The purpose of the test used to make this report was to determine if anodizing could become a part of the canning operation prior to autoclaving, other factors permitting, or if it must follow autoclaving.

This bibliography contains 145 references on the technology and apparatus used in the purification of argon, helium and xenon, and on the analysis for water, carbon monoxide, hydrogen, nitrogen, and oxygen, in the purification process. The references are arranged in four classifications: general, argon, helium, and xenon. Within each classification, the references are arranged in chronological order.

Partial abstract: "The investigation of the high temperature and pressure dissociation of water under irradiation was undertaken by the Power Pile Division of Oak Ridge National Laboratory in an effort to determine the degree of importance of the phenomenon with respect to the design of a high temperature water-cooled power reactor. Theory and past experimentation indicate that net steady-state dissociation is determined by the rates of the dissociation and recombination reactions under the imposed conditions, the dissociation rate being essentially a function of flux and the recombination rate essentially a function of temperature" (p. 3).

"Panels of aluminum alloy sheets, framed by side and end stiffeners, were subjected to combined loading by means of offset knife edges applying loads to top and bottom end plates with reacting forces against the end plates supplied by laterally acting rollers. The test specimens were 17S-T aluminum alloy shoots 0.040 inch thick in panels of 10-inch width and three different lengths (approximately 10, 26, and 30 inch). Data were obtained for the bowing of transverse and longitudinal ribs of rectangular cross section and varying depths mounted on one side of the sheet only, for several ratios of compression to shear loads" (p. 1).

Report presenting the lift of wing-body combinations at supersonic speeds as obtained by means of an approximate linearized-theory analysis involving an assumption concerning the geometry of the body. A comparison with several groups of data is provided to show the accuracy of the method.

Report presenting comparisons of low-lift drag measurements on eight airplane configurations at a range of Mach numbers by various techniques. Data was obtained from wind tunnel testing, rocket propelled model tests, and airplane flight tests. The agreement of data is generally good and no consistent Reynolds number effects are observed.

Combined compressor coolant injection and afterburning for turbojet engine thrust augmentation.

Report presenting an investigation of the performance of a single can-type combustor designed for a turbojet engine equipped with an 11-stage axial-flow compressor and a single-stage turbine. The investigation was conducted to determine the altitude operational limits of the engine for two fuels, combustion efficiencies at various simulated conditions of altitude and engine speed, combustor-outlet temperature distribution for several altitudes at constant engine speed, and combustor total-pressure drop.

Memorandum presenting an investigation at Mach numbers of 1.41, 1.62, and 1.96 to determine the effects of airfoil section and wing plan form on the pressures acting on the base of blunt-trailing-edge wings operating through an angle-of-attack range. The investigation included two groups of untapered wings of aspect ratio 2.7, with one group being unswept and the other with 45 degrees of sweepback. Results regarding the effects of wing location and body size, spanwise variations of base pressures, variations of average base pressure coefficients with angle of attack and wing section, and effects of plan form are provided.

"A preliminary investigation has been made in order to determine the static and dynamic longitudinal stability characteristics and the force characteristics of a Grunberg hydrofoil system comprising a main lifting hydrofoil and planing-surface stabilizers. The tests showed that a rearward movement of the center of gravity decreased the static and dynamic stability but increased the lift-drag ratio. In smooth water, adequate static stability was observed for all conditions tested" (p. 1).

Report presenting an investigation to determine the control hinge moments and effectiveness at transonic speeds of a delta wing equipped with a constant-chord flap-type control with and without an unshielded triangular horn balance in the 7- by 10-foot tunnel using the transonic-bump method. The data indicated that the horn balance control was consistently more effective in changing lift at all Mach numbers than was the plain control but there was no appreciable difference in pitching-moment effectiveness.

Report presenting hinge-moment data for a wing-body combination at Mach numbers of 1.46 and 1.99 and some lift and drag results for the lower Mach number. The model consisted of an aspect ratio 4, triangular, all-movable wing with an 8-percent-thick double-wedge section mounted on a pointed cylindrical body of fineness ratio 9-1/3. The results indicated that the wing has a relative effectiveness ranging from 63 to 98 percent.

Report presenting a discussion of some of the requirements and of the application of the augmented performance of compressor coolant injection and afterburning in a turbojet engine in a high-speed, high-altitude flight. Results regarding the experimental performance of a combined system and the application of augmented performance to high-speed flight are provided.

