The following report describes the process of epoxy resin casting of high-voltage transformers, bushings, and potheads.

Abstract: This report gives a general description of the single stage axial compressor blade test facility located at the Oak Ridge Gaseous Diffusion Plant, Oak Ridge, Tennessee.

Report presenting a flight program using the Northrop X-4 semitailless airplane to investigate the effect on the longitudinal and lateral stability and control of thickened elevons with trailing-edge thickness one-half the control-hinge-station thickness. The investigation consisted of speed runs, wind-up turns, abrupt rudder-fixed rolls, and longitudinal pulses between a range of Mach numbers.

"An evaluation is made of the existing theories of a linearized tire motion and wheel shimmy. It is demonstrated that most of the previously published theories represent varying degrees of approximation to a summary theory developed in this report which is a minor modification of the basic theory of Von Schlippe and Dietrich. In most cases where strong differences exist between the previously published theories and summary theory, the previously published theories are shown to possess certain deficiencies" (p. 139).

Report on an investigation to determine the erect and inverted spin and recovery characteristics of a model of the North American FJ-4 airplane. The testing found that either a flat-type of steep-type spin may be obtained when the airplane is spinning erect. The optimum recovery technique from inverted spins was full rudder reversal with simultaneous movement of the ailerons to full with the stick maintained full forward.

Report presenting measurements of the velocity distributions at the outlet of a large number of duct elbows of round and elliptical as well as square and rectangular cross section at a range of Reynolds numbers. Special investigations include measurements of the decay of velocity patterns produced by curved ducts and the effect of asymmetrical upstream velocity distributions. Results regarding typical distributions, tabulation of principal results, and special investigations are provided.

Memorandum presenting a five-stage rocket-propelled model flown up to a Mach number of 10.9 and a corresponding free-stream Reynolds number of 6.57 x 10(exp 6) based on nose diameter. Temperatures were measured at 16 stations on the inside of a flat-faced cylinder made of copper. Results regarding the flight test, wall temperatures, heat-transfer data, measurement repeatibility and effects of angle of attack, comparison of measured and theoretical stagnation-point heating rates, and measured and theoretical heating rates over the front and side of the nose are provided.

Report presenting an investigation to obtain a survey of the flying characteristics at low speeds of models with low-aspect-ratio delta wings. Four models with triangular plan-form sweptback wings and five models with the tips cut off to give taper ratios were tested. Results regarding the stability and control characteristics of each of the models is provided.

Report presenting an investigation of the characteristics of three representative NACA 1-series nose inlets over a Mach number range extending from 0.4 to 0.925 in the high-speed wind tunnel. Results regarding pressure distribution, drag, and some potential design considerations are provided.

Investigation of the internal performance characteristics of several jet-exit configurations over a wide range of pressure ratios, which are summarized to provide an overall picture of jet-exit performance. The configurations investigated include a convergent nozzle, fixed convergent-divergent nozzles, an adjustable plug-type convergent-divergent nozzle, and jet ejectors. Results regarding the performance of several jet-exit configurations and matching adjustable jet exits to supersonic aircraft are provided.

Report presenting the development of an annular combustor by utilizing the design principles evolved in previous investigations and by making 12 design changes to optimize the altitude performance of the combustor. Three types of fuels were used and the combustion efficiency, pressure losses, and outlet temperature profiles were evaluated.

Report presenting an investigation of the low-speed stability and control characteristics of a scale model of the proposed MX-1554A design. It employs a triangular wing and triangular stabilizing surfaces. Results regarding the effect of wing incidence, tail position, fences, and chord extensions on the longitudinal characteristics are provided.

Report presenting pressure distributions calculated for some symmetrical wing-body combinations at zero lift. Of particular interest is the effect of indenting the body on the distribution of pressure over the wing.

Report presenting the longitudinal stability characteristics of the Convair XF-92A delta-wing airplane in maneuvering flight. The investigation included the determination of the characteristics of the basic airplane and the effects of two wing fence configurations on the characteristics.

Report presenting dynamic longitudinal maneuvers over a range of Mach numbers at an altitude of 30,000 feet by utilizing the XF-92A delta-wing research airplane. An analysis of the dynamic responses was made with three approaches: measured period and time to damp, analogue computer simulation of the airplane time-response characteristics, and Fourier transformation. Results regarding period, time and cycles to damp, and stability derivatives with Mach number are provided.

Report presenting flight measurements of the elevon hinge moments on the Convair XF-92A delta-wing airplane over a range of Mach numbers during longitudinal elevon pulses, aileron rolls, and wind-up turns. During wind-up turns, the hinge moments become nonlinear at about the angle of attack at which the airplane experiences a marked decrease in longitudinal stability.

"The field of a uniformly loaded wing in subsonic flow is discussed in terms of the acceleration potential. It is shown that, for the design of such wings, the slope of the mean camber surface at any point can be determined by a line integration around the wing boundary. By an additional line integration around the wing boundary, this method is extended to include the case where the local section lift coefficient varies with spanwise location (the chordwise loading at every section still remaining uniform)" (p. 471).

