Abstract: "The elastic double scattering of deuterons by complex nuclei has been investigated experimentally. Measurements were made on carbon, aluminum, and copper at around 157 Mev; on lithium, beryllium, and carbon at around 125 Mev; and on carbon and aluminum at 94 Mev. The expected tensor components of the deuteron polarization have not been observed. Measurements have been made of the differential cross section and vector-type polarization as a function of angle for the scattering of deuterons from the above elements, at the above energies. The observed polarizations were larger than would be expected on the basis of the individual nucleon-nucleus interactions. In a second experiment we measured the 169-Mev proton-proton polarization at 10, 15, 22.5, 30, and 35 in the laboratory system. The results indicate that partial waves up to and including L = 3 are important at this energy."

From Introduction: "The primary purpose of the investigation described in the present described in the present report is to formulate a method which is of value for qualitative calculations of base pressure both on airfoils and bodies."

After two batches (~ 340 kg) of fluoride salt from the ARE were reprocessed, pilot plant operations were terminated because of a leak through which an estimated 780 g of uranium (as UF6) escaped. Of the 21 kg of highly enriched uranium in the feed, 93.12% was collected as UF6 product, 0.13% represented measured losses, and 3.72% was unaccounted for (leak). An additional 3.03% was reclaimed from NaF beds and equipment washes. The product met both chemical purity and activity specifications for product level UF6. Decontamination from fission products was essentially complete. A gross gamma D.F. was apparently limited by the low activity of the feed salt.

"An analysis was made at flight Mach number of 0.9 to estimate performance of nuclear-energy-powered turbojet engine and optimum engine operating conditions and to determine gross weight and load-carrying capacity of airplane powered by such an engine. The size of airplane required to carry disposable load of 20,000 pounds was found to vary from approximately 300,000 to 900,000 pounds depending on assumptions. For a reactor tube-wall mean temperature of 2500 degrees R, turbine-inlet temperature of 2000 degrees R, reactor-free-flow-area ratio of 0.33, reactor-shielding-material specific gravity of 6.0, shielding thickness of 3.0 feet, and altitude of 30,000 feet, the airplane gross weight required to carry a 20,000 payload is 545,000 pounds" (p. 1).

Sanderson & Porter have carried out a series of studies over the last four years which indicate that the pebble-bed reactor way be an attractive way to obtain low-cost power. At the request of the Atomic Energy Commission, two design studies have been carried out on this concept at the Oak Ridge National Laboratory. The first of these a preliminary design of a 10-Mw(t) reactor experiment, the PRRE, was initiated September 10, and a report on the study was issued November 1960. The second phase of the work, a conceptual design study of a 330-Mw (e) central station, was initiated November 1, and is the subject of this report.

Sea-level static testing of turbojet engine afterburner.

Report presenting a sea-level static investigation to determine the performance and some design principles for a short afterburner. The power section of a 12-stage axial-flow turbojet engine was used and the afterburner was designed to fit within the length required for the tail pipe used on the standard nonafterburning model.

Gradual corrosion and mechanical wear of equipment over a period of years has affected the seals and gasketing of the electric pot calcining equipment in the 224-U Building Cell E to such an extent that the desirable vacuum cannot be maintained in the pots. Air contamination has been gradually increasing, and this, together with a lowering of the mask working limits, has made it necessary to require personnel to wear assault masks continuously. Indications are that, with the increased production now required, the level of air contamination will continue to rise unless measures are taken to prevent it. The Manufacturing Department has requested that a project be established to reduce the contamination level. Several items of improvement are listed for consideration including, in general, the electric pot agitation and sealing, semi-automatic pot unloaders, cell ventilation and air locks, and the nitric acid off-gas system and stacks. Because of the urgency of improving the conditions, the project, at first, is to provide for immediate improvements for the electrical pot agitation, the pot cover leakage, and the nitric acid off-gas system and stack. Additional study will be required to determine the extent of the ventilation and semi-automatic unloading improvements required.

"Low-aspect-ratio wings having pointed plan forms are treated on the assumption that the flow potentials in planes at right angles to the long axis of the airfoils are similar to the corresponding two-dimensional potentials. For the limiting case of small angles of attack and low aspect ratios the theory brings out the following significant properties: (1) The lift of a slender, pointed airfoil moving in the direction of its long axis depends on the increase in width of the sections in a downstream direction. Sections behind the section of maximum width develop no lift. (2) The spanwise loading of such an airfoil is independent of the plan form and approaches the distribution giving a minimum induced drag. (3) The lift distribution of a pointed airfoil travelling point-foremost is relatively unaffected by the compressibility of the air below or above the speed of sound. A best of a triangular airfoil at a Mach number of 1.75 verified the theoretical values of lift and center of pressure" (p. 1).

Low-aspect-ratio wings having pointed plan forms are treated on the assumption that the flow potentials in planes at right angles to the long axis of the airfoils are similar to the corresponding two-dimensional potentials.

From abstract: "A method for fabricating 30-in.-long stainless steel - uranium dioxide sheet was developed and the properties of the fabricated sheet were investigated."

