Although the oxides such as Al/sub 2/O/sub 3/, MgO, UO/sub 2/, ThO/sub 2/ , Be O, and ZrO/sub 2/ are used as refractory materials, very little reliable thermodynamic data predicting the stabilities of the gases in equilibrium with the solids at temperatures above 1700 deg C exist. In most cases the vapor pressures are not accurately known and in some cases the gaseous molecules are uncertain. Hence one experiences difficulties in attempting to predict ihe interaction of these oxides with the refractory metals such as tungsten and tantalum. The problems are made even more difficult because of a lack of reliable information concenning the gaseous oxides of tungsten and tantalum. As a means towards establishing the thermodynamic stabilities of these refractory oxides, the authors propose to survey the existing results and to describe some rather crucial experiments relating to the interaction of these oxides with tungsten and tantalum. Although not establishing accurate free energies, these experiments, neventheless, hnve shown conclusively the unreliability of some supposedly accurate thermodynamic properties because of a failure to examine the investigations in this manner. In addition, they indicate more reliable limits of free energies in certain cases. (auth)

Report presenting the performance of a two-dimensional side inlet with a technique of