Technical report describing the tests on types 309, 316, and 347 stainless steel. These steels were tested for a total of 779 to 828 hours in three different synthetic waste solutions. Results shoe that the best all-around corrosion resistance to the test conditions was exhibited by 316 stainless steel, but in one solution 347 stainless steel was more resistant. [From Abstract]

Six structural materials (aluminum 2S, aluminum 72S, copper, iron, steel, lead and bismuth) were irradiated for about 100 kilowatt hours in the center of the Argonne pile. The alpha and gamma decays were then followed for 130 days on Geiger counters and are presented here graphically as number of rays per minute per gram per kilowatt hour vs. time of decay. A quantitative interpretation of the gamma-ray decay curves gave fair agreement with the chemical analysis of impurities found in the materials.

Report discussing an investigation of the DM-1 glider, which has an approximately triangular plan form, with auxiliary studies of a model of triangular wings. The pitching-moment coefficient, drag coefficient, and angle of attack with the lift coefficient are provided. Results indicated that the angles of descent without power are likely to be prohibitive and airplanes with the tested type of wings will not be able to land safely without power.

Memorandum presenting the effects of specimen-axis orientation with respect to forging direction on the true stress-strain curves and the fracturing characteristics at room temperature of forged and subsequently heat-treated billets of alloys 16-25-6, S-816, and Inconel X. Results regarding plastic properties and fracture properties are provided.

From Introduction: "The investigation reported herein, which was conducted in an NACA Lewis altitude test chamber, covered a range of altitudes from 30,000 to 50,000 feet at a flight Mach number of 0.8."

An investigation was conducted to determine the behavior of recently produced, forged S-816 turbine blades in a full-scale turbojet engine, and in particular, the scatter in performance of the alloy. The turbine blades were operated as continuously as possible at a temperature of 1500 degrees F and a centrifugal stress of 21,500 pounds per square inch. The operating lives of the turbine blades varied from 181 to 539 hours, a range of 358 hours. Stress-rupture properties of specimens cut from blade airfoils also varied considerably, as much as 1257 hours at 20,000 pounds per square inch and 1500 degrees F. Since the variability of scatter of stress-rupture data is greater than that of blade performance, the scatter is probably caused by variations in the properties of the forged blades rather than by variations caused by engine operation or installation of the blades. Metallographic examinations were made to determine possible causes of the scatter and although numerous differences in microstructures of blades were found, no consistent tendencies were observed and the findings did not permit an explanation of the scatter of blade performance. The results of the metallographic examinations and of the physical tests indirectly indicated variables in the fabricating method …

Report presenting an experimental investigation in the altitude test chamber on an axial-flow turbojet engine at transonic flight conditions to determine the magnitude of thrust augmentation and to ascertain the operational characteristics of a combined augmentation system. Results regarding the augmented engine performance, influence of coolant on afterburner combustion, performance losses, and operational problems are provided.

The adhesive and protective characteristics of National Bureau of Standards Coating A-417 were investigated, as well as the effect of the coating on the life of forged Refractaloy 26 and cast Stellite 21 turbine blades. Coated and uncoated blades were run in a full-scale J33-9 engine and were subjected to simulated service operations consisting of consecutive 20-minute cycles (15 min at rated speed and approximately 5 min at idle). The ceramic coating adhered well to Refractaloy 26 and Stellite 21 turbine blades operated at 1500 degrees F. The coating also prevented corrosion of the Refractaloy 26, a corrosion-sensitive nickel-base alloy, and of the Stellite 21, a relatively corrosion-resistant cobalt-base alloy. Although the coating prevented corrosion of both alloys, it had no apparent effect on blade life.

"An Army liaison-type airplane, representative of personal airplanes in the 150 to 200 horsepower class, has been modified to reduce propeller and engine noise according to known principles of airplane-noise reduction. Noise-level measurements demonstrate that, with reference to an observer on the ground, a noisy airplane of this class can be made quiet -- perhaps more quiet than necessary. In order to avoid extreme and unnecessary modifications, acceptable noise levels must be determined" (p. 115).

