A series of two-group calculations has been made on the Oracle for the purpose of obtaining critical-mass and flux distribution data for various ORR core configurations. The 3G3R code of Bate, Einstein, and Kinney was used, together with the RSP code developed by Nelson. This made it possible to obtain results for the three-dimensional case. The results, which are presented graphically, are intended to serve as a guide for the design of experiments until such time as actual measurements are available. The calculations were performed for the "clean cold" case, and it should be realized that the presence in the core of experiments and of fission products built up during operation will materially alter the flux patterns found. It is believed that the critical-mass data are accurate to within 10%. Within the fuel region it is believed that the thermal-flux patterns are the also accurate to this degree. Comparison of the results with MTR critical experiments, however, indicates that the thermal flux in the reflector in the vicinity of the fuel-reflector interface may have been underestimated by a factor of as much as 1.3. It should also be recalled that in a two-group calculation the "fast flux" is often a …

A preliminary investigation was conducted to determine the combustion characteristics of a fuel composed of 50 percent pentaborane and 50 percent JP-4 (MIL-F-5624A) by weight in a turbojet combustor. A combustor designed to fit the housing of a J33-A-23 turbojet engine was selected for convenience. The fuel was evaluated at two engine conditions simulating altitudes of 40,000 and 57,000 feet, an engine speed of 85 percent of rated rpm, and a flight Mach number of 0.6. The pentaborane blend was initially evaluated in combustors developed for pure pentaborane and diborane reported in NACA RM E53B18 and RM E52L15. The performance of the blend was unsatisfactory in these combustors. A new combustor was then developed which provided combustor efficiencies measured from 91 to 101 percent as compared with efficiencies of 92 to 94 percent previously obtained for pentaborane at comparable conditions. Additional refinements of design details are needed to obtain lower oxide deposits and a more uniform outlet temperature profile; however, the combustor is believed to incorporate some of the design principles required to obtain satisfactory over-all performance with the fuel blend investigated.

The Atomic Energy Commission has requested that HAPO produce 30 Kg of U-233 in the form of irradiated thorium (Q) slugs. It is requested that delivery be completed by July 1, 1955, and that delivery begin as soon after July 1, 1954 as possible. The bulk of the ``Q`` pieces will not be available for charging for some time; June 1954 is the best estimate at this time. There are no data on a mixed J-Q loading. There are some thorium slugs on-site which are normally used for flattening purposes, and there is time to get some preliminary information by the exposure of a few mixed J-Q columns. It is intended that the U-233 produced in the test will be part of the production requested by the AEC in HAN-53744. This Production Test authorities the charging of sixteen columns loaded with alternate ``J`` and thorium.

Report presenting an evaluation of convective heat-transfer coefficients from skin temperatures measured along the body of a research model designated NACA RM-10. Heat-transfer data is presented for a range of Mach and Reynolds numbers based on the axial distance from the nose to the point at which the temperature measurements were made. Results regarding the recovery factor, heat transfer, correlation with different aircraft models, and Reynolds analogy are provided.

"Instrument-flying trials have been conducted in a single-rotor helicopter, the maneuver stability of which could be changed from satisfactory to unsatisfactory. The results indicated that existing longitudinal flying-qualities requirements based on contact flight were adequate for instrument flight at speeds above that for minimum power. However, lateral-directional problems were encountered at low speeds and during precision maneuvers" (p. 1).

Abstract: This report presents the results of a study performed by the Ford Instrument Company, Division of Sperry Rand Corporation, and its subcontractor, Maryland Shipbuilding & Drydock Company, for the Maritime Administration, U. S. Department of Commerce, under terms of Study Contract No. MA-1893, dated March 11, 1959. The purpose of this study is to evaluate various techniques for pretesting and installing nuclear prototype power plants in merchant ships and develop that technique offering the widest general application using time, cost and safety as essential criteria. Acknowledgement is made for the valuable counsel received from personnel of the American Bureau of Shipping, Isbrandtsen Company, Inc., Maritime Administration, Atomic Energy Commission, and the United States Coast Guard.

Report presenting an investigation of the effects of suction through a porous leading-edge surface in the 19-foot pressure tunnel on a wing with 37 degrees of sweepback of the leading edge, an aspect ratio of 6, taper ratio of 0.5, and NACA 64(sub 1)-212 airfoil sections normal to the 27-percent-chord line. Results regarding the wing without flaps, wing with trailing-edge flaps, and power requirements for porous-leading-edge suction are provided.

The purpose of this study has been to evaluate the chemical resistance of various bearing materials to solutions of nitric acid and uranyl nitrate hexahydrate with views toward selecting the best material to be used as bearings in Purex submerged rotating equipment.

Flow-visualization studies, using smoke, were made of the secondary flows in rectangular bends, tandem cascades, and high-turning configurations. The roll-up of the wall boundary layer of a rectangular bend forms a passage vortex near the suction surface similar to that previously observed for cascades. The vortex so formed then shifts out into the main stream. Because of leading-edge effects, the boundary-layer flows in bends were found to be sufficiently different from the flows in blade rows to make direct application of bend results to blade rows inadvisable.

From Summary: "An investigation was conducted in the 8-by-6 foot supersonic wind tunnel on the effect of exhaust-gas temperatures on the external and internal characteristics of a convergent-divergent nozzle having an area expansion ratio of 1.83. Data were obtained over a pressure-ratio range from 1 to 20 at free-stream Mach numbers of 1.6 and 2.0 for exhaust temperatures of 860 degrees, 1650 degrees, and 2000 degrees R. Results of this investigation indicated that generally both the internal and external performance characteristics were only slightly affected by a large change in jet temperature. The small differences in performance which did occur were predicted satisfactorily from theoretical considerations."

