Report discussing details of the design for the Bevatron at the University of California Radiation Laboratory. The Bevatron is a "6-billion-electron-volt (Bev) proton synchotron. This device will receive a 10-million-electron-volt (Mev) proton beam from a linear accelerator, and further accelerate a reasonable percentage of these protons, at a nominally constant radius of 600 inches, to a final energy greater than 6 Bev."

Abstract: "A titrimetric method for the determination of fluoride in plutonium is reported. Prior to a steam distillation of the fluoride, the bulk of the plutonium is separated by precipitation of the sulfate. The fluoride in the distillate is titrated at a pH of 3.2 with 0.001 M thorium nitrate, using chrome azurol-S indicator. Applied to samples containing 1 to 15 parts per million fluoride, the recovery is 87% and the precision on the 95% confidence level is +/- 0.65 ppm."

Document 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: Authority of a county to lease space and facilities from a private hospital for the purpose of hospitalizing county paupers.

Document 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: Construction of Article 5221b-5 (c)(5), V.C.S., to determine the denominator of the fraction representing "State experience factor" as that term is used in the above statute.

Document 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: Travel expense of State employees.

The design and proposed construction of the new PR facility for Redox is based on the need for increased capacity for plutonium processing (4.25 kg./day, equivalent to the 8.3 tons of U/day for Redox phase 2 rate), and reduced acid-to-Pu ratios in the final product to permit satisfactory processing in task 1 of the 234-5 operation. A number of alternate Pu cycle flowsheets have been scouted and proposed in the past several years. One such flowsheet decreases the acid-to-Pu ratio in the 3BP product by eliminating acid from the 2AX and 3AX, thus requiring either an increased solvent flow, or an increased ANN salting strength. This does not, however, provide additional Pu processing capacity. A second alternative flowsheet involves the reflux of 97.5% of the 2BP stream back to the 2A Column. The reflux flowsheet meets both of the needs outlined above, but on the basis of nuclear safety considerations is not yet considered ready for adoption in the Redox Plant. This report deals with the laboratory testing of a third alternative for reducing the acid concentration in the final product by decreasing the acidity of both scrub and feed streams to the third cycle.

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Memorandum presenting pulse techniques applied to strain gages for increasing the output level and extending the usable range. Bonded and unbonded strain gages which normally operate with exciting potentials between 3.5 and 14 volts operated satisfactorily with 200-volt pulses of 1-microsecond duration and a repetition rate of 350 per second. Results regarding maximum allowable voltages, effective pulse duration, sensitivity, minimum readable signal, effects of cable capacitance and inductance, sensitivity to external noise, and linearity are provided.

"Flight tests were made to determine the total-pressure recovery of a split-wing ram-jet inlet with a fixed area exit 20 percent larger than the inlet throat over a Mach number range from 1.4 to 3.16. Total-pressure-recovery measurements at the diffuser exist station indicated abrupt pressure changes in the total-pressure profile throughout the Mach number range. Comparisons of average total-pressure recovery with the theoretical total-pressure recovery showed good agreement" (p. 1).

Memorandum presenting an investigation in the 7- by 10-foot tunnel to determine the effect of wing-root leading-edge- and scoop-type jet-engine air-inlet configurations on the static lateral stability characteristics of a scale model of the MX-1764 airplane. The addition of the inlet configurations to the model generally had only small effects on the lateral stability.

From Introduction: "The purpose of this report is to present the results of the analytical investigation of the turbine of reference 1 to indicate the extent to which the various turbine losses affect the turbine efficiency over the range of performance."

Report presenting an investigation of the proper means of coordinating the lift-acceleration commands and the roll-attitude commands to the autopilot in order to minimize transient racking errors encountered during bomber evasion. Results regarding the pull-up maneuver, horizontal turning maneuvers, the split S vertical plane maneuver, diving turn maneuver, other considerations involved in rolling maneuvers, and maximum rates of roll, control motion, and tracking-line motion are provided.

A survey of experimental data at supersonic speed indicated that shock-induced separation of a turbulent boundary layer will result for Mach numbers of approximately 1.33 or greater when a theoretical stream static-pressure-rise ratio of approximately 1.89 occurs across a shock interacting with the boundary layer. The significance of this tentative criterion for turbulent boundary-layer separation is discussed with respect to the design of supersonic diffusers.

"Slurry fuels containing extremely small particles of magnesium were prepared by concentrating the dilute slurry product resulting from the shock-cooling of magnesium metal vapors with a liquid hydrocarbon spray. A complete description of the equipment and procedure used in preparing the fuel is given. Ninety-five percent by weight of the solid particles formed by this process passed through a 100-mesh screen. The particle-size distribution of the screened fraction of one run, as determined by sedimentation analysis, indicated that 73 percent by weight of the metal particles were finer than 2 microns in equivalent spherical diameter" (p. 1).

Report presenting an experimental investigation to determine the effect of thickness and of thickness distribution on the fluctuations of normal-force and pitching-moment coefficients of airfoils. Seven symmetrical airfoils were tested. Two types of pressure pulsations were noted in the study: pulsations from an intermittent build-up and dropping of the pressure peak near the leading edge and pulsations attributable to shock-wave motion and unsteady air flow following the shock wave.

Report presenting preliminary drag data obtained for the XF-92A delta wing airplane during demonstration tests after it had been modified to use the J33-A-29 turbojet engine. Drag data, lift coefficients, and lift-curve slopes are provided.

From Introduction: "Because of the lack of data on compressor characteristics at 130 or 145 percent of design equivalent rotational speed, several simplifying assumptions were made regarding the compressor characteristics during operation at equivalent rotational speeds above the design value (hereinafter called "compressor overspeeding"). In addition to results based on these assumptions, the effect of deviation from these assumptions is discussed."

Report presenting flight tests to determine the total-pressure recovery of a split-wing ram-jet inlet with a fixed area exit 20 percent larger than the inlet throat over a range of Mach numbers. Total-pressure-recovery measurements at the diffuser exit station indicated abrupt pressure changes in the total-pressure profile throughout the Mach number range.

Report presenting a scale model of the Convair XF2Y-1 airplane with a solid-fuel rocket motor designed to simulate full-scale turbojet engine characteristics with full afterburning at a Mach number 1.2 and an altitude of 35,000 feet in free flight at a maximum Mach number of 1.45. Results regarding stability characteristics, trim characteristics, and the effect of rocket exhaust over the beaches are provided.

Report presenting the ignition delays of propane-oxygen-nitrogen mixtures as a function of temperature and composition in a flow system. Results regarding the effect of apparatus parameters, effect of propane concentration, effect of oxygen concentration, effect of temperature, and interpretation in terms of slow reaction kinetics are provided.

Memorandum presenting an investigation of the effect of the addition of approximately 6 percent nickel, cobalt, or platinum on some properties of molybdenum disilicide. These additions resulted in appreciably lowering the modulus-of-rupture strength from that of unalloyed molybdenum disilicide. Results regarding density and particle-size analysis, chemical analysis of bars, metallographic and x-ray analysis, density and resistivity, modulus-of-rupture strengths, thermal shock tests, and oxidation resistance are provided.

Report presenting free-falling recoverable-model tests at transonic speeds on a model with a low-aspect-ratio thin unswept wing and a 45 degree swept tail in the chord plane of the wing. Static- and dynamic-stability data and load-distribution data were obtained at a range of angles of attack. Results regarding lift, drag, static longitudinal stability, dynamic longitudinal stability, horizontal-tail effectiveness, loading distribution over the fuselage, and buffet boundary are provided.