Report presenting an investigation to determine the effect of several chord-extension configurations at low speed on a variable-sweep airplane model with a partially cambered wing. Testing occurred at a designated Reynolds number based on the mean aerodynamic chord of the wing at 50 degrees sweep for average test conditions. Results regarding the effect of chord extensions at 50 degrees, 60 degrees, and 20 degrees sweep, effect of chord extensions on lateral stability, and a comparison with different wing modifications are provided.

Abstract: "A fast, linear air-ionization chamber has been developed for integrating and monitoring external heavy-particle beams. It consists of a thin-windowed air chamber in which the beam ionization light is viewed by a photomultiplier whose output is fed directly to a standard electrometer."

This report analyzes the stability and feasibility of a reflector-control system for a boiling heterogeneous reactor.

Basis: "It is desired to test the effect of neutron flux on the creep rate of zirconium. These data will greatly add to the metallurgical information needed for design specifications of reactor components utilizing this metal."

Abstract: "Methods for recovering radium from K-65 residue have been investigated. A process using Versene was developed and demonstrated on a laboratory scale. In this process K-65 residue is leached with Versene solution and radium is adsorbed from the leach liquors and purified by the use of cation exchange resin."

Operating plant experiences in restoring to useful service failed equipment contaminated through exposures to radioactive processes is of international interest to the nuclear industry. In accordance with a request from the Hanford Operations Office of the United States Atomic Energy Commission this report of the various measures taken in rehabilitating for re-use expensive engineered equipment has been compiled by the General Electric Company. This report is a review and summary of the disposition of contaminated major processing equipment at Hanford Atomic Products Operation during 1958-1959 and a listing of 1) equipment buried, 2) equipment stored, to be buried or decontaminated, and 3) equipment decontaminated and returned to service.

The mathematics of the approximation is developed for the case of a H2O-cooled, graphite-moderated matrix

Report issued by the Oak Ridge National Laboratory discussing semiannual progress made by the Physics Division. Descriptions of progress and studies conducted are presented. This report includes tables, and illustrations.

Report issued by the Oak Ridge National Laboratory discussing progress made by the Stable Isotopes Division. Descriptions of of the progress and studies made are presented. This report includes tables, illustrations, and photographs.

Report discussing important elements of thermometer design. Factors affecting the use of common types of liquid-in-glass thermometers are included together with tables of tolerances and reasonably attainable accuracies. The calculation of corrections for the temperature of the emergent stem is given in detail for various types of thermometers and conditions of use.

"An investigation was made in the 7 by 10-foot wind tunnel and in the variable-density wind tunnel of the NACA 23012 airfoil with various slotted-flap arrangements. The purpose of the investigation in the 7 by 10-foot wind tunnel was to determine the airfoil section aerodynamic characteristics as affected by flap shape, slot shape, and flap location. The flap position for maximum lift; polars for arrangements favorable for take-off and climb; and complete lift, drag, and pitching-moment characteristics for selected optimum arrangements were determined" (p. 1).

Rim cracking in turbine wheels with welded blades was evaluated. The problem is explained on the basis of the occurrence of plastic flow in the rim during transient starting conditions when thermal compressive stresses resulting from high-temperature gradients exceed the proportional elastic limit of the material.

"A flight investigation of the spinning of the F4B-2 single-seat fighter airplane was made for the purpose of finding modifications that would eliminate dangerous spin tendencies exhibited by this type of airplane in service. The effects on steady spins and on recoveries of changing the loading, enlarging the fin areas, changing the elevator plan form, and raising the horizontal surfaces, were determined" (p. 413).

Technical report describing and comparing drilling methods.

Lewis in 1929 determined the thermal conductivity of beryllium metal for the first time. The next measurement reported in the open literature on the thermal conductivity of beryllium was by Powell in 1953. Measurements were also made by Grenell, Linebrink, and Johnson at Battelle Memorial Institute in 1947. Their values are in good agreement with those of Powell.