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The following report is a quarterly report done by the Physics Division of the University of California's Radiation Laboratory, covering the period of November and December of 1953, and January of 1954. This report discusses general physics research and the development and operation of the accelerator.

Herman Lurie's weekly report for the sugar market.

Report presenting an investigation of the static lateral stability characteristics of a swept-wing fighter-type airplane with three vertical-tail configurations and two wing configurations at an altitude of 40,000 feet over a range of Mach numbers. Data was obtained in several conditions, including constant-heading sideslips and wings-level turns, aileron rolls, and abrupt rudder pulses. Results regarding the sideslip characteristics, lateral control, and control effectiveness derivatives are provided.

Report presenting measurements of the local flow angles near the fuselages of a triangular-wing wind-tunnel model and an F-86A-5 airplane in flight using airflow detectors on the fuselages. A comparison of the measured and predicted flow angles is provided. Results indicated that the accuracy of the predicted indicated angles of attack was not sufficient to eliminate the necessity of a flight calibration of a detector mounted on a fuselage.

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From Summary: "An experimental investigation was made to determine the feasibility of using hollow turbine blades in engines designed for short service life. Airfoils were fabricated from sheet material and techniques of welding and brazing attachment were investigated. The airfoils were not intended to be cooled. A principal objective was the reduction of strategic material requirements primarily as a function of direct weight reduction."

The object of this project is to conduct studies on the coating of metals and alloys by the gas plating process. Coatings to be studied consist of chromium on copper; alloys of nickel chromium on copper; molybdenum on stainless steel and Inconel; chromium on stainless steel and Inconel; and tungsten and molybdenum and their carbides on stainless steel and Inconel.

Experiments in the controlled melting of irradiated fuel speciman, particularly of the APPR, STR, and MTR types, have confirmed that prolonged heating in air at temperatures in excess of the melting point results in the release of a large portion of the radioactivity. On the other hand, a moderate amount of heating in air or steam sufficient only to melt a specimen results mainly in the partial volatilization of rare gases, iodine, bromine, cesium, and rubidium. In the presence of air or water vapor, strontium and other fission products are not released. At trace concentration of fission products, slow melting of the APPR plate at 1525 d C in air or steam effected the release of 50% of the rare gases, 33% of the iodine, 9% of ihe cesium, and traces of strontiuun. After 25% burn-up, the cesiuun value increased to about 60%. Aluminum alloy of the MTR type, also at trace concentration, upon melting at 700 d C released up to 2% of the iodine, 10% of the rare gases, and negligible portions of other fission products. Zirconium alloy of the STR type after 15% burn-up, when melted at 1850 d C, released up to 95% of the rare …

Experiments in the controlled melting of irradiated fuel specimens, particularly of the APPR, STR, and MTR types, have confirmed that prolonged heating in air at temperatures in excess of the melting point results in the release of a large portion of the radioactivity. On the other hand, a moderate amount of heating in air or steam sufficient only to melt a specimen results mainly in the partial volatilization of rare gases, iodine, bromine, cesium, and rubidium. In the presence of air or water vapor, strontium and other fission products are not released. At trace concentration of fission products, slow melting of the APPR plate at 1525 C in air or steam effected the release of 50% of the rare gases, 33% of the iodine, 9% of the cesium, and traces of strontium. After 25% burn-up, the cesium value increased to about 60%. Aluminum alloy of the MTR type, also at trace concentration, upon melting at 700 C released up to 2% of the iodine, 10% of the rare gases, and negligible portions of other fission products. Zirconium alloy of the STR type after 15% burn-up, when melted at 1850 C, released up to 95% of the rare gases, 90% of …

"Pressure-distribution and force tests of a circular cylinder have been made in the Langley 11-inch hypersonic tunnel at a Mach number of 6.86, a Reynolds number of 129,000 based on diameter, and angles of attack up to 90 degrees. The results are compared with the hypersonic approximation of Grimminger, Williams, and Young and with a simple modification of the Newtonian flow theory. The comparison of experimental results shows that either theory gives adequate general aerodynamic characteristics but that the modified Newtonian theory gives a more accurate prediction of the pressure distribution" (p. 1).

Report on the principle of measuring the time-of-flight of neutrons, magnetic-core storage of detector pulses, how pulses are stored, current generator, storage cycle generator, and cathode ray oscillograph.

Report presenting an analysis of results obtained from a transonic wind-tunnel investigation of two bodies of revolution with the same nose shape but two different shapes of afterbody. Results regarding pressure distribution, normal-force characteristics, pitching-moment and center-of-pressure characteristics, and detailed load characteristics are provided.

The purpose of this specification is to set forth in a single document a coherent set of requirements as affected by interrelated design and operating conditions. Basic values, dimensions, and other parameters fundamental to establishment of design specifications for the individual reactor components are given. This document will eventually become a part of the complete ``Design Specifications for ``X`` Reactor`` to be issued later. At that time some of the information given here (such as the moderator dimensions) will appear elsewhere in the document and therefore there is some duplication. Such information was necessary to give the complete scope. An attempt is made to give the basis or background at the end of the document. All references pertinent to the choice are probably not included.