This report follows the study of a perturbation in the fringing magnetic field of a synchrocyclotron, using the computed unperturbed orbits of the modified Berkeley 184-inch synchrocyclotron, and introduces the peeler extraction to overcome limitations by using a perturbation that recedes with increasing radial amplitude.

Abstract: Beehive is a five energy group, two region, time independent spherical reactor code. It considers the problem of reactor system in which the core material is assumed to be at a higher energy (temperature) than the reflector material. The code obtains a closed solution for the critical reactor assembly by a procedure which is a logical extension of normal two group theory. The companion code, Hornet, computes the neutron fluxes for the critical assembly determined by the Beehive calculation. Both codes have been programmed for the IBM Magnetic Drum Data-Processing Machine, Type 650. The codes, together with the flow diagrams, are included with this report.

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Summary: The scope and intent of this report is to demonstrate the feasibility of a nuclear powered tanker for service in the United States Maritime Fleet.

Report discussing tests performed with a rocket-boosted model of the McDonnell F4H-1 airplane at transonic and supersonic speeds. Special attention is given to the external drag coefficient at various Mach numbers. Large pitching oscillations were also noted at Mach numbers between 0.20 and 1.17, which made it impossible to determine the drag at that range.

Report discussing a series of experiments involving the reaction of water with decaborane and HEF-3, a boron fuel containing ethyldecaborane. The chemical properties of the hydrolysis reaction are described. Two isomers were also prepared to assist with the syntheses, and their melting points, molecular weights, and solubilities in certain solvents are included.

Memorandum presenting an investigation to determine the dynamic lateral stability characteristics of a configuration of the North American X-15 research airplane. Of specific concern were characteristic modes, period and damping, airplane response to yaw and roll controls, ratio of roll to sideslip in the Dutch-roll oscillation, and the roll-coupling problem. Results regarding stability-boundary plots, characteristic roots, roll-to-sideslip ratio, and time histories are provided.

"An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers of 1.7 x l0(exp 6) and 3.6 x l0(exp 6) to determine the pressure distributions over a swept wing with a series of 14 control configurations. The wing had 40 deg of sweep of the quarter-chord line, an aspect ratio of 3.1, and a taper ratio of 0.4. Measurements were made at angles of attack from 0 deg to +/- 15 deg for control deflections from -60 deg to 60 deg. This report contains tabulated pressure data for the complete range of test conditions" (p. 1).

Report presents results of tests made on a power control system by means of a ground simulator to determine the effects of various combinations of valve friction and stick friction on the ability of the pilot to control the system. Various friction conditions were simulated with a rigid control system, a flexible system, and a rigid system having some backlash. For the tests, the period and damping of the simulated airplane were held constant.

This letter dated March 8, 1957 summarizes the results of preliminary studies on the stepwise expansion of Purex facilities to the ultimate rate of 4.0 capacity factor, using a two-cycle flow-sheet. Briefly, it was suggested that Purex be expanded to the intermediate capacity of 3.5 capacity factor using available FY-1958 funds insofar as possible; decision to expand Purex to 4.0 capacity factor, could have been deferred for subsequent budgetary consideration.

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Discussing a uranium reconnaissance program undertaken to evaluate formations that were producing uranium and vanadium ore in the Sanastee area.

Progress report of the Brookhaven National Laboratory Nuclear Engineering Department providing updates on various projects, experiments, and other work. This report includes a summary of scholarly output from the reactor physics division, the applied chemistry and chemical engineering division, and metallurgy division.

Report issued by the Oak Ridge National Laboratory discussing the Research Reactor (ORR). General descriptions of the ORR are presented. This report includes tables, and illustrations.

Purex process which utilizes solvent extraction to separate and purify uranium and plutonium from each other and from fission products contained in irradiated uranium fuel elements.

Report discussing a low-lift lateral stability investigation with a rocket-propelled model of a 45 degree swept-wing-airplane configuration equipped with an auxiliary yaw-rate damper system at a range of Mach numbers. Results indicated that the system was nonlinear due to a large dead spot in the system. The primary effect of the system was to increase the damping of lateral oscillations.

"A series of experiments involving the reaction of water with decaborane and HEF-3, a borane fuel consisting mainly of ethyldecaborane, was performed. The results show that the presence of one alkyl group on the decaborane nucleus inhibits the hydrolysis reaction significantly and that the hydrolysis rate can be increased by using an acidic hydrolysis mixture. Two diiododecaborane isomers were prepared for use as intermediates in proposed dimethyldecaborane syntheses, and their melting points, molecular weights, and solubilities in certain solvents were determined" (p. 1).

Report presenting experiments in a 200-pound-thrust jet fuel-nitric acid rocket with an axial-flow igniter employing the hypergolic alkyl thiosphosphite-nitric acid system. No combustion instability was observed in the igniter, but many of the main-stage runs exhibited low-frequency oscillations.

Report presenting the deposition rate of boric oxide from a stream containing submicron particles, which was found experimentally to fit a molecular diffusion equation. Results regarding boundary-layer studies, deposition studies, deposition tests, and turbojet engine performance are provided.

Report presenting an investigation to determine the dynamic lateral stability characteristics of a configuration of the North American X-15 research airplane. The characteristic modes, period and damping, airplane responses to yaw and roll controls, ratio of roll to sideslip in the Dutch-roll oscillation, and the roll-coupling problem are the primary focus.

Memorandum presenting a study of the chemical and physical properties of the high-energy fuel HEF-2. The properties measured included elemental analysis, heat of combustion, density, freezing point, self-ignition temperature, flash point, viscosity, molecular weight, vapor pressure, refractive index, and the water and oxygen stability.

Air was bled over the fifth-and tenth-stage rotor-blade rows through ports designed to pass 11 and 9 percent of the inlet flow, respectively, at 80 percent speed. Along the rated operating line the maximum speed at which rotating stall was encountered was lowered by either of these bleeds, and the stall patterns below these speeds were altered so that no dangerous resonant rotor-blade bending vibrations were excited. The combination of the two bleeds completely eliminated rotating stall to at least 50 percent speed. The compressor-discharge weight flow was decreased only at intermediate speeds, and the overall pressure ratio was affected only at intermediate speeds, and the overall pressure ratio was affected only by the combination bleed at intermediate speeds. Fifth-stage bleed increased compressor efficiency at low speeds, and tenth-stage bleed decreased efficiency at intermediate speeds.

Report presenting an exploratory investigation to determine the effects of wing slots on the longitudinal stability characteristics of a 45 degree sweptback wing-fuselage combination. Results regarding pitching-moment characteristics and lift and drag characteristics are provided.

From Summary: "A flight test was conducted with a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane configuration at transonic and supersonic speeds. The external drag coefficient varied from a value of 0.044 at a Mach number of 1.17 to 0.045 at a Mach number of 1.40 and then decreased to 0.041 at a Mach number of 1.90. The limited oscillatory data available indicate the existence of a coupled longitudinal-lateral motion in the Mach number range from 0.20 to 1.17."