From abstract: "The stability of polystyrene and phenolic ion-exchange resins to radiation from a Co60 source and from absorbed Ce144-PR144 was investigated. Sulfonated polystyrene cation-exchange resins lost 10 to 20% of their capacity per watt-hour of radiation absorbed per gram of oven-dry resin, while the quaternary amine anion-exchange polystyrene resins lost about 40%. Phenolic cation-exchange resins lost only 1%."

This partially annotated bibliography contains 334 references from papers published from 1945 to 1959 and includes references on the consumable - and nonconsumable - electrode vacuum arc melting process. References are also given on electrode preparation, furnace construction and operation, melting, sintering, vacuum techniques, and theory.

Abstract: "The analysis of hafnium and zirconium by the copper spark technique is presented for solutions of HCl, HF, and HClO4 acids. The special techniques of electrode protection and vacuum drying of perchloric acid samples are outlined. Also given are the working curves and deviations of both elements."

Engine dynamics and controls data are presented for a ram-jet engine which was operated in a free-jet facility at a Mach number of 2.76 and altitudes from 68,000 to 82,000 feet. The predominant engine dynamic characteristics was dead time, with values ranging from 0.018 to 0.053 sec. The control systems were designed to hold a constant ratio of a diffuser static pressure to an inlet-cone reference static pressure.

Report describing an experiment to obtain heat-transfer and pressure-drop data for the air side of a liquid-metal to air, shell-and-tube heat exchanger. Testing was conducted in a 500 kilowatt facility using sodium as the shell-side heating fluid. Results regarding the shell-and-tube heat exchanger and finned-tube heat exchanger friction factor are provided.

Experimental investigation of engine dynamics and controls for 48-inch ramjet engine in free jet facility at Mach number 2.76 and altitudes 68,000 to 82,000 feet. The engine data presented include steady-state performance, indical response, frequency response, and ignition characteristics. Ignition data are presented for representative fuel-air ratios which show that the normal shock overshoots its final position by several feet during ignition transients.

From Summary: "A study of the available transonic Mach number data on low-lift buffeting, wing dropping, and changes in the angles of zero lift for symmetrical airfoils indicates that these phenomena are allied and are probably the result of shock-induced separation. The study has indicated that there are combinations of airfoil-thickness ratio, aspect ratio, and sweep which may allow flight through the transonic speed range without experiencing buffet or wing drop at low lift."

Memorandum presenting a wind-tunnel investigation of the low-speed, static, lateral and directional characteristics of a model of an early design of the X-3 airplane with the wing flaps neutral and deflected. The model utilized a wing with an aspect ratio of 3.01, a 4.5-percent-thick hexagonal section, and a taper ratio of 0.4. Results regarding lateral stability and control with the flaps neutral, with the flaps fully deflected, with miscellaneous additions to the complete model, directional stability and control with the flaps neutral, with the flap fully deflected, with miscellaneous additions to the complete model, and oscillating rolling moments are provided.

Thermal-shock resistance of a ceramic comprising 60 percent boron carbide and 40 percent titanium diboride was investigated. The material has thermal shock resistance comparable to that of NBS body 4811C and that of zirconia, but is inferior to beryllia, alumina, and titanium-carbide ceramals. It is not considered suitable for turbine blades.

Report presenting an experimental investigation of a modified parabolic-bladed centrifugal impeller that was altered by cutting back every other blade to form splitter vanes. It was investigated over a range of equivalent impeller tip speeds and a range of flow rates. Results regarding the overall performance characteristics, a comparison of the splitter vane impeller and the fully bladed impeller, the maximum weight flow, and static-pressure ratios are provided.

From Summary: "Several methods of obtaining the time response of Linear systems to either a unit impulse or an arbitrary input from frequency-response data are described and compared. Comparisons indicate that all the methods give good accuracy when applied to a second-order system; the main difference is the required computing time. The methods generally classified as inverse Laplace transform methods were found to be most effective in determining the response to a unit impulse from frequency-response data of higher order systems. Some discussion and examples are given of the use of such methods as flight-data-analysis techniques in predicting loads and motions of a flexible aircraft on the basis of simple calculations when the aircraft frequency response is known."

"A primary objective of turbine research is to obtain information that will aid in the design of gas turbines for any given application with minimum losses. As part of a program to obtain such information, flow surveys downstream of both the stator and the rotor of an experimental turbine were made in order to obtain detailed information about the flow conditions and the losses within the machine. The single-stage, low-radius-ratio turbine studied is relatively conservative in design, having low rotor-inlet relative Mach number, low turning angle, and high reaction at the rotor-root section" (p. 1).

