Theoretical investigation on the nature of ion exchange of acidified uranyl sulfate solutions with Dowex 21K, a strong base ion exchange resin.

Corrosion of anode assembly materials in fluorine generators is pronounced, therefore, selection of the proper materials for construction is important. Several metals and alloys have been tested for corrosion resistance when anodic in a fluorine test cell. In general, copper, copper alloys and magnesium alloys offer the best corrosion resistance.

The present study was undertaken for the purpose of determining the feasibility, establishing the required development program, and estimating the cost of a turbocirculator to provide the pumping power for a 1000-Mw(e) high-temperature gas-cooled reactor power plant as part of the TARGET program. This necessitated preliminary design of the turbocirculator in conjunction with the reactor power plant as well as the investigation of methods for the optimization of the turbocirculator and for its development. This study was carried out in sufficient detail to fix the methods required to resolve the problems that would be encountered during the course of a prototype program resulting in a turbocirculator for the TARGET power plant.

Report discussing high-speed cascade tests made of a blade section designed for conditions typical of the hub section of high-flow transonic rotors. The intent of the testing is to provide information on the effects of local surface Mach numbers on blade performance. The test results, effect of more forward location on peak surface velocities, effect of increase in pressure-rise coefficient, effect of Mach number and pressure rise on turning angle, and a comparison of variation in momentum-loss coefficient with surface pressure-rise coefficient are provided.

Report discussing testing on a scale model of the Convair XF2Y-1 airplane with solid-fuel rocket motors that simulate full-scale turbojet-engine characteristics at a height of 35,000 feet with full afterburning at Mach number 1.53. The model was found to have dynamic lateral instability, but these results were not likely to be found in a full-scale airplane. Information about the pitching moment, directional stability, lift-curve slope, and drag coefficients is provided.

Report presenting testing of two full-scale models of an inline, cruciform, canard missile configuration with a low-aspect-ratio wing equipped with flap-type controls to determine the missile's longitudinal aerodynamic characteristics. Stability derivatives and control and drag characteristics are provided.

Memorandum presenting a free-flight investigation to determine the lift, drag, static stability, and hinge-moment characteristics of a rocket-powered model of a rocket-powered model of a ballistic-missile configuration at supersonic speeds. The model consisted essentially of a body of fineness ratio 16.9 and a cruciform set of small 60 degree delta fins located approximately 1 body diameter from the base of the body. The model lift and pitching-moment coefficients were nonlinear with angle of attack.

The flame velocities of 37 pure hydrocarbons including normal and branched alkanes, alkenes, and alkynes; as well as benzene and cyclohexane, together with the experimental technique employed are presented. The normal alkanes have about the same flame velocity from ethane through heptane with methane being about 16 percent lower. Unsaturation increases the flame velocity in the order of alkanes, alkenes, and alkynes. Branching reduces the flame velocity.

Report presenting tests of two models of an inline, cruciform, canard missile configuration with a low-aspect-ratio wing equipped with flap-type controls to determine the missile's longitudinal aerodynamic characteristics. Stability derivatives and control and drag characteristics are presented for a range of Mach numbers.

Report presenting tests of a wing-body combination using the free-fall method, which was made up of a fineness-ratio-12 body with a 45 degree sweptback wing, an aspect ratio of 3.75, and an NACA 65-003 airfoil section in the direction perpendicular to the 50-percent-chord line. Results regarding the complete configuration, wing, body-tail combination, and component effects on total drag are provided.

Total-pressure deficiency for an annular cascade of 65-(12)10 blades was measured at three radial stations over a range of Reynolds numbers from 50,000 to 250,000 and at angles of attack of 15 degrees and 25 degrees. The variation of turning angle and shape of static pressure distribution at these stations is also shown.

The effects of one type of camber on the aerodynamic characteristics of rectangular wings at high subsonic and transonic speeds have been studied by applying the transonic similarity rules to the correlation of experimental data for a series of 18 cambered wings having NACA 63A2XX and 63A4XX sections, aspect ratios from 1 to 4, and thicknesses from 4 to 8 percent. The data were obtained by use of a transonic bump over a Mach number range of 0.6 to 1.1.

"The results of analyses of the airborne gamma radiation and total magnetic field survey flown for the region identified as the Socorro National Topographic Map NI13-4 is presented in this report"--Abstract.

Report explaining some different categories of special refractory materials. These categories of materials and their properties are discussed as well as the specific materials that fall into these categories.

Report describing the results of corrosion tests on 68 types of materials. Generally, most materials were tested with an agitator and vapor and some were tested a 3rd way with alternate immersion.

Report discussing a study involving P.I.G.'s (Philips Ion Gage) in TCl₄ vapor in an all-carbon oven to compare data to a previous study involving P.I.G.'s in air. The purpose of the investigation was to determine the best P.I.G. in TCl₄ vapor and obtain its calibration.

This report refutes earlier calculations made in the flux level of exponential piles. The results of the earlier calculations made on subcritical assemblies using critical assembly equations are in error. The calculations used in this report were more successful.

An exact treatment of the structure of tracks in nuclear research emulsion recently was attempted with some success. Many of the proofs also appear to be generally valid for bubble tracks in Wilson chambers. This is a summary of the results that are applicable to tracks of charged particles in bubble chambers.

Memorandum presenting a low-speed investigation to determine the effect of a fuselage on the longitudinal aerodynamic characteristics of a 45 degree sweptback wing equipped with 0.35-semispan double slotted flaps. The wing had an aspect ratio of 3.7, a taper ratio of 0.41, and a streamwise thickness ratio of 0.086.

Memorandum presenting a high-flow sonic-inlet compressor rotor employing double-circular-arc blade sections that was designed and tested in Freon-12. Results regarding overall performance, radial distribution, and blade-element performance are provided.

Report presenting a free-flight investigation over a range of Mach numbers at a range of lift coefficients to determine the aerodynamic characteristics of an airplane-configuration model with a 52.5 degree delta wing and a low, swept horizontal tail. Results regarding time history, longitudinal trim, lift, drag, longitudinal static stability, side-force characteristics, and theoretical comparisons are provided.

"Simultaneous measurements were made of the speed of flame and the rise in pressure during explosions of mixtures of carbon monoxide, normal heptane, iso-octane, and benzene in a 10-inch spherical bomb with central ignition. From these records, fundamental properties of the explosive mixtures, which are independent of the apparatus, were computed. The transformation velocity, or speed at which flame advances into and transforms the explosive mixture, increases with both the temperature and the pressure of the unburned gas" (p. 39).

"An investigation was conducted to determine the longitudinal- and lateral-stability characteristics of a 0.5-scale model of the Fairchild Lark missile. The model was tested with 0 deg and with 22.5 deg of roll. Three horizontal wings having NACA 16-009, 16-209, and 64A-209 sections were tested. Pressures were measured on both pointed and blunt noses" (p. 1).

Report presenting an investigation to study the influence of high relative inlet Mach number on the performance of a highly loaded blade row. Twenty-nine rotor blades were installed in a compressor rotor and static and total pressure, total temperature, and flow-angle surveys were taken upstream and downstream of the row.