a relay-controlled automatic operations selector. A beam-amplitude regulating device has been used to set the beam level on any pulse to within a few percent. The range of this equipment is 1000:1. Experimentation on the accelerator this quarter included measurements of start frequency and frequency-tracking jitter, beam-versus-radial-aperture measurements, empirical study of gas scattering effects, and preliminary testing of an automatic beam-controlled frequency-tracking system. High-energy physics experiments have been performed by ten groups within this laboratory. These groups are using counter techniques for the elastic proton-proton scattering, K-particle half-life determination, and {pi}{sup -}-meson cross-section measurements. A high-pressure hydrogen diffusion chamber is being used to study multiple production of {pi}{sup -} mesons. A strong-focusing pair spectrometer has been used to produce beams of K particles. Emulsion exposures have been made to determine the masses and mean lifetimes of K mesons. The interactions and modes of decay of K{sup {+-}} mesons at rest, as well as in flight, have been studied in emulsions.
BEVATRON OPERATION AND DEVELOPMENT. XIV. Period covered May, June, July 1957
The first half of this quarter was in part a continuation of the shutdown of the last period and in part a shutdown recovery period. The second half of the quarter was devoted to high-energy physics and chemistry research and to the extension and improvement in techniques of producing secondary-particle beams. The principal physics research efforts were a continuation of the investigations of interactions of negative particles in hydrogen using the 10- inch liquid hydrogen bubble chamber; counter sludies of the pi /sup 0/ modes of heavy-meson and hyperon decay; and a series of twenty-one nuclear emulsion exposures to K-meson beams. During this period twenty emulsion stacks were exposed for thirteen external groups. Thirteen target bombardments were made for the chemistry group. (For preceding period see UCRJ-8021.) (M. H.R.)
Blow-Out Velocities of Solutions of Hydrocarbons and Boron Hydride - Hydrocarbon Reaction Products in a 1 7/8-Inch-Diameter Combustor
Combustion blow-out velocities were determined for JP-4 solutions containing: (1) 10 % ethylene - decaborane reaction product, (2) 10% and 20% acetylene - diborane reaction product, and (3) 5.5%, 15.7%, and 30.7% methylacetylene - diborane reaction product. These were compared with blow-out velocities for JP-4, propylene oxide, and neohexane and previously reported data for JP-4 solutions of pentaborane. For those reaction products investigated, the blow-out velocities at a fixed equivalence ratio were higher for those materials containing higher boron concentrations; that is, blow-out velocity increased in the following order: (1) methylacetylene - diborane, (2) acetylene - diborane, and (3) ethylene - decaborane reaction products.
A Brief Investigation of the Effect of Waves on the Take-Off Resistance of a Seaplane
Report presenting testing to determine the resistance of a model of a seaplane with a length-beam ratio of 15 and a wing loading of 120 pounds per square foot was determined in smooth water and three wave heights under various conditions of load, speed, elevator setting, angle of dead rise, and center-of-gravity position.
Buffeting of a vertical tail on an inclined body at supersonic Mach numbers
Report presenting time histories of rolling and yawing moments on inclined bodies of revolution with vertical-tail surfaces at several Mach numbers and Reynolds numbers. Three ogival-nose bodies with three overall fineness ratios and a conical-nosed body with a fineness ratio of 12.0 were tested. Results regarding the visual-flow studies, rolling- and yawing-moment measurements, and pressure measurements are provided.
Bulk ThO2, a Reactor Material
Thorium, a fertile material, is of interest to the Reactor Program in the production of U233. Thorium can be extracted and processed to a very pure bulk metal for fabrication into solid fertile elements. There are advantages, technical and economic, for using fabricated bulk thorium dioxide rather than the metal in some applications. It is the purpose of this paper to point out these advantages and to present briefly the technology related to fabrication, radiation damage and chemical processing of ThO2.
A button source of plasma
From abstract: " This report describes the construction of a plasma source that projects deuterium and titanium ions and eletrons at speeds up to 2 x 10^7 cm/sec."
C and D machines functional and life tests: Interim report No. 2, Test project No. 29
This test project is being carried on for the purpose of testing certain machines which are designed to charge and discharge reactor units with process metal while the unit is in operation. Satisfactory charging of process pieces while the reactor now required for charging operations. These presently required shutdowns are costly in terms of production time, and may cause undesirable thermal stresses in the unit as it changes power level. If charging can be accomplished during operation, reactor shutdowns would only be necessary for maintenance or emergency purposes. During the testing of these metal handling machines, problems have arisen involving the behavior of the process pieces as they are charged. Because these problems directly affect the charging operations, they are being closely investigated also. the machines covered by this report are designated as pressurized machines since they contain the same water pressure as the end of the process tube on ;which they are located. In most of the test work covered by this report, the full scale pressurized charging machine was replaced with a small charging cylinder. The charging operation was simplified by this change.
