The following report focuses on research made to determine whether the service performance of UO₂ fuel-elements cores for the PWR can be improved by certain ceramic or metal additions.

Thesis discussing the study of deuterons produced at wide angles to a beam of 300 Mev neutrons and a beam of 300 Mev protons. It was observed that the deuterons are formed by "a two step process in which the incident nucleon, or its collision partner, is scattered and then picks up in the same nucleus." Some tritons are also observed, and it is thought that they are formed by the same process as the deuterons. From these findings, the author concludes that "for heavy nuclei, there is a nuclear skin rich in neutrons."

Translating spike inlet air flow regulation characteristics from transonic to supersonic speeds at zero angle of attack.

"An investigation has been made in the NACA Lewis icing research tunnel to determine the aerodynamic and icing characteristics of a full-scale induction-system air-scoop assembly incorporating a flush alternate inlet. The flush inlet was located immediately downstream of the offset ram inlet and included a 180 deg reversal and a 90 deg elbow in the ducting between inlet and carburetor top deck. The model also had a preheat-air inlet" (p. 1).

From Summary: "In an effort to increase the operational range of existing small icing tunnels, the use of truncated airfoil sections has been suggested. With truncated airfoils, large-scale or even full-scale wing-icing-protection systems could be evaluated. Therefore, experimental studies were conducted in the NACA Lewis laboratory icing tunnel with an NACA 651-212 airfoil section to determine the effect of truncating the airfoil chord on velocity distribution and impingement characteristics. A 6-foot-chord airfoil was cut successively at the 50- and 30-percent-chord stations to produce the truncated airfoil sections, which were equipped with trailing-edge flaps that were used to alter the flow field about the truncated sections. The study was conducted at geometric angles of attack of 00 and 40, an airspeed of about 156 knots, and volume-median droplet sizes of 11.5 and 18.6 microns. A dye-tracer technique was used in the impingement studies."

Memorandum presenting an investigation conducted in the 20-foot free-spinning tunnel on a 1/20-scale model of the McDonnell F2H-3 airplane. The effects of control settings and movement on the erect spin and recovery characteristics of the model were determined for the take-off condition and for the condition with full wing-tip fuel tanks installed.

Memorandum presenting an investigation in the icing research tunnel to determine the aerodynamic and icing characteristics of a full-scale induction-system air-scoop assembly incorporating a flush alternate inlet. Results regarding the ram-inlet tests, alternate-inlet tests, and preheat-air tests are provided.

"The methods of characteristics has been linearized by assuming that the flow field can be represented as a basic flow field determined by nonlinearized methods and a linearized superposed flow field that accounts for small changes of boundary conditions. The method has been applied to two-dimensional rotational flow where the basic flow is potential flow and to axially symmetric problems where conical flows have been used as the basic flows. In both cases the method allows the determination of the flow field to be simplified and the numerical work to be reduced to a few calculations. The calculations of axially symmetric flow can be simplified if tabulated values of some coefficients of the conical flow are obtained" (p. 933).

The results of a parametric study on a gas cooled reactor are reported on herein. The system considered was a helium cooled, UO2 fueled arrangement with the fuel assemblies consisting of clusters of long cylindrical elements, each element covered b a stainless steel jacket. The axial power distribution was assumed to be a "chopped cosine" having an axial peak-to-average power 1.32.

Report discussing the progress of various research projects by members of the Mathematics Panel at Oak Ridge National Laboratory for the quarter ending April 30, 1952.

Report discussing about 400 references pertaining to the hydrodynamic design of seaplanes have been compiled, and the information is presented in the form of abstracts classified under six main headings.

Combustion in a spark-ignition engine was investigated by means of the NACA high-speed motion-picture cameras. This camera is operated at a speed of 40,000 photographs a second and therefore makes possible the study of changes that take place in the intervals as short as 0.000025 second. When the motion pictures are projected at the normal speed of 16 frames a second, any rate of movement shown is slowed down 2500 times. Photographs are presented of normal combustion, of combustion from preignitions, and of knock both with and without preignition. The photographs of combustion show that knock may be preceded by a period of exothermic reaction in the end zone that persists for a time interval of as much as 0.0006 second. The knock takes place in 0.00005 second or less.

From Summary: "For a number of years now, experimenters have been making measurements of skin friction. Formerly, the main interest was at low Mach numbers; later, measurements were made at supersonic Mach numbers. However, almost all of these measurements were over a limited range of Reynolds numbers. On the other hand, these measurements fairly well determined the effects of Mach number and heat transfer on skin friction. The purpose of this paper is to give the results of skin-friction measurements in turbulent boundary layers at high Mach numbers and high Reynolds numbers where data have not previously existed."

"A supplementary investigation has been conducted in the Langley 20-foot free-spinning tunnel of a 1/30 -scale model of the Grumman XF10F-1 airplane to determine what effect full-span slats would have on the spin-recovery characteristics of the swept-wing version of the XF10F-1 airplane, which had previously been indicated as possessing undesirable spin-recovery characteristics without slats. The effects of extended nose-wheel doors and of fairing the air-duct inlets were also determined" (p. 1).

This report is a summary of work done for system development on the NPR ball safety backup for the horizontal rods. This phase of the system development is limited to discussion of the horizontal rod counting circuitry utilizing a direct current bridge network.

This document presents preliminary chemical flowsheets for cladding and core dissolution of zircaloy-clad uranium dioxide and stainless steel-clad uranium-molybdenum non-production fuels. These preliminary flowsheets together with existing process flowsheets should be adequate for process development in the currently forecast non-production fuels dissolution facility.

A "particle" of charge Ze moves with velocity v, mass M, energy [formula], through a "substance" of atomic number Zo, density N atoms/cm3. We have to consider the process of slowing down, and the nature of the trail of ions produced. Very slow particles are of little interest, as their range is very short. If Z is large, or if the particle is an electron, there are complications which we postpone. Thus, our considerations will apply particularly to protons, deuterons, o< -particles, and mesons.