A large number of ``hot spot`` slug failures characterized by intergranular corrosion of the aluminum can have occurred in the past year. The cause of this type of failure may be vertical displacement of one or more slugs in the slug columns. To determine if such displacement may reasonably be expected and to determine the cause and cure of the displacement a set of experiments have been performed in the 189-D laboratory. This document presents data which has been thus far collected. (1) Slugs which are cocked in a process tube are cause for severe-column bowing. Bowing is most severe when the cocked slug is in the downstream portion of the tube. Stopping flow will not realign bowed slugs. (2) Flow seating a slug column can cause slugs to cock and cocked slugs remain cocked even when backseated and the water flow is stopped. (3) When all slugs have undamaged ends and are well aligned with the tube ribs as well as fully seated against the rear nozzle insert, only minor bowing will occur, even when the upstream end of the slug column is restrained. (4) Anodized pieces behave erratically and in an unexplained manner. (5) Flows as much as …

Reactivity measurements have been made in the Hanford Test Pile, comparing the one-piece I&E slug and the wafer I&E slug with the standard solid slug (1.336 inch uranium diameter). The results of these measurements, made by the Experimental Physics Unit of Pile Engineering, are summarized in this report.

In April of 1955 the Radiation Laboratory of the University of California sent out to 18 high schools in the Bay Area letters which said, in part, 'The object of this program is to help science teachers achieve some practical knowledge and experience in nuclear science by working with some of our basic research groups in physics and chemistry. In this way we believe that we can assist these teachers in their efforts to make their students more aware of the nature of atomic energy and help to prepare them for the impact of atomic energy in their future.'

This paper constitutes a review of the experimental events that led our laboratory to focus its attention on thioctic acid, a discussion of some of the purely chemical and physical properties of thioctic acid that this awakened interest prompted us to investigate, and a brief description of some of our recent biological investigations with thioctic acid.

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Report presenting a brief series of airplane-wing aerodynamic-noise and boundary-layer-profile measurements made in flight as part of an extended investigation of boundary-layer noise. Results regarding the boundary layer data and ratio of root-mean-square sound pressure to the dynamic pressure are provided.

Memorandum presenting an investigation of an airplane model to determine the effect of area suction trailing-edge flaps and several leading-edge modifications on the aerodynamic characteristics of a 45 degree sweptback wing. The wing had an aspect ratio of 2.8 and a taper ratio of 0.17.

Report presenting an investigation in a 16-inch-diameter simulated afterburner using gaseous hydrogen fuel. Results regarding combustion efficiency, afterburner pressure losses, spontaneous ignition, and a heat-balance check are provided.

Memorandum presenting an investigation of a number of short turbojet combustor configurations for hydrogen fuel in a quarter-annulus duct. The best combustor liner consisted of an annular primary zone and a secondary zone composed of T-shaped channels sloping from the primary zone to the combustor wall.

Report presenting an investigation to determine the effect of motion periodicity on the aerodynamic derivatives due to yawing velocity and yawing acceleration for a 60 degree delta wing, a 45 degree sweptback wing, and an unswept wing. Results were obtained from steady-state yawing-flow tests and tests of model performing pure sinusoidal yawing oscillations. Results regarding the static longitudinal characteristics, derivatives due to yawing velocity, and derivatives due to yawing acceleration are provided.

Report presenting an investigation utilizing a blowdown-type tunnel to determine the effects of a propulsive jet on a zero angle-of-attack wing surface located in the vicinity of both a choked convergent nozzle and a convergent-divergent nozzle. Static-pressure surveys were made on a flat surface located in the vicinity of the propulsive jet. Results regaridng the jet-off and jet-on pressure coefficients, shock waves, and incremental normal force are provided.

From Summary: "Removal of compression-surface boundary layer from the throat of a supersonic aft inlet is shown to increase the critical total-pressure recovery to values comparable to the better axisymmetric nose inlets. Throat bleed on two-dimensional and three-dimensional-type inlets by discrete slots or by porous plates has provided gains in critical recovery of as much as 7 percent at Mach number 2.0. A proper combination of bleed ahead of the inlet and at the inlet throat to control both fuselage and compression-surface boundary layer is shown to produce maximum values of propulsive thrust."

The present paper re-examines the derivation of the integral equations for transonic flow around slender wings and bodies of revolution, giving special attention to conditions resulting from the presence of shock waves and to the reduction of the relations to the special forms necessary for the discussion of sonic flow, that is, flow at free-stream Mach number 1.

Report presenting basic principles affecting the performance of side-inlet air-induction systems as well as an examination of the performance of several fuselage side inlets and a comparison with nose inlets. Methods for improving the performance of both types of inlets are reviewed.

Report presenting a study of the survey results obtained from two transonic turbines in an effort to gain an insight into the physical aspect of the flow. The results indicate that the flow characteristics through a single-stage turbine can be deduced by rotor-exit surveys. Results regarding momentum variation and actual total-pressure loss are provided.

Report discussing a study that investigates the use of small amounts of tracer elements placed in the fuel alloy of subassemblies in order to locate fuel-element failure. Details of experimental methods and materials are included as well as data that leads to the suggestion of further investigation.

A report about elevated-temperature tensile properties of dilute uranium alloys. Alloys up to 2 a/o aluminum and 4 a/o zirconium have been fabricated to rod and are being tested at temperatures up to 500 C.

A report about the mechanical properties of dilute uranium alloys which might be crucial to developing high strength alloys for possible use as fuel.

The purpose of this study was to develop and design a cutting torch which would slit aluminum tubes in a graphite matrix without damaging the graphite.

Measurement of radioactive carry-over was made on borax III operating at 300 psig and at power levels ranging from 4 to 14 mv. Decontamination factors of from 1.5 x 104 (at 14 mv) were obtained. These data are in essential agreement with those predicted by previous laboratory experimental work.

From Introduction: "This report also presents a method of optimizing the blade number and solidity for a given application if the blade loss variation with solidity can be estimated or experimentally determined. Also discussed are the penalties in performance that accompany deviations from optimum values of blade number and solidity."

From Summary: "An investigation was conducted in a 16-inch-diameter simulated afterburner using gaseous hydrogen fuel. No flameholder was used with a multipoint fuel injector. The burner length was varied from 9.5 to 38 inches. The afterburner-inlet conditions were: temperature of 1200 degrees or 1500 degrees F, pressure of 14 to 44 inches mercury absolute, and velocity of 300 to The measured combination efficiency ranged from 85 to 98 percent over an equivalence-ratio range of 0.2 to 1.0. The cold-flow pressure-drop coefficient was 1.0 for the system. Spontaneous ignition was always possible at temperatures above 1200 degrees F but was not possible at temperatures above 1200 degrees F but was not possible below 1100 degrees F for all pressures and velocities tested."

Data were calculated for equivalence ratios of 1 to 4, chamber pressures of 300 and 600 pounds per square inch absolute, and pressure ratios of 1 to 1500. Parameters included are specific impulse, combustion and exit temperatures, molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, and thermal conductivity. A correlation is given which permits determination of performance for a wide range of chamber pressures. A method for obtaining specific impulse of JP-4 fuel with OF2 and O3-F2 mixtures is given.

Report presenting an investigation of an airplane model conducted to determine the effect of area-suction trailing-edge flaps and several leading-edge modifications on the aerodynamic characteristics of a 45 degree sweptback wing. Results regarding the effect of trailing-edge flaps on the aerodynamic characteristics of the model with horizontal tail off, effect of wing modifications on the high-lift characteristics of the model with the horizontal tail off, aerodynamic characteristics of the model with the horizontal tail installed, and area-suction requirements are provided.