This report covers a study of the deformation characteristics of uranium in grooved rolls. The study's purpose was to provide a basis for possible improvements in the uniformity of the rolled rod produced for the Hanford and Savannah River reactors.

This report follows work performed to determine the effects of large boron additions on the fabricability and room-temperature tensile properties of various steels for reactor shielding.

This report analyzes two high-current linear accelerators, the A-54--a 48.5 megacycle resonant cavity accelerator--and the A-48, that is under construction during the time this report is written.

The following report provides results from investigations of torsional vibration stresses in the drive shafts of two Westinghouse motor generator sets in 1952.

This document presents a summary of work and progress at the Hanford Engineer Works for August 1955. The report is divided into sections by department. A plant wide general summary is included at the beginning of the report, after which the departmental summaries begin. The Manufacturing Department reports plant statistics, and summaries for the Metal Preparation, Reactor and Separation sections. The Engineering Department`s section summarizes work for the Technical, Design, and Project Sections. Costs for the various departments are presented in the Financial Department`s summary. The Medical, Radiological Sciences, Utilities and General Sciences, Employee and Public Relations, and Community Real Estate and Services departments have sections presenting their monthly statistics, work, progress, and summaries.

The APPR-I is described and the various hazards are reviewed. Because of the reactor's location near the nation's Capitol, containment is of the utmost importance. The maximum energy release in any possible accident is 7.4 million Btu's which is completely contained within a 7/8 inch thick steel cylindrical shell with hemispherical ends. The vapor container is 60 ft high and 32 ft in diameter and is lined on the inside with 2 ft of reinforced concrete which provides missile protection and is part of the secondary shield. All possible nuclear excursions are reviewed and the energy from any of these is insignificant compared to the stored energy in the water. The maximum credible accident is caused hy the reactor running constantly at its maximum power of 10 Mw and through an extremely unlikely sequence of failures, causing the temperature of the water in the primary and secondary systeras to rise to saturation; whereupon a rupture occurs releasing the stored energy of 7.4 million Btu's into the vapor container. If the reactor core melts during the incident, a maximum of 10/sup 8/ curies of activity is released. While it appears impossible for a rupture of the vapor container to oecur except …

This memorandum provides an estimate of the uranium requirements for the third and fourth quarters of calendar year 1955.

This document presents a summary of work and progress at the Hanford Engineer Works for September 1955. The report is divided into sections by department. A plant wide general summary is included at the beginning of the report, after which the departmental summaries begin. The Manufacturing Department reports plant statistics, and summaries for the Metal Preparation, Reactor and Separation sections. The Engineering Department`s section summarizes work for the Technical, Design, and Project Sections. Costs for the various departments are presented in the Financial Department`s summary. The Medical, Radiological Sciences, Utilities and General Services, Employee and Public Relations, and Community Real Estate and Services departments have sections presenting their monthly statistics, work, progress, and summaries.

Report of the daily cash position for Sugarland State Bank.

"Some aileron load characteristics for three thin wings varying in sweep have been presented for Mach numbers from 0.80 to 1.05. For the transonic Mach number range, shock effects exert a large influence on the loading, but the exact location of each shock for a specific wing design cannot be cataloged at the present time. It is shown, however, that the aileron loading, although greater in magnitude than at subsonic speeds, nevertheless varies in as uniform a fashion as at subsonic speeds" (p. 1).

Report presenting an investigation in the supersonic pressure tunnel at Mach number 2.01 to study the wake patterns in the lee of bodies at high angles of attack. The configurations tested consisted of two cylindrical body shapes, one circular and one elliptical in cross section, with a fineness-ratio-3.5 ogival nose and a fineness-ratio-6 conical nose. Results regarding vapor-screen photographs, wake characteristics, wake patterns, wake characteristics, and testing with transition strips are included.

Report presenting a determination of the landing contact conditions of the Boeing B-47 airplane using a specially built motion picture camera. A statistical analysis of the sinking speeds and horizontal speeds was carried out on the photographs.