Summary: The design, construction and assembly of all components were completed during the first contract year previous to December 1963. These efforts, defined by Tasks A-F, are document in (1), (2), and (3). Brief summaries of these completed efforts are given in the introduction to each of the tasks in the text of this report. The digest given below covers only the shakedown and analysis work carried out in the fourth quarter of the first contract year. Task G Shakedown Tests. The photographic procedure has been experimentally defined for the glass test section. Four automatic 35 mm cameras and four strobe light sources have been ordered on ATL funds and their respective mounting arrangements are in place. Roughly ten test runs were carried out in the glass test section during the course of the above work. Satisfactory recorder traces have been obtained on all measurement systems. These systems presently meet the accuracy and linearity specifications initially set. An x-ray void fraction signal adjustment and filtering circuit has been design and installed to provide equal resolution across the test section. Calibration disc inserts have been installed to permit satisfactory beam intensity calibration. Good agreement has been obtained between calculated and measured …

"The correction to photon-photon scattering processes due to the existence of the particles other than electrons is reported. The correction is of the same order in the electric charge as the lowest order term in the perturbation expansion in quantum electrodynamics, although the relevant corrections to the electron-photon and electron-electron scattering are all of higher order."

Abstract: Neutron flux and gamma radiation measurements through the SM-1 primary shield were made at the startup of Core II in June 1961. They extend previous measurements (APAE-35) both vertically and horizontally in the primary shield and in the rod drive pit. Dose rate measurements on spent fuel elements under water are also reported.

An investigation on various can-type burners in a Bumblebee 18-inch ram jet under controlled conditions of pressure altitude and ram pressure ratio was conducted in the NACA Lewis altitude wind tunnel with kerosene as fuel. The performance of the following can-type burner configurations was better than that of the other burner configurations investigated: (1) a flame holder having a two-pitch alinement of perforations, 0.07-inch-wide cooling slots, and an arrangement of fuel nozzles located within an annulus having a mean radius of 7.24 inches; and (2) a flame holder having a zero-pitch alinement of perforations, 0.16-inch-wide cooling slots, and an annulus of fuel nozzles having a mean radius of 6.89 inches.

Report presenting an investigation of the boundary-layer characteristics at the mean radius immediately downstream of a typical turbine stator blade over a range of blade-outlet critical-velocity ratio from 0.8 to 1.16. Total boundary-layer momentum thickness for the blade and individual thicknesses obtained for the suction and pressure surfaces are compared with values calculated from the turbulent-boundary-layer theory.

"The ditching characteristics of the Army B-36 airplane were determined by testing 1/20- and 1/30-scale dynamic models in calm water in Langley tank no. 2 and at the outdoor catapult. The scope of the tests consisted of ditching the models at various conditions of simulated damage, landing attitudes, and speeds, with various flap settings using several degrees of restraint of the flap hinges. The ditching behavior was evaluated from recordings of deceleration, length of run, and motions of the models" (p. 1).

"A wind-tunnel investigation of a 0.049-scale model of the Boeing XB-52 airplane was made at Mach numbers from 0.30 to 0.925 and at corresponding Reynolds numbers from about 2.3 x 10(exp 6) to 4.3 x 10(exp 6). The results of the investigation indicate satisfactory static longitudinal stability throughout the test Mach-number range and some loss in tail effectiveness beginning at about 0.80 Mach number. A comparison of the results of these tests with those of the same model in the Boeing Airplane Company's wind tunnel showed close agreement of lift- and drag-divergence Mach numbers. Slight differences were observed in tail effectiveness and the position of the stick-fixed neutral point."

"Free-flight tests have been made to determine the zero-lift drag of several configurations of the XAAM-N-2 pilotless aircraft. Base-pressure measurements were also obtained for some of the configurations. The results show that increasing the wing-thickness ratio from 4 to 6 percent increased the wing drag by about 100 percent at M = 1.3 and by about 30 percent at M = 1.8. Increasing the nose fineness ratio from 5.00 to 6.25 reduced the drag coefficient of the wingless models a maximum of about 0.030 (10 percent) at M = 2.0" (p. 1).

Report on UCRL progress in general physics research and accelerator operation and development.

M-388 is an aluminum alloy consisting of 2S aluminum with an addition of 1% nickel. Preliminary corrosion studies which were conducted by Dreley and by Dillon indicated that the material exhibited excellent resistance to intergranular type of corrosion in distilled water at temperatures of up to 350 C. The combination of a low thermal neutron cross-section and good corrosion resistance make M-388 alloy a candidate material for use in reactor process tubes and fuel element cans. The purpose of the study was to determine some of the mechanical properties of M-388 aluminum alloy at room temperature and at elevated temperatures.

Thorium bismuthide when crystallized from a solution i bismuth results in large platelets which may be as large a 1 centimeter in diameter. A slurry of these platelets is difficult to pump through pipe lines and filters. The particle size can be reduced by (1) very rapid cooing (approximately 1000 degree C per second) or (2) ultrasonic treatment. The latter, much easier to attain in large scale, gives equiaxed particles of thorium bismuthide.