Report discussing the personal aspects involved in the research on transcurium elements at the Lawrence Radiation Laboratory, as well as a brief summary of previously unpublished work with heavy ions.

Memorandum presenting wind-tunnel testing of a jet-engine nacelle on a semispan wing with the leading edge swept back 37.25 degrees made to determine the effects of the nacelle on the aerodynamic characteristics of the wing. In comparison with the force characteristics of the wing alone, the addition of the nacelle to the wing in each position resulted in favorable interference on the maximum-lift and pitching-moment characteristics and in a small increase in drag.

Results are presented of tests up to a Mach number of 0.92 at altitudes around 30,000 feet. The data obtained show that the airplane can be flown to this Mach number above 30,000 feet. Longitudinal trim changes have been experienced but the forces involved have been small. The elevator effectiveness decreased about one-half with increase of Mach number from 0.70 to 0.87.

Report presenting pressure distributions of three triangular wing models: a wing-alone model, the same wing combined with a body, and a mock-up of a triangular-wing airplane. Results regarding the separation-vortex air flow over triangular wings, general comments regarding the applicability of the study, chordwise pressure distribution, section lift characteristics, center of pressure, and span load distribution are provided.

Report presenting measurements of the handling qualities of the Bell XS-1 transonic airplane using NACA instruments. Information regarding the stability and control characteristics and aerodynamic loads was obtained using two different airplanes in gliding and powered flight. Results regarding the longitudinal and lateral stability and control and stalling characteristics are provided.

A comparative evaluation was made for all-movable delta and flap-type controls on several wing plan forms. Comparison of these experimental results from various test facilities shows the effectiveness on various wing plan forms and an evaluation of hinge-moment characteristics of all-movable delta controls, swept trailing-edge flap, and straight trailing-edge flap-type controls.

"Pressure-distribution measurements were made during a lateral-control investigation of a semispan wing with the NACA 0012-64 section and a 20-percent-chord plain aileron. The results are presented as tables of pressure coefficients for Mach numbers from 0.60 to 0.85. No analysis of the results is included" (p. 1).

The interaction of the flow from one convergent and two convergent-divergent nozzles on parabolic afterbodies was studied at free-stream Mach numbers of 2.0, 1.6, and 0.6 over a range of jet pressure ratio. The influence of the jet on boattail and base drag was very pronounced. Study of the total external afterbody drag values at supersonic speeds indicated that, over most of the high-pressure-ratio range, increasing the nozzle design expansion ratio increased the drag even though the boattail area was reduced. Increasing the pressure ratio tended to increase slightly the total-drag increment caused by angle-of-attack operation.

From Summary: "Surveys were made through a turbulent boundary layer on a flat plate by means of a pitot probe, an x-ray densitometer, and hot-wire and cold-wire probes. Results from these surveys were analyzed to determine (a) the reliability of the basic data and hence the methods by which they were obtained, and (b) how well the actual distributions of properties in the boundary layer compare with those commonly assumed in semiempirical and theoretical analyses. All surveys were made at the same longitudinal station on the flat plate. The tests were conducted in a an 8- by 8-inch supersonic nozzle. The free-stream Mach number was 3.03 and the Reynolds number was approximately 210,000 based on boundary-layer thickness."

Abstract: "This is a selective bibliography of books and periodical articles relating to die design of hot presses. Sources consulted include: ASM Review of Metal Literature, 1950-1954; Chemical Abstracts, 1950-1055; Engineering Index, 1950-1055; Industrial Arts Index, 1950-March 1957; Metallurgical Abstracts, 1950-1953; Nuclear Science Abstracts, 1950-March 1957; Physics Abstracts, 1950-1955; the library card catalog, and the Technical Information Division AEC card catalog."

A memorandum report on test drilling of areas of anomalous radioactivity.

Abstract: This technical report describes the changes incurred in the SM-1 by the insertion of the SM-1 Core II without special components. The SM-1 Core II components were made to specifications very nearly identical to those of SM-1 Core I. The differences consist of europium absorber sections, internal europium flux suppressors in the control rod fuel elements, and low impurity cladding. Each of the SM-1 Core II components with the exception of the five absorber sections new in SM-1 Core I were subjected to a Zero Power Experiment at the Alco Critical Facility. The results of this experiment indicate that the SM-1 Core II will have nuclear characteristics very similar to that of the SM-1 Core I. Since SM-1 Core II will be operated with the same mode of rod control, in the same core support structure, and with the same primary coolant flow conditions, the thermal characteristics should be essentially identical to that of SM-1 Core I. Also, all kinetic characteristics of SM-1 Core II should be identical to those of SM-1 Core I. This report demonstrates that there is no increase in potential for a hazardous situation at SM-1 due to the replacement of SM-1 Core I by …

From introduction: "These data were taken on a 1/16th scale model of the magnet shown on sketch no. FS-2. The object of these measurements was to get information that would determine the final design of the full scale magnet. The one main point to be settled was whether a tapered or a cylindrical pole piece would give the largest value of Hρ for a given power input into the magnet (the cylindrical pole piece is shown in dotted lines in sketch FS-2)."

Report presenting a large number of measurements of natural environmental radiation in various parts of the United States using a 20-liter air filled polyethylene-walled ionization chamber at atmospheric pressure. The ionization current was measured with a vibrating reed electrometer connected as a continuously reading voltmeter driving a pen recorder" (p. 1).

From introduction: "In this paper the adaptation of the wax lab surface vibratory polisher is described. The wax lap requires little maintenance during the life of the lap. It is not necessary to remove any of the holding devices on the bowl to clean and recondition the lap. The bowl is merely washed out, recharged and placed in operation. The wax lap will not wrinkle or tear, nor is it necessary to change it each day such as the silk or nylon cloths."

Report presenting testing using a 1 7/8-inch inside-diameter combustor that can measure and compare the blow-out velocities of single-component fuels, slurries, and fuel mixtures with a wide range of reactivity and physical properties. The blow-out velocities of isooctane, n-heptane, isopentane, allyl chloride, and propylene oxide varied int he same way as flame speeds of the fuels. Results regarding the effects of different additives are also provided.

From Summary: "Stability derivatives have been computed for twisted wings of different plan forms that include variations in both the wing taper and the aspect ratio. Taper ratios of 1.0, 0,50, and 0.25 are considered for each of three aspect ratios: 6, 10, and 16. The specific derivatives for which results are given are the rolling-moment and the yawing-moment derivatives with respect to (a) rolling velocity, (b) yawing velocity, and (c) angle of sideslip. These results are given in such a form that the effect of any initial symmetrical wing twist (such as may be produced by flaps) on the derivatives may easily be taken into account."

The transition region between two parts of a pile which have different compositions is investigated. In the case where the moderator is the same in both parts of the pile, it is found that the diffusion constant times thermal neutron density plus diffusion constant times fast neutron density satisfied the use pile equations everywhere, right to the boundary. More complicated formulae apply in a more general case.

Ultrasonic cleaning uses high-frequency sound waves to induce cavitation within a cleaning, medium. During cavitation, millions of small bubbles form and collapse, resulting in agitation proportional to the energy put into the solution. The making and breaking of these bubbles produce the scrubbing action associated with ultrasonic cleaning.