Thesis describing the the computation of eigenstates for a particle moving in a spheroidal potential well under the influence of a strong spin-orbit interaction.

Some measurements of the effects of rocket-motor operation on base pressure were obtained incidental to other research on some bodies in free flight. These data are presented and qualitatively analyzed. The analysis indicates that jet effects on drag are of sufficient importance to deserve consideration in the design of jet motor nozzles, especially for aircraft and missiles where the thrust and drag are of the same order of magnitude. The base-pressure changes induced by the jet should be considered in the structural design of the outer body skin on the aft portion of fuselages containing jets. (author).

Combustion-chamber performance characteristics of a Python turbine-propeller engine were determined from investigation of a complete engine over a range of engine speeds and shaft horsepowers at simulated altitudes. Results indicated the effect of engine operating conditions and altitude on combustion efficiency and combustion-chamber total pressure losses. Performance of this vaporizing type combustion chamber was also compared with several atomizing type combustion chambers.

"A metal-ceramic composition containing approximately 80 percent chromium plus 20 percent aluminum oxide (Al(sub 2)O(sub 3)) by weight has been investigated for possible gas-turbine blade use. The results of modulus-of-rupture, thermal-shock, and blade-performance studies indicate that this material may have adequate thermal-shock resistance; however, the strength for the application appears marginal" (p. 1).

Memorandum presenting an investigation of the evaporation and spreading of isooctane sprays over a range of inlet-air conditions common in ram-jet engines. The total and liquid fuel distribution across the duct were determined. Over the specified ranges in the investigation, expressions were obtained which related the evaporation rate and degree of spreading of the sprays to the experimental variables.

From Summary: "An air-launched cone-cylinder test vehicle designed to obtain data at Mach numbers above 4.0 was rocket boosted from a release Mach number of 5.18. The vehicle was launched at an altitude of 35,000 feet and reached peak velocity of 5150 feet per second at 28,500 feet. The total-drag coefficient (based on maximum cross-sectional area) decreased gradually from 0.31 at a Mach number of 1.75 to 0.145 at a Mach number of 5.18, while the Reynold's number (based on body length) increased from 31 x 10 to the 6th power to 107 x 10 to the 6th power."

From Summary: "Current NACA research on the subject of jet effects on the flow over afterbodies in a supersonic stream is briefly summarized. Several jet nozzle types installed in various afterbody configurations are considered for a wide range of operating conditions."

From Summary: "Data from ditching investigations conducted at the Langley Aeronautical Laboratory with dynamic scale models of various airplanes are presented in the form of tables. The effects of design parameters on the ditching characteristics of airplanes, based on scale-model investigations and on reports of full-scale ditchings, are discussed. Various ditching aids are also discussed as a means of improving ditching behavior."

From Summary: "Some factors relating to inadvertent speed and Mach number increases in transport operation are discussed with the object of indicating the manner in which they might vary with different qualities of the airplane and the minimum margins required to guard against reaching unsafe values. The speed increments and the margins required under several assumed conditions are investigated. The results indicate that, on a percentage basis, smaller margins should be required of high-speed airplanes than of low-speed airplanes to prevent overspeeding in inadvertent maneuvers."

From abstract: Mesa V of the Lukachukai area is capped by Morrison sediments which dip gently eastward from the mountains to the mesa tip, where the strata are tilted sharply to the opposite dip by the Lukachukai monocline. The Salt Wash of Mesa V contains ore outcrops which indicate favorable intensity of mineralization at one horizon along a 2000-foot outcrop interval. Other scatted exposures indicate the existence of ore under much of the mesa surface.

LITR Fluoride-Fuel Loop. — The inconel loop was dismantled for removal of the samples and for recovery of the uranium by using the remote cutting tools installed in a half cell of the Solid State Building. Disassembly proceeded without incident. An electric-arc cutting technique was developed for removal of the stainless steel enclosure around the pump bowl. Fission power and maximum flux were determined by irradiating a simulated loop, by heat-balance calculations, by radiochemical analyses for fission products in the fuel, by measuring the activation of cobalt foils attached to the loop, and by activation of the loop tubing itself. The determination of the power by these various methods gave 2.5 to 2.8 kw during operation of the loop, and the maximum power density was 0.4 kw/cc. Chemical analyses of the fuel were carried out to determine U, Zr, and the major constituents of inconel: Ni, Cr, and Fe.

The results of this investigation indicate that maximum electric power generation can be obtained by selecting the turbine steam temperature within a range of plus/minus 30 degrees C. from an "idealized" steam temperature. This "idealized" steam temperature is shown to depend primarily on the maximum permissible uranium temperature. The minimum available condenser temperature and the temperature rise of the coolant in the pile effect the selection of the turbine steam temperature to lesser extent.

Report presenting base pressures measured in flight on fin-stabilized bodies of revolution with and without rocket chambers and a converging afterbody at a range of Mach numbers. Pressures were found to be higher over the center portion of the bases of models with rocket chambers than edge pressures, while center base pressures on models without rocket chambers were lower than edge pressures.

A study of the basic problems associated with the use of electrical propulsion systems for space travel has been carried out at the Lawrence Radiation Laboratory. The emphasis is on large systems capable of manned flight.

The Thorex Pilot Plant at Oak Ridge National Laboratory was operated during 1955, processing reactor-irradiated thorium slugs to recover U233 and thorium and 12 MTR fuel elements to recover U235 and Np237. The radiation exposure received by operating personnel during this period averaged 60 mrcp/man-week. Most radiation exposure was received in areas that were intended to be only slightly or nonradioactive. However, because insufficient decontamination of process solutions was achieved and equipment surfaces became contaminated from equipment failures, these areas became primary sources of personnel exposure. The installation of additional shielding where needed and the prompt removal of surface contamination successfully reduced the radiation levels and exposures in these areas. Remote control of processing equipment and sampling of very radioactive solutions from process equipment was successfully accomplished, and assisted in the reduction of exposure to operating personnel.

Zircaloy-2 has a strong tendency to absorb oxygen and nitrogen at elevated temperatures. These gas impurities are extremely harmful, causing brittleness and loss of corrosion resistance. The production of ductile corrosion-resistant welds by present methods required shielding of the weld metal by an inert gas atmosphere or by a vacuum. The alternative to an inert gas atmosphere or a vacuum is reduction of the welding time to a few milliseconds of time to prevent gas absorption.