C-Reactor I and E loading instability limits
The pilot charging of I & E fuel elements has been implemented at C-Reactor under Production Test IP-19-A. It was necessary to provide adequate tube protection against flow interruption by establishing proper trip setting on the Panellit pressure gauges. the administration of these Panellit trip settings is done by trip-before- boiling tube outlet temperature limits, which are similar in principle to the current instability limits. Trip-before-boiling limits for C-Reactor I & E fuel elements loadings are presented in this document.
Calculation of Average Flux in Moderator of Water Lattices by Means of a Relaxation Method
The following report concerns the application of a relaxation mesh method for the determination of the average flux within the moderator of a light water moderated, 1.027 per cent U-235, hexagonal lattice with a volume ratio (V_H2O + V_Al)/V_Uranium of 4:1. It was hoped that the calculation would enable one to determine any differences in flux which might result from the fact that the unit cell is a hexagon instead of a cylinder. Because we were primarily interested in the effect due to geometry we applied the same theory, diffusion theory, to the hexagon by means of the mesh method and to the equivalent cylinder.
Calculation of Fields on Plasma Ions by Collective Coordinates
No Description Available.
Calculation of the Lateral Stability of a Directly Coupled Tandem-Towed Fighter Airplane and Correlation with Experimental Data
"A theoretical method is presented for predicting the dynamic lateral stability characteristics of an airplane towed in tandem by a much larger airplane. Values of period and time to damp to one-half amplitude and rolling motions calculated by an analog computer have been correlated with results of two experimental investigations conducted in the Langley free-flight tunnel which were part of a U.S. Air Force program (Project FICON) to develop a satisfactory arrangement by which a bomber could tow a parasite fighter. In general, the theoretical results agree with the experimental results" (p. 1).
Calculations of Laminar Heat Transfer Around Cylinders of Arbitrary Cross Section and Transpiration-Cooled Walls with Application to Turbine Blade Cooling
An approximate method for development of flow and thermal boundary layers in laminar regime on cylinders with arbitrary cross section and transpiration-cooled walls is obtained by use of Karman's integrated momentum equation and an analogous heat-flow equation. Incompressible flow with constant property values throughout boundary layer is assumed. Shape parameters for approximated velocity and temperature profiles and functions necessary for solution of boundary-layer equations are presented as charts, reducing calculations to a minimum. The method is applied to determine local heat-transfer coefficients and surface temperature-cooled turbine blades for a given flow rate. Coolant flow distributions necessary for maintaining uniform blade temperatures are also determined.
Carbon Dioxide Fixation by Microorganisms
Resting cells of eleven microorganisms were exposed to radioactive carbon dioxide for 40 minutes. The radioactive compounds formed during this time were separated and identified by paper chromatography. Resting cells of Lactobacillus casei fixed no carbon dioxide and growing cells fixed carbon dioxide primarily in malic and aspartic acids. All of the radioactive compounds formed could have become radioactive by reversal of known decarboxylation reactions.
Chemical and physical properties vs degree of concentration of uranyl nitrate-nitric acid process streams of metal conversion plant
Uranium is recovered as an aqueous solution of uranyl nitrate and nitric acid in both the tributyl phosphate metal recovery process and the Redox separation process. The streams are designated as RCU and IIIEU in the respective processes. For metal recovery these streams are combined. The purpose of the nitric removal operation is to minimize equipment corrosion and to restrict contamination of the final uranium oxide with corrosion products which might be formed in the elevated temperature reactor employed for the decomposition of uranyl nitrate to the oxide. Because of the large quantities of uranium being processed it is desirable to conduct the concentration of the combined RCU and IIIEU streams in a continuous type process to reduce the operating and fixed charges. Determination of the physical and chemical properties of the dilute aqueous uranyl nitrate -- nitric acid system, as it progresses toward an essentially nitric acid free concentrated state, is necessary to define the optimum operating conditions.