Report presenting an experimental vaporizing annular combustor that evolved from a high-performance annular combustor developed for vapor-fuel injection. The combustor consisted of a one-quarter sector of a single-annulus combustor designed to fit in a housing with an outside diameter of 25.5 inches, an inside diameter of 10.6 inches, and a combustor length of approximate 23 inches. Results regarding the performance of the Model 29I combustor, performance of Model 30, and performance of the best combustor configuration are provided.

Report presenting comparisons of low-lift drag measurements on eight airplane configurations at a range of Mach numbers using various techniques. Data was obtained from wind-tunnel testing, rocket-propelled model testing, and airplane flight testing. The majority of the data showed agreement and discrepancies were likely due to issues regarding surface condition, individual test setup and accuracy, and detail geometric differences between the airplanes and respective models.

Abstract: A summary of thermodynamic calculations for zirconium halides is given. Data indicates that the iodide is the most promising of the halides for arc dissociation and that good recoveries of zirconium should be obtainable provided dissociation is carried out at reduced pressure.

The following document analyzes the Automatic Isotope Mass Spectrometer that consists of a Laboratory Isotope Mass Spectrometer, covered by Union Carbide Nuclear Company Job Specification "JS-747", which has been modified to meet Union Carbide Nuclear Company Job Specification "JS-741", as well as the instrument's samples collected and analyzed.

"The experience at Oak Ridge National Laboratory in decontamination equipment and working areas from radioactivity has been summarized." The methods and reagents that were used for decontamination are discussed.

The indicated methods for determining the following constituents of Diban, which is an aqueous solution of dibasic aluminum nitrate, Al(OH)2NO3, were evaluated statistically: 1aluminum by gravimetric, volumetric, and spectrophotometric procedures, 2. basicity (hydroxyl value) by formation of an aluminum complex and titration of the free acid with standard alkali solution, 3. total nitrogen by the Kjeldahl method, 4. ammonia by the Kjeldahl method, and 5. nitrates by means of a cation-exchange resin and titration of the liberated acid with standard alkali solution. Recommendations are made regarding the preferred methods of determining the constituents in dibasic aluminum nitrate and regarding means of minimizing errors in these analyses.

At the request of the Hanford Operations Office of the Atomic Energy Commission, a criticality instrumentation meeting was held at Hanford on August 17 and 18, 1959. The purposes of the meeting were: (a) to review types of criticality control and/or alarm instrumentation at each site, their problems, shortcomings and potential obsolescence; (b) to discuss instrumentation in the area if approaching criticality; and (c) to consider for material balance purposes, the feasibility of devising instruments to detect the buildup of plutonium and enriched uranium bearing residues in process systems.

An analytical method for Cu-64 in reactor effluent has been studied based upon electrodeposition of the active copper with inert copper carrier. A two hour plating time was employed at a current density of 10 ma/sq cm and four volts across the cell. A stainless steel cathode plate was used. Carrier yields of greater than 80% were obtained with a standard deviation of the yield-corrected counting rate as low as 0.24%. Very little, if any contamination by other radioactive elements present was shown by decay curve studies. Self-absorption and self-scatter factors to correct the counting rate were obtained.

Summary: The High Power Density Project includes a comprehensive fuel development program which has the objective of developing and demonstrating the performance of a nuclear reactor core having a high power density, long fuel life, and low fabrication cost. The fuel program is made up of two principal tasks. Task 1A consists of irradiation tests in the VBWR of Type 304 stainless steel clad, UO2 pellet type fuel rods fabricated by current commercial processes. Task 1B consists of the investigation of lower cost fabrication processes and the irradiation testing of fuel elements fabricated by these processes. Both tasks include the investigation of the feasibility and use of thin-wall stainless steel cladding as a means of improving the neutron economy and fuel cycle costs of stainless steel clad fuel. Irradiation of the Task 1A fuel assemblies in the VBWR was initiated in September, 1960. Subsequently, Task 1B fuel assemblies were inserted in the VBWR as various fabrication processes and design concepts were investigated. Fuel cladding failures have occurred in fuel rods in both Task 1A and 1B. As of this date, cladding failures have occurred in twenty-two rods of approximately 700 fuel rods which have been irradiated. Twenty of the failures …

Report documenting experience gained by operating the spare PRTR Primary Process Pump. This includes descriptions of equipment used, testing procedures, and operating history.

Tests were made to determine the motor performance characteristics under flight conditions at propellant preignition temperatures of -25 degrees F, ambient temperature, and 130 degrees F. Results regarding the trajectories of the various test vehicles, time histories of velocity and Mach number, acceleration time histories, thrust curves, and maximum variation of total impulse are provided.