Major additions to separations facilities may be required because of increased reactor power levels, reduced exposures; changes in slug specifications, obsolescence of existing solvent extraction plants or development of new separations processes with lower operating costs. The magnitude of first costs for a separations plant is so large as to discourage production planning which would require an additional major separations facility. Experience in separations design has shown that certain process and equipment changes, if they could be developed, would significantly reduce the capital investment in a separations facility. Accordingly design development for a new separations facility is under way. The purposes of this document are to present the results of the first separation design study directed toward a new solvent extraction plant and to summarize process, plant, and equipment changes which should be developed to achieve significant capital and operating cost reduction.

This document defines the basic criteria to be used in the preparation of detailed design for Project CG-558, Reactor Plant Modification for Increased Production and for Project CG-600, 100-C Area Alterations. It has been determined that the most economical method of increasing plutonium production within the next five years is by the modernization and improvement of the 100-B, 100-C, 100-D, 100-DR, 100-F, and 100-H reactor plants. These reactors are currently incapable of operating at their maximum potential power levels because of a limited availability of process cooling water. As a result of this program, it is estimated that 1650-2350 megawatts of total additional production will be achieved.

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Report presenting measurements of the longitudinal stability, lift, and drag characteristics of an airplane configuration with a 60 degree delta wing and a swept horizontal tail mounted near the wing plane extended at a range of Mach numbers using the rocket-model technique. Comparisons are made to data form a similar model with the tail mounted above the wing plane.

Report presenting an investigation in the transonic pressure tunnel to determine the aerodynamic loading characteristics of a 60 degree delta wing in the presence of a body with and without body indentation in accordance with the transonic-area-rule concept. Tests covered a range of angles of attack and Mach numbers. Results regarding force and moment coefficients and curves are provided.

Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.61 in which separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The report presents data on a configuration which simulated a fighter-bomber airplane with a large and a small external store.

Report presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.61. Separate forces on a store, a swept wing, and a swept-wing-fuselage combination were measured. This report presents data on a configuration that simulated a fighter-bomber airplane with a large and a small external store.

"The source of an appreciable pitching-moment difference between left and right hovering turns for a tandem helicopter is described. The difference in pitching moment results from the difference in rotational speed of the counter rotating rotors with respect to the air while the helicopter is turning" (p. 1).

From Summary: "It is demonstrated with the aid of similitude arguments that a model launched from a hypervelocity gun upstream through a special supersonic nozzle should experience aerodynamic heating and resulting thermal stresses like those encountered by a long-range ballistic missile entering the earth's atmosphere. This demonstration hinges on the requirements that model and missile be geometrically similar and made of the same material, and that they have the same flight speed and Reynolds number (based on conditions just outside the boundary layer) at corresponding points in their trajectories. The hypervelocity gun provides the model with the required initial speed, while the nozzle scales the atmosphere, in terms of density variation, to provide the model with speeds and Reynolds numbers over its entire trajectory."

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Report presenting a linear stability analysis and flight-test investigation on a rolleron-roll-rate stabilization system for a canard missile. This type of damper provides roll damping by the action of gyro-actuated uncoupled wing-tip ailerons. A dynamic roll instability predicted by the analysis was confirmed by flight testing and was subsequently eliminated by introducing control-surface damping about the rolleron hinge line.