Report presenting an investigation to determine the possibility of using simplified procedures for the estimation of control loads at supersonic speeds. The results indicated that relatively simple procedures are possible for the estimation of loadings on flap-type controls at supersonic speeds for cases when no flow separation occurs ahead of the hinge line.

Report presenting a wind-tunnel investigation at subsonic Mach numbers up to 0.9 to measure the root-mean-square variation of the normal forces on 27 NACA airfoil sections. The effects of thickness-chord ratio, camber, location of minimum pressure, and leading-edge radius were investigated.

"An investigation to determine the static longitudinal and lateral stability characteristics of a 1/62-scale model of the Bell X-1A has been conducted in the Langley 9-inch supersonic tunnel. tests were made at Mach numbers of 1.62, 1.94, 2.22, 2.40, and 2.62 on the wing-body, wing-body-vertical-tail, and complete configurations. Data are presented for both the body and stability axes. Detailed analysis of the test results is omitted" (p. 1).

Report discussing an investigation of the performance of a three-stage transonic compressor with high stage pressure ratios to investigate problems encountered when high-pressure-ratio transonic stages are grouped together to form a multistage compressor. Results are presented regarding overall performance in Freon, stage performance, and radial variation in overall stagnation pressure ratio.

Memorandum presenting a theoretical analysis of a cruciform missile configuration equipped with floating controls to determine if such controls can be utilized to improve the airframe transient response characteristics.The investigation covers either forward or aft locations of the floating controls at supersonic speeds. The results indicate that a substantial increase in airframe damping can be obtained through a proper selection of hinge-moment coefficients and through the use of a fixed-rate viscous damper attached to the floating-control surfaces.

Report presenting the aerodynamic loads acting over the vertical tail, which were determined during an investigation of the lateral stability and control characteristics of the Convair XF-92A. Results regarding the vertical-tail panel characteristics, vertical-tail load parameters, and vertical-tail bending and normal-force coefficients are provided.

Report presenting the status of oscillating air forces, including forces, moments, and their respective phase angles for a 45 degree swept wing of aspect ratio 2 and for two bodies of revolution. Derivatives based on available analyses were also demonstrated for those three configurations.

Report presenting an investigation to determine the reverse-thrust performance of hemispherical target-type thrust reversers over a wide range of geometric variables. Several factors were found that increased the flow turn angle and reverse-thrust ratio, primarily the hemisphere diameter. Results regarding operating characteristics, relation of flow turn angle and reverse-thrust ratio, reverse-flow velocities and pressures along boattail, effect of boattail shape on reverse-thrust ratio, and modifications to hemispherical thrust reverser are provided.

"The flow-field characteristics around a swept-wing airplane model at low subsonic speed are described, and the loads induced on a typical missile model while operating within these flow fields are presented. In addition, theoretical flow fields are compared with experiment and are used in first-order estimations of the resulting induced missile loads" (p. 1).

Memorandum presenting an investigation of a low-speed leading-edge chord extension in the 19-foot pressure tunnel. Chord-extensions of various geometric designs were tested on three 45 degree sweptback wings of aspect ratio 5 and taper ratio 0.28 incorporating different airfoil sections. The data indicated that leading-edge chord-extensions could be used to produce large reductions in the longitudinal instability of all three wings tested.

Report discussing testing of a Hughes Falcon missile, C configuration, to determine the stability and control characteristics of the missile while rolling. Information about the time histories, normal force due to angle of attack, pitching moment due to angle of attack, damping, and control effectiveness is provided.

Report presenting the effects of inlet-air-flow distortion on the steady-state performance of a current axial-flow turbojet engine studied in an NACA altitude test chamber at a range of altitudes and simulated Mach number of 0.8. Radial distortions of various shapes up to 22 percent of the average engine-inlet total pressure and circumferential distortions up to 26 percent were imposed. Results regarding propagation through the engine, compressor-interstage performance and stall, effects on component performance, effects on overall engine performance, and effect on compressor blade vibration are provided.