From page 2: "This article first describes the Bevatron [particle accelerator] and its operation, and then discusses a portion of the research program. The principles of the machine and its early history were given in "The Bevatron," by Lloyd Smith, Scientific American, February 1951."

A sprawling group of buildings on an impressive campus site in the Berkeley hills provides the home of the Radiation Laboratory of the University of California. A succession of large accelerators has been built there, the latest of which is the Bevatron. It is the largest and highest-energy accelerator in operation at the present time. It was built and is operated under contract with the United States Atomic Energy Commission. It is of the type known as a proton synchrotron, of which there are two others in operation, one at the University of Birmingham, England, whose energy is 1 Bev (billion electron volts), and another at the Brookhaven National Laboratory, known as the Cosmotron, which operates at 3 Bev. The Bevatron accelerates protons (stripped nuclei of hydrogen atoms) to an energy of 6.2 Bev. The design was started in 1947 under the direction of Professor E. O. Lawrence, and although it was the product of collaboration of a large group of physicists and engineers, the original conception was due to William Brobeck who also contributed more than any other individual. A working quarter-scale model was built and operated in 1948 and 1949 to verify the correctness of the design concept. …

Report presenting analytical estimates of the thrust, efficiency, drag, and weight of the air-turborocket engine. The effects of changes in the engine components on design and off-design performance are emphasized. Results regarding the performance, effect of design parameters, effect of subsonic cruising Mach number, geometry variations, engine weight estimates, and comparison with turbojet engines are provided.

Report presenting an evaluation of data obtained with an automatic constant inlet-pressure control valve designed to facilitate the study of transient engine performance characteristics in the altitude wind tunnel. The engine characteristics obtained by use of the pressure valve were compared with those obtained with a bellmouth inlet operating in simulated free-stream conditions.

Report discussing methods for recovering hafnium-free zirconium from irradiated fuel elements. Two methods are discussed: the fluoride method and the Zircex method. Experimental procedures to evaluate these methods and their results are presented.

Report presenting an investigation of an exhaust jet and elementary contoured surface at Mach number 1.6 over a range of nozzle pressure ratios from jet-off to a pressure ratio of 9. The effect of the presence of streamline fairings between the surfaces and parabolic afterbody housing the exhaust nozzle on the interaction was also investigated.

Report presenting a determination of the relative reactivities of six fuels with red fuming nitric acid in a 40-pound-thrust rocket engine with rapid liquid-phase mixing. Hydrazine, trimethyl-trithiophosphite, furfuryl alcohol, unsymmetrical dimethylhydrazine, allylamine, and o-toluidine were studied. Results regarding the combustion characteristics of the fuels, fuel ratings, pressure in the mixing cup, effect of chamber diameter, and overall combustion efficiency are provided.

Memorandum presenting a study of several typical air induction systems for modern aircraft, which indicates that flow distortions of about-pipe-flow magnitudes can be expected at near-optimum inlet-engine matched air-flow conditions and at small angles of attacks. The distortions may be seriously increased by operation at large angles of attack or yaw, or by supercritical operation of the inlets. Boundary-layer bleed, duct overexpansion and contraction, and freely rotating fans appear promising as devices for reducing distortions with little cost in propulsive thrust.

From Summary: "During the course of an aerodynamic loads investigation of a model of the Martin XP6M-1 flying boat in the Langley 16-foot transonic tunnel, longitudinal-aerodynamic-performance information was obtained. Data were obtained at speeds up to and exceeding those anticipated for the seaplane in level flight and included the Mach number range from 0.84. to 1.09. The angle of attack was varied from -2deg to 6deg and the average Reynolds number, based on wing mean aerodynamic chord, was about 3.7 x 10(exp 6)."

This paper discusses technical bases, operating standards, and instrumentation systems required to achieve the goal of nuclear safety in operation of high-level reactors. Because of the relatively long neutron lifetime in a thermal reactor and the comparatively modest time rates of reactivity change associated with fission poison and temperature effects, the rod system used for compensating reactivity transients and for maintaining flux distribution control may be operated manually. Manual operation of the reactor and the prediction of pile reactivity statue during outages of course involve factors of human error, normal reaction time, and judgment. It is the aim to specify procedures for the operation such that manual control of the reactor may be adequately maintained at all times within the range of reasonably expected calculational errors and human reaction times. The technical considerations used in developing these standards, including the available monitoring indications are discussed first; then the automatic trip devices which should back up the procedures are also mentioned.

At the request of F. W. Albaugh of the Engineering Department, the corrosive effect of 1% uranium nitrate hexahydrate solution on aluminum at 100 C has been measured. The corrosion of aluminum in uranium nitrate solution has been shown in laboratory tests to be too severe to permit the use of aluminum for containing hot uranium nitrate solutions. A minimum corrosion penetration rate of 2 mils per day was observed with M-329 aluminum in 1% uranium nitrate hexahydrate in pH 2 aqueous solution at 100 C.