From abstract: "This report summarizes the corrosion data obtained for nine construction materials located throughout the ORNL Purex Pilot Plant Acid Recovery Unit during seven hundred hours of operation."

Abstract: "The trajectory analysis of an immobilized plasma has been generalized to include the presence of electrons having a far similar radius of gyration and, therefore, fitting readily into the broader scale structure established by the ions. This problem has been adapted to machine calculations and the results for various strengths plasmas have been calculated."

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, Will Wilson, regarding a legal question submitted for clarification: Whether or not the royalty interest and fee interest conveyed in trust to the First National Bank of Longview for the use and benefit of the Roy H. Laird Memorial Hospital owned by the City of Kilgore would be exempt from taxation.

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, Will Wilson, regarding a legal question submitted for clarification: Certification of candidates is a special election where his application was mailed on that last day for filing but was not received until the following day.

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, Will Wilson, regarding a legal question submitted for clarification: Authority of the Commissioners' Court of a County to pay the salaries of a secretary and business manager for a Soil Conservation District.

Introduction: "The problem of determining the properties and necessary controls on the TBP Plant waste disposal to eliminate transport line plugging and to permit higher concentration prior to return of this to the tank farms was studied. A report of preliminary findings was made to L. W. Finsh on January 31, 1953. This report compiles information in the aforementioned report and findings since its issuance. Previous studies related to this problem are summarized in the U. R. Technical Manual, HW-19140."

Annual report of the Liquid Metal Fuel Reactor Experiment describing progress during calendar year 1958 and as well as an evaluation of progress and plans for future work.

The in-line monitoring instruments installed in the Redox plant in the late 1950s consisted of six gamma monitors, a single channel gamma spectrometer, an alpha monitor, and a neutron counter. A gamma monitor on the steam condensate outlet line and a uranium monitor on the 2DFS stream were to be added at a later date. The first section of this information manual describes the in-line gamma monitors and gives operating instructions for them. The second section covers the alpha monitor, and the third section the neutron counter. Sections on the uranium monitor and the steam header gamma monitor were to be added at a later date.

Progress made in the field of spectrophotometry of molten fluoride salts is summarized. The high-temperature cell assembly designed and fabricated for use in this work is described, as well as the various types of sample containers used. Spectra of nickel fluoride, cobalt fluoride, chromic fluoride, and uranium tetrafluoride in LiF--NaF-KF (46.5-11.5--42 mole%) are presented. (auth)

A process has been developed for application of a thin, adherent vinyi plastic coating to graphite plates to prevent absorption of coupling fluids'' used in ultrasonic inspection. The plates are preheated and dipped mechanically in a fluid plastisol, and the resulting coating is fused in an infra-red heater. No significant attenuation of ultrasonic impulse results from presence of the coating. After inspection, the vinyl sheath may be easily stripped from the plate. (auth)

Report presenting testing of a towed airplane model in the 19-foot pressure tunnel in conjunction with the development of a flutter testing technique. The model was equipped with an autopilot to keep the model flying straight and level in the tunnel while restrained only in drag. Results regarding period and cycles to damp to half amplitude, time histories, and motions of the flexible wing model are provided.

Report presenting the results of a wind-tunnel investigation to determine the effects of various free-flight rocket-model booster-adapter configurations on the aerodynamic characteristics in pitch and sideslip of a swept-wing, fighter airplane model with a Mach number of 2.01. Results regarding the effect of adapter shape and aerodynamic characteristics of the model alone are provided.

Report presenting a flight investigation of a rocket-launched ram-jet engine incorporating an end-burning solid fuel. Results regarding acceleration, altitude, booster separation, survival time of booster adapter, and air specific impulse are provided.

Report presenting a rocket-propelled missile model with cruciform, triangular, inline wings and tails, which has been tested through a range of Mach numbers at small wing-deflection angles. Results regarding the stability and damping, control effectiveness, and hinge moments are provided.

Report presenting an investigation of spoilers at a Mach number of 1.93 to determine the effects of height and chordwise location on the section pressure distributions and section aerodynamic characteristics of a two-dimensional, 6-percent-thick, symmetrical wing. Spoilers of 3-, 5-, and 7-percent-chord height were tested at three chordwise locations. Results regarding pressure distributions, aerodynamic characteristics, and shock boundary-layer interactions are provided.

Report presenting an investigation in the transonic blowdown tunnel between Mach numbers of 0.65 and 1.4 to determine whether the principles of the transonic area rule could be used to improve the transonic drag-rise characteristics of a semielliptical shaped sweptback air inlet installed in the root of a sweptback wing-body combination. Results regarding the effect of the inlet and the interaction of Mach number and drag coefficient are provided.

Report presenting the effects of nacelle location on the zero-lift drag of 45 degree sweptback wing-body combinations with boattail and cylindrical afterbodies at a range of Mach and Reynolds numbers. The nacelles were located at three different areas and the afterbody shape was also altered by replacing the boattail afterbody with a cylinder. Results regarding faired curves of the variations of total drag, base drag, and fin drag coefficients, and applicability of the transonic area rule are provided.

Report presenting the effect on base pressure of bleeding air to the semidead-air region at the trailing edge of two-dimensional blunt-trailing-edge airfoils at two Mach numbers. Variation of base pressure with base-bleed rate was determined for two airfoils profiles with both laminar and turbulent boundary layers approaching the trailing edge. Results regarding the effects of jet geometry, effects of jet area, effect of base bleed on the flow in the wake, effect of angle of attack, effect of Reynolds number, correlation of the results with mass-flow rate of the bleed air, and effect of base bleed on the drag of blunt-trailing-edge airfoils are provided.

From Introduction: "The purpose of this paper is to present an analysis of the data for the remaining airplanes where the data were sufficient to warrant analysis. The data analyzed represent totals of 351 to 5660 hours of operations with ten types of Navy airplanes and were recorded during the period 1949 to 1953."

Preliminary results are presented from an investigation to determine the influence of afterbody geometry on the effects of a sonic propulsive jet at transonic speeds. The results presented are base pressure coefficient and afterbody pressure-drag coefficient as a function of jet pressure ratio for different values of Mach number and jet temperature. Geometric parameters investigated include boattail angle, jet-to-model diameter ratio, and jet-to-base diameter ratio.

From Summary: "Measurements of pressure distributions have been made over a wing midsemispan station on the 35 degree sweptback wing of the Douglas D-558-II research airplane at Mach numbers from 1.17 to 2.0. The results of the investigation indicate that, as the angle of attack increased at the higher Mach numbers, the pressure coefficient for a vacuum limited the extent to which the upper-surface pressures could expand. Consequently most of the increase in section normal-force coefficient at high angles of attack can be attributed to the increase in pressure over the lower surface."

Report presenting results of a wind-tunnel investigation to determine the effects of various free-flight rocket-model booster-adapter configurations on the aerodynamic characteristics in pitch and sideslip of a swept-wing, fighter airplane model for a Mach number of 2.01. Normal-force, lateral-force, pitching-moment, and yawing-moment coefficients of the airplane model were measured, and schileren photographs of the various configurations were obtained.

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