"Design work was completed and construction initiated on a prototype field altimeter based on the gas density dependence of Townsend discharge current in an electrical discharge. The design of an ion tracer air velocity meter for laboratory applications, and construction of three units were successfully completed. Theoretical and experimental support is presented, showing the applicability of the ion tracer system to the accurate measurement of linear gas velocity. The operating range of the laboratory meter is 150 to 2500 ft/min at ambient pressures between 200 mu and 30.0 mm Hg. Further investigations on the application of the ion tracer concept to flowrate measurements are presented. By generating velocity profile curves with an ion tracer calibrated thermoanemometer, it was possible to determine the flowrate for 2 flow and pressure conditions; 37.5 cfm at 19.6 mm and 75 cfm at 9.8 mm Hg. Comparison with a calibrated Rotameter technique was within 5% in both cases. Also presented are some preliminary investigations leading to the development of a generalized ion tracer flowmeter for low gas densities. Results of some supplemental electrical discharge experiments in rarefied atmospheres are described. It was observed that electrical oscillations could be produced in a low density gas discharge, …

Considerable work has been done on decontamination procedures for both corrosion products and fission products. Testing of promising procedures under typical rupture conditions is an important phase of this work. The Irradiated Rupture Prototype (IRP) has been used since August in this evaluation work. This document is one of a series reporting these data.

The biological evaluation of the thermal neutron capture reaction of boron-10, B10 (n,α)Li7 + 2.786 MeV, has previously been studied, using different particles from the boron-10 thermal neutron capture reaction compared with 250 kvp x-rays has been reported as 1.05 for spleen-thymic weight reduction (1), as 1.5 to 2.0 for skin lesions in pigs (2), and 1.87 for skin lesions of the rabbit's ear (3). The significance of such a calculation is felt to be unreliable for the boron-10 reaction in animals because of the vagaries of dose determination resulting from irregular boron distribution, and by the presence of an adventitious irradiation from fast neutrons and capture gammas that is inadequately determined at present. Our present experiment attempts to circumvent the difficulties attendent to studies of the boron-10 reaction in animals by comparing the effect of this reaction on the proliferative capacity of HeLa cells with those produced with 250 kvp x-ray.

In these lectures we will discuss some examples of information about magnetic properties of solids which can be obtained by neutron scattering. We consider a scattering process in which a neutron with wave vector k and spin σ is incident upon a solid in state q>. (Here q stands for all of the quantum numbers which describe the state of the solid, such as spin and orbital electronic states, phonon numbers, etc.) After interacting with the solid, the neutron goes off with wave-vector k' and spin σ', leaving the solid in state q'>. In performing an experiment of this sort one does not usually observe the initial and final spin states of the neutron or the initial and final states of the solid. We must then sum over all possible final states and average over all initial states.

The present core of the Brookhaven Graphite Reactor consists of some 4900 highly enriched uranium fuel loaded in 615 horizontal fuel channels passing through a 25 foot cube of graphite moderator and reflector. The core is divided into two halves (north and south) by an 8 cm. wide vertical gap in the center of the graphite. The cooling air enters the reactor through inlet filters, at the rate of 270,000 CFM, passes into the central gap and flows bi-directionally through the north and south halves of the core. It then enters the collecting plenums and flows into the north and south ducts. The air is first monitored by the north and south exit air monitors located within the pile building. These are moving filter tape monitors with beta scintillation detectors. They are essentially operational monitors and are maintained by reactor operations. They are essentially operational monitors and are maintained by a reactor operations. The air then passes through the exit air filters, heat exchanger, venturi and on to the fan house where the north and south ducts join. After the fan house the air is monitored by Argon-41 by a Kanne ion chamber syste.

Boron-10 has a high thermal neutron capture cross section (3880 barns). Following neutron capture, the subsequent nuclear disintegration produces an alpha particle and a lithium-7 nucleus with the release of an average of 2.34 MeV for the particle irradiation, and in 93% of the reactions there is also the emission of an 0.48 MeV gamma ray: [equation not transcribed]. The kinetic energy is divided between the lithium-7 nucleus and the alpha particle giving the equal and opposite momentums with a range in tissue of about 8-14μ or approximately 1 cell diameter (1). This fact and the reported favorable partition of boron between tumor and the normal brain suggested a possible therapeutic usefulness which has been investigated clinically. The object of our study is to document the biological effects of the B10 (n,α) Li7 reaction on the brain of dogs injected with boron-10 30 minutes prior to irradiation with thermal neutrons. For this, we felt it desirable to estimate a dose for the boron-10 reaction which if exceeded, produces destruction of normal tissue. This dose could then be a reference dose to be utilized as a maximal limit for the irradiation of normal tissue. We have assured that the largest fluence …

A part of the development activities of the Process Equipment Development Group, Chemical Development, HLO through the year 1959 has consisted of test evaluation of some of the never products of manufacturers, design and refinement of novel units to do certain specialized jobs and development of improved components for existing plant equipment. Modification of present chemical processing methods and investigation of new basic procedures have made it necessary to utilize different and "exotic" materials, titanium, has given rise to another problem-- that of the selection of adequate and compatible bearings where the titanium is used as moving or rotating part.