A linear accelerator, which increases the energy of protons from a 4 Mev Van de Graaff injector, to a final energy of 31.5 Mev, has been constructed. The accelerator consists of a cavity 40 feet long and 39 inches in diameter, excited at resonance in a longitudinal electric mode with a radio-frequency power of about 2.2 x 10{sup6} watts peak at 202.5 mo. Acceleration is made possible by the introduction of 46 axial "drift tubes" into the cavity, which is designed such that the particles traverse the distance between the centers of successive tubes in one cycle of the r.f. power. The protons are longitudinally stable as in the synchrotron, and are stabilized transversely by the action of converging fields produced by focusing grids. The electrical cavity is constructed like an inverted airplane fuselage and is supported in a vacuum tank. Power is supplied by 9 high powered oscillators fed from a pulse generator of the artificial transmission line type. Output currents are 3 x 10 {sup-9} ampere average, and 50 {mu}a peak. The beam has a diameter of 1 cm and an angular divergence of 10{sup-3} radians.

In the past year, exploratory data have been taken to determine the relative solubilities of hydrogen and deuterium in various solvents in the vicinity of room temperature and atmospheric pressure. This investigation is one phase of a program to determine the feasibility of separating deuterium from hydrogen by means of rectified absorption.

Gamma plutonium is found to be orthorhombic with eight atoms in a unit cell of dimension (1t 235 degree C) [formula]. The calculated density is [formula]. The space group is Fddd and the positions of the eight atoms are: [formula]. Each plutonium atom is bonded to ten others at an aver distance of [formula], four being at [formula], two at [formula] and found at [formula]. The mean linear coefficients of thermal expansion are found to be [formula].

"The field of a uniformly loaded wing in subsonic flow is discussed in terms of the acceleration potential. It is shown that, for the design of such wings, the slope of the mean camber surface at any point can be determined by a line integration around the wing boundary. By an additional line integration around the wing boundary, this method is extended to include the case where the local section lift coefficient varies with spanwise location (the chordwise loading at every section still remaining uniform)" (p. 471).

The results of fuel-air ratio and temperature surveys made in the flame stabilizing zone of a 16-inch ram-jet combustor indicated that the distribution of combustible mixture immediately downstream of a flame holder should be mechanically controlled if a preferred mixture composition is to be maintained in that zone. A sloping-baffle combustor configuration gave combustion efficiencies of 90 percent or greater over a range of fuel-air ratios from 0.010 to 0.045.

Report presenting an investigation to determine the effect of fuel volatility characteristics on the minimum spark energy required to ignite a single tubular turbojet-engine combustor. Results regarding the ignition at sea-level conditions, ignition at altitude conditions, relation between distillation data and minimum ignition-energy requirements, and application of relation to data from a previous investigation are provided.

Report presenting the development of an annular combustor by utilizing the design principles evolved in previous investigations and by making 12 design changes to optimize the altitude performance of the combustor. Three types of fuels were used and the combustion efficiency, pressure losses, and outlet temperature profiles were evaluated.

From Summary: "A parameter is introduced which simplifies the accounting for pressure losses in ram-jet combustors. This parameter, called the combustor-force coefficient, relates the jet force and the total pressure at the combustion-chamber entrance. Experimental data for several different combustors are presented for evaluation and comparison."

Report presenting the results of an experimental investigation of several types of aerodynamically balanced trailing-edge flaps on an aspect ratio 2 triangular wing are presented. The balancing devices tested consisted of flap overhang, paddles, rectangular and triangular horns, and trailing-edge tabs. Results regarding the lift, drag, pitching moment, hinge moment, and rolling moment are presented for a range of Mach numbers and a constant Reynolds number.

The results of transonic flight measurements of the longitudinal stability characteristics of the Douglas D-558-II research airplane in the original configuration and with outboard fences mounted on the wings are presented. The levels of normal-force coefficient at which the stability decreases and pitch-up starts have been determined for both airplane configurations at Mach numbers up to about 0.94.

Purpose: "The Hanford Works Analytical Manual for Process Water is designed to specify the analytical methods to be applied for control purposes in the Reactor Section, Process Sub-Section laboratories. The procedures are in general form and serve as references rather than outlined laboratory instructions. The manual us designed to replace the "Hanford Works Manual," HW-12862."

Investigation of the internal performance characteristics of several jet-exit configurations over a wide range of pressure ratios, which are summarized to provide an overall picture of jet-exit performance. The configurations investigated include a convergent nozzle, fixed convergent-divergent nozzles, an adjustable plug-type convergent-divergent nozzle, and jet ejectors. Results regarding the performance of several jet-exit configurations and matching adjustable jet exits to supersonic aircraft are provided.

Report presenting an investigation of a four-blade single-rotation propeller in combination with an NACA 1-series D-type spinner-cowling combination at Mach numbers up to 0.83. Characteristics of the propeller operating in the presence of the cowling are compared with the characteristics of the propeller with the spinner.

The following documents are quarterly progress reports recorded in the chemistry division of the University of California's radiation laboratory.

A summary of operating experience and observations obtained during approximately 5OO hrs of running time on the PuP lead-bismuth forced circulation system is given. (auth)

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Report presenting engine evaluation tests of twelve sets of cermet turbine blades. The first five runs were similar to previous engine tests, but the remaining ones were modified based on information gained during the first runs.

Report presenting a theoretical investigation of the lateral stability of a towed high-speed fighter plane using a fighter cruising at supersonic speed at 50,000 feet and a 1000-foot cable. The motion of this configuration was shown to have highly unstable oscillation caused by the towline restraint, but the configuration can be stabilized by choosing the right position for the towline connection and several types of automatic controls.

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Report discussing the distribution of mass in the spontaneous fission of Cm²⁴², which was investigated by a radiochemical determination of the fission yields of twenty-one nuclides ranging in mass from 91 to 140. "Corrections for absorption, scattering, geometry, decay, and fractional saturation were applied to obtain saturation disintegration rates, which, with the known fission rate of the source, give the fission yields."

Report presenting an investigation of the low-speed stability and control characteristics of a scale model of the proposed MX-1554A design. It employs a triangular wing and triangular stabilizing surfaces. Results regarding the effect of wing incidence, tail position, fences, and chord extensions on the longitudinal characteristics are provided.

The operational characteristics of the Cosmotron were reviewed in brief. Since a rather complete account of this machine is now available in the September 1953 issue of Rev. Sci. Inst., this summary will include only the more recent utilization of the machine as a research instrument.

Report presenting an investigation to determine the low-speed large-scale characteristics of an aspect ratio 3 triangular-wing airplane model. The model consisted of the wing in combination with a fuselage of fitness ratio 12.5, a thin, triangular vertical tail with a constant-chord rudder, and a thin, unswept, all-movable tail.