"The possibility of radioactivity transport in the groundwater system as the result of a hypothetical maximum credible gas leak was evaluated." "The present study confirms the low radiation levels in the groundwater predicted in the initial calculations." (from Summary)

Report presenting an investigation to determine the effect on performance of two methods of throat-area modulation of two convergent plug nozzles. Data were obtained over a range of pressure ratios. Results regarding the performance of the translatable outer-shell-type plug nozzle, performance of the iris-outer-shell-type plug nozzles, sensitivity to throat-area variation, and air-flow parameter are provided.

This report presents the best estimate possible on the basis of the available information as to how high an energy would be necessary in order that the gas pressure which could be tolerated would be attainable with present techniques (say 10-(-7) mm Hg.)

Performance and boundary-layer data were taken in a 12 degree 10-inch inlet-diameter conical diffuser of 2:1 exit- to inlet-area ratio. These data were taken for two inlet-boundary-layer conditions. The first condition was that of a thinner inlet boundary later (boundary-layer displacement thickness, delta* approximately equal to 0.034) produced by an inlet section approximately 1 inlet diameter in length between the entrance bell and the diffuser. The second condition was a thicker inlet boundary layer (delta* approximately equal to 0.120) produced by an additional inlet section length of approximately 6 diameters. Longitudinal static-pressure distributions were measured fro wall static orifices. Transverse total- and static-pressure surveys were made at the inlet and exit stations. Boundary-layer velocity distributions were measured at seven stations between the inlet and exit. These data were obtained for a Reynolds number (based on inlet diameter) range of 1 x 10(exp 6) to 3.9 x 10(exp 6). The corresponding Mach number range was from M = 0.2 to choking. At the maximum-power-available condition supersonic flow was obtained as far as 4.5 inches downstream from the diffuser inlet with a maximum Mach number of M approximately equal to 1.5. The total-pressure loss through the diffuser in percentage of inlet dynamic …

Report presenting an investigation of an experimental 15-stage axial-flow compressor to determine the effect of inlet-annulus area blockage on disrupting the rotating stall and altering the overall performance and stall characteristics of the compressor. It is part of a general investigation to determine how to alleviate the general problems of blade vibration and poor off-design performance associated with compressor rotating stall.

A large (size 2) Purex pulse generator was installed in the 321 Building Tan Farm to pulse solutions in the prototype Purex HA Column. Flow sheet considerations indicated a need for information on leakage rates with various size weep holes in the pulse generator piston. In addition to leakage tests, experiments were conducted to determine the air required under the piston to hold the column contents away from the pulse generator piston thereby preventing leakage during shut down and the determine the time required to bleed the air trapped in the pulse leg when the column is first filled. [...] Leakage past the piston was not appreciably affected by pulse frequency. [..] Bleeding the air out of the pulse leg under start-up conditions, even with the piston weep hole plugged, was rapid. The longest time required to bleed the pulse leg was 36 minutes, which included a column-filling time of 30 minutes.

The technique of high-frequency titrimetry has been applied to the determination of thorium, uranium, sulfate, and free acid. In Part I of this report, the reproducibility of the method for the titration of standard solutions which contained 50mg of thorium in the absence of interferences is established. The coefficient of variation of the method, under these conditions, was found to be less than one per cent. In Part II, the effect of uranium on the high-frequency titration of thorium, as well as the application of the method to actual samples, is discussed. Uranium in a ratio of 5 to 1 to thorium can be tolerated. When the method is applied to the analysis of representative samples, the coefficient of variation is one per cent.

"A ram-jet engine with an experimental 48-inch-diameter combustor was investigated in a free-jet facility. The combustor design comprised a large-volume annular pilot region and an array of sloping baffle- or gutter-type flameholders. The combustor was intended to operate at a fuel-air ratio of about 0.037" (p. 1).

Report presenting an investigation in a free-jet facility of a ramjet engine with an experimental 48-inch-diameter combustor. Three combustor lengths, three lengths of the shroud which separated the bypass air from the burning stream, and four fuel-distribution systems were investigated over a range of fuel-air ratios and a range of engine air flows. Results regarding the engine performance and ignition data, effect of fuel profile on combustion efficiency, total-pressure ratio, and distribution of static pressure in the main air stream are provided.

The following report analyzes several reported incidents of uranium-rich zirconium-uranium explosions. This report offers notes designed to describe conditions sufficient to cause an explosion with an 80% wt. uranium alloy.

Abstract: This project was designed to test the chemical feasibility of depositing of depositing a primary uranium mineral from a pregnant solution by exposing the solution to natural gas in an environment favorable to such deposition.

Report presenting an investigation of the estimated minimum cooling requirements and related performance of turbojet engines equipped with high-performance single-stage turbines with air-cooled corrugated-insert blades over a range of turbine-inlet temperature, tip speed, and hub-tip radius ratio for Mach number 2 at 50,000 feet. The effects of stress-ratio factor, flight Mach number, altitude, turbine rotor impeller efficiency, and outside heat-transfer coefficient on cooling requirements were also investigated.

Report presenting wind-tunnel testing at Mach numbers of 1.5 and 2.0 to investigate the force, moment, and control characteristics of a canard missile configuration and its components in pitch and sideslip. The missile had small all-movable horizontal control surfaces at the nose and a cruciform wing at the rear, all of trapezoidal plan form. Trailing-edge flaps on the vertical fins were provided to supply directional control.