CHEMICAL PROPERTIES OF BERKELIUM
The recent production by Thompson, Ghiorso, and Seaborg of a radioactive isotope of berkelium (atomic number 97) makes it possible to investigate the chemical properties of this transuranium element by means of the tracer technique. This isotope has been prepared through the bombardment of Am{sup 241} with about 35 Mev helium ions in the 60-inch cyclotron of the Crocker Laboratory and is believed to have the mass number 243, or possibly 244. This Bk{sup 243} has a half-life of 4.6 hours and decays by electron capture with about 0.1% branching decay by alpha-particle emission. In the present tracer chemical experiments, the radiations accompanying the electron capture process were used as a means of detection and were counted in two ways. Where the sample deposits on the platinum plates were essentially weightless, as was the case following the evaporation and ignition of the elutriant solutions in the column adsorption experiments, a high efficiency was obtained by using a windowloess proportional counter to count the Auger electrons. The thicker samples from the precipitation experiments in which carrier materials were used were counted close to the thin window (3 mg/cm{sup 2} mica) of a bell type Geiger counter filled with 10 cm. xenon to enhance the efficiency for counting the x-rays. An aluminum absorber of thickness about 20 mg/cm{sup 2} was used between the sample and counter window to reduce errors due to variable absorption of soft components caused by small differences in sample thickness.
Chordwise pressure distribution at high subsonic speeds near midsemispan of a tapered 35 degree sweptback wing of aspect ratio 4 having NACA 65A006 airfoil sections and equipped with various spoiler ailerons
From Summary: "An investigation was made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.60 to 0.93 to determine the effects on the chordwise pressure distributions of projecting various spoiler-type ailerons on a swept wing. The semispan 35 degree sweptback wing had an NACA 65A006 airfoil section, an aspect ratio of 4, and a taper ratio of 0.6. The results of the investigation are presented as curves of chordwise pressure distributions near the midspan of the spoilers (0.46-wing-semispan station)."
COMMERICAL UTILIZATION OF FLORIDA LEACHED ZONE ORE
No Description Available.
COMPARATIVE ANALYSIS OF ANL HIGH PURITY URANIUM
No Description Available.
Comparative Analysis of ANL High Purity Uranium
In the course of the development at Argonne of high purity uranium metal in ingot form, some questions arose as to the validity of the chemical analyses of some of the impurities (particularly those for carbon, boron, and silicon), with one analytical laboratory reporting concentrations in some instances of an order of magnitude greater than another laboratory. Since the low concentrations of impurities in this material involved, in some cases, the development of modified analytical procedures and standards, it was decided to check these discrepancies by having identically prepared samples analyzed by several AEC and associated laboratories. This report is a compilation of the results obtained.
A comparative analysis of the performance of long-range hypervelocity vehicles
From Summary: "Long-range hypervelocity vehicles are studied in terms of their motion in powered flight, and their motion and aerodynamic heating in unpowered flight. Powered flight is analyzed for an idealized propulsion system which rather closely approaches present-day rocket motors. Unpowered flight is characterized by a return to earth along a ballistic, skip, or glide trajectory. Only those trajectories are treated which yield the maximum range for a given velocity at the end of powered flight. Aerodynamic heating is treated in a manner similar to that employed previously by the senior authors is studying ballistic missiles (NACA RM A53D28), with the exception that radiant as well as convective heat transfer is considered in connection with glide and skip vehicles."
Comparison of effect of a turbojet engine and three cold-flow configurations on the stability of a full-scale supersonicle inlet
Increasing the volume and length of the duct behind the inlet affected the inlet stability at Mach 2.0 and zero angle of attack. Close approximation of the inlet stability limit of the J34 engine-inlet configuration was obtained by a cold-pipe configuration having a length and volume approaching that measured to the engine turbine. Variation of these parameters had a small effect on the minimum subcritical stable mass flow below a cowl-lip-position parameter of 44 degrees and appeared to have a negligible effect on the inlet pressure-recovery - mass-flow curve. Initial buzz frequency and minimum cowl-lip-position parameter for complete buzz-free operation varied with configuration.
Comparison of effects of ailerons and combinations of spoiler-slot-deflector arrangements on spin recovery of sweptback-wing model having mass distributed along the fuselage
Report presenting an investigation in the free-spinning tunnel to determine the effect of lateral-control systems using various combinations of spoilers, slots, and deflectors as compared with ailerons on the spin-recovery characteristics of a model of a 35 degree swept-wing fighter loaded heavily along the fuselage. Testing indicated that the ailerons were favorable for recovery when they were deflected full with the spin. Results regarding the effect of ailerons and two spoiler-slot-deflector configurations are provided.
A Comparison of the Effects of Radiant Thermal Energy on Bare, Blackened and Whitened Pig Skin
No Description Available.
Comparison of the Minimum Drag of Two Versions of a Modified Delta-Wing Fighter as Obtained From Flight Tests of Rocket-Boosted Models and Equivalent Bodies Between Mach Numbers of 0.80 and 1.64
Report presenting an investigation to determine the reduction in minimum drag that could be obtained at supersonic speeds by redesigning the fuselage and reducing the wing and tail thickness of a modified delta-wing fighter-type airplane. Results regarding the mass-flow ratio, total-pressure recovery, and drag are provided.
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