Optical microscopic examination of air- and rain-borne dust shows most of the particles to be less than one micron in diameter. Electron microscopic examination of the same dust shows predominantly clusters of particles whose individual diameters are in the range 200 to 1000 A. The residue obtained by filtering rain water through a millipore filter is found to be slightly radioactive in more than half the cases observed.

Abstract: "This report describes a flame photometric system which continuously monitors a process water stream for ppm quantities of alkali metals, and automatically diverts the stream when the contamination exceeds a pre-determined level."

From introduction: "This report describes the second phase of the work on the application of protective coatings to uranium by vapor deposition to reduce or prevent its corrosion by water."

Abstract: "The shock-tube experiments of Professor R. G. Fowler and his co-workers at the University of Oklahoma, and of Professor Arthur Kantrowits and his group at Cornell University, are reported by the author, who visited the laboratories of the two groups. Fowler's group has studied expanding low-pressure sparks; Kantrowits and his group have studied shocks produced by the adiabatic expansion of a compressed gas."

Since 105-C Pile was designed without thimbles, gas seals are required on all horizontal control rods to prevent the pile gases from escaping and contaminating the atmosphere.

Subjects discussed include uranium structure, stability under irradiation, cold working of surfaces, deformation, hollow slugs, grain size, canning, etc.

A program to develop a new fuel element was initiated at Hanford in 1951. A survey of the possible methods of making such a fuel element was completed and a document listing all possible lines of research was written. The problem was outlined as it appeared at that time; various developments which have occurred subsequently have changed this problem to a greater or lesser extent. Essentially the problem concerned the development of a fuel element which would not fail or would fail in a slow and predictable manner and would not cause damage to the pile. A largenportion of the research and development was concerned with the application of these layers. This paper will review the research that was done on the development of these corrosion-resistant layers and will evaluate the problem as it appears now after approximately four years have elapsed.

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This document presents a summary of work and progress at the Hanford Engineer Works for March 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.

The Ferrotherm Company is undertaking a design study of a test radiator. Since January 21, 1955, preliminary designs of several radiators have been completed prior to the selection of one for the final design study. Ferrotherm has been given prototype design specifications for structural design, typical in-flight prototype performance specifications for core-size estimates, test core specifications for their design study, and a method whereby radiators may be evaluated. From analysis of the prototype specifications a matrix will be selected for the test core design study. Although the analysis has narrowed to both a plate-and-sheet-metal fin and a plate-and-pin-fin core geometry, Ferrotherm is more or less committed to pin-fins.

In April, 1954, Thompson Products Inc. formally began work on a program leading to the fabrication of two test radiators. The work done to date is summarized in report number PWAC-127, First Technical Report by Thompson Products Inc. on Liquid-Metal-to-Air Radiators and in PWAC-128, Second Technical Report by Thompson Products Inc. on Liquid-Metal-to-Air Radiators. The first report describes possible radiator design concepts meeting the required specifications and presents an analytical method which was derived to optimize the designs. Thompson Products has decided that a core with cast NaK passages in combination with the sheet-metal, ribbon fins on the airside offers maximum reliability. The second report formulates the analysis of the final radiator design and presents the fabrication and evaluation studies used to select the design. To evaluate the permeability of cast NaK passages, Thompson Products is planning to build a hot NaK flow rig. A parallel investigation on wrought materials will be carried out as an alternate NaK passage type. The next phase of the program, the final design of the test radiator, has started.

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Report presenting a consideration of the problem of shaping an adjoining fuselage for a given wing and supersonic Mach number so that the combination will have a low wave drag. Only fuselages that can be simulated by singularities distributed along the body axis are studied.

"Aerodynamic data have been obtained for a fuselage forebody alone and for canopy-body configurations consisting of four different canopies mounted on a fuselage forebody. Two of the canopies had the same shape and size rearward of the windshield but one had a "flat" and the other a "vee" windshield. The remaining two canopies were located at different body stations and were geometrically similar. The data indicated that the drag of the flat-windshield model was consistently lower than that of the vee-windshield model" (p. 1).

Memorandum presenting experimental flutter Mach numbers for several solid, thin, rectangular cantilever wings with uniform section properties, low aspect ratio, and high relative density estimated from the results of previous tests at zero angle of attack. The experimental values are considered estimates, rather than determinations, in the high subsonic speed range because in that range the amplitude criterion was necessarily arbitrary. Results regarding conservatism of standard analysis relative to the experiment, closeness of analytical and experimental results, and interpretation of the analytical and experimental uncertainties are provided.

From Introduction: "The investigation reported herein was initiated to define further the effects on the aerodynamic characteristics and load distribution of a thin, sweptback wing of a low-pressure blowing system and also to provide information on which to base a more thorough study of a complete airplane configuration."

Report presenting an investigation of a turbojet engine with variable inlet guide vanes in an altitude test facility to determine the steady-state compressor performance and surge characteristics. Compressor surge pressure ratios were found to be unaffected by changes in flight condition for either position of the inlet guide vanes. Decreasing the inlet Reynolds number was found to reduce the corrected fuel flow required for compressor surge.

Report presents an approximate subsonic theory for the solid-blockage interference in circular wind tunnels with walls slotted in the direction of flow. This theory indicated the possibility of obtaining zero blockage interference. Tests in a circular slotted tunnel based on the theory confirmed the theoretical predictions.

From Summary: "Hydrodynamic characteristics have been determined for a 1/13.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat with the forebody modified so as to increase the depth of step and the angle between the forebody and afterbody keels. Longitudinal stability during takeoff and landing in smooth water and resistance of the complete model in smooth water and in waves are presented."

Memorandum presenting an investigation of a flight version of the NACA heated-wire liquid-water-content instrument, which was constructed and flight tested in natural icing conditions. Data obtained simultaneously with rotting multicylinders indicated that reliable flight measurements of liquid-water content could be made with the heated-wire instrument.