This report analyzes a procedure based on the production of acetylene from the active water, with subsequent measurement of the ionization caused by the tritium beta particle. This eliminates the troublesome absorption on the chamber walls when hydrogen is used, and provides a rapid method for the preparation of the urine samples.

The experimental data presented in HDC-1255 for the pressure drops through the various portions of a standard process tube assembly for isothermal flow are correlated in this report. Data include orifice sizes up to 0.310 inches. The equations have been adapted for the calculation of pressure drops or flow rates for clean tubes in pile operation. A systematic procedure is outlined for determining the pressure drops through each portion of the tube assembly. A method is presented for calculating the flow rate through a process tube from header pressure and panellit age readings.

This trip was spent in conferences with H. Etherington, A. Amroni, Geo. Anderson, and L.W. Fromm; and in inspection of components now being built for the Navy Test Rig which is to be installed at H Pile. Mr. Anderson believes that the entire assembly will arrive at Hanford between January 16 and 23, 1950. Much has yet to be designed and built, however. Also, certain incompatibilities with the H Pile were pointed out, and will be altered.

This paper describes a means of determining tritium oxides in urine relying upon the production of acetylene from the active water with subsequent measurement of the ionization caused by the tritium beta particle.

Report presenting the flying qualities problems of current helicopters, including instability with angle of attack in forward flight, control sensitivity in hovering, and control forces following control movement in maneuvers. Some possible solutions to these issues are presented.

Report presenting the results of a wind-tunnel investigation of the low-speed aerodynamic characteristics of a 45 degree sweptback horizontal-tail model of aspect ratio 2 and a comparison of these results with results for a model of the same aspect ratio with an unswept hinge line. Results regarding the lift and hinge-moment parameters, static longitudinal stability, effect of Reynolds number, effect of standard roughness, effect of removing elevator nose seal, and visualization of the air flow are provided.

Report presenting rocket-powered flight tests from high subsonic to supersonic speeds and at high Reynolds numbers to determine the zero-lift drag of a transonic wing-body and body-alone configuration. The configuration tested featured a wing of 45 degree sweepback, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section, and a body of fineness ratio of 10 and a frontal area equal to 6.06 percent of the wing-plan-form area.

An investigation was conducted at a Mach number of 1.91 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic leading edge swept back at 70 degrees. Except for pressure distribution on the top surface in the immediate vicinity of the subsonic leading edge, the maximum difference between linearized theory and experimental data was 2 1/2 percent (of free-stream dynamic pressure) for angles of attack up to 4 degrees and 7 percent for angles of attack up to 8 degrees. Pressures on the top surface nearest the subsonic edge indicated local expansions beyond values predicted by linearized theory.

Memorandum presenting the low-speed lateral-control characteristics of a 37 degree sweptback semispan wing of aspect ratio 6 and NACA 64-series airfoil sections in the 19-foot pressure tunnel. The investigation included the measurement of the hinge-moment characteristics of an aileron and the rolling-effectiveness characteristics of the aileron and two configurations of spoilers.

An investigation of the damping-in-roll characteristics of three wings with an aspect ratio of 4, a taper ratio of 0.6, three sweep angles at the quarter chord line, and the NACA 65A006 section as determined through a range of Mach numbers and angles of attack.

From Summary: "A determination of the dynamic characteristics of a typical turbojet engine with a centrifugal compressor, a sonic-flow turbine-nozzle diaphragm, and fixed area exhaust nozzle is presented. A generalized equation for transient behavior of the engine was developed; this equation was then verified by calculations using compressor and turbine performance charts extrapolated from equilibrium operating data and by experimental data obtained from an engine operated under transients in fuel flow."

The overall testing of the vertical sheet rod system is a comprehensive program which has been divided into several phases. These phases are presented here, with a short resume of the testing required under each phase, to enable the formulation of the project proposal for the complete test program. It is intended that very detailed test requests will be issued for the separate phases as data from previous tests and further design studies indicate the exact information or data desired from a particular test.

The basis feed to the Redox plant is 5,000 lb/day of uranium, supplied both as current irradiated uranium metal slugs in jackets, and as uranium compounds from the existing metal waste storage tanks. The proportions of the two feeds are chosen according to the enrichment level of the irradiated metal, so as to give a plutonium production of about 650 gm/day. The design basis has been taken as 0 to 1,500 lb/day U from the waste storage system and 2,000--5,000 lb/day of irradiated metal. Only the feed preparation from irradiated metal is discussed in this process description, and a basis of 5,000 lb/day is used throughout. The metal feed has associated with it 172.5 lb. Al and 2.5 lb. Si as slug jackets, and contains about 650 gpm. plutonium and 3 {times} 10{sup 5} curies of gamma-emitting fission products (FP). The purpose of the feed preparation section is to remove the aluminum and silicon, and to dissolve the uranium as an aqueous solution for feed to the Redox extraction battery. Secondarily, it is tentatively proposed to provide equipment in this section to achieve a preliminary decontamination from ruthenium, which is poorly handled by the Redox extraction system, and from FP …

This report details events of importance reported by the Hanford Operations Office for the week ending April 27, 1949.

This report details events of importance reported by the Hanford Operations Office for the week ending May 25, 1949.

Field work in White Canyon was initiated to determine reserves of uranium ores and to determine the nature of the physical, geological, and economic conditions affecting mining and milling of such ores.

From Summary: "An investigation has been conducted with the Langley helicopter tower to obtain basic performance and control characteristics of the Raman rotor system. Blade-pitch control is obtained in this configuration by utilizing an auxiliary flap to twist the blades. Rotor thrust and power required were measured for the hovering condition and over a range of wind velocities from 0 to 30 miles per hour. The control characteristics and the transient response of the rotor to various control movements were also measured."

The take-off stability characteristics of a Consolidated Vultee Aircraft Corporation Skate 7 seaplane were determined in the Langley tank no. 2. Trim limits of stability, trim tracks, and elevator limits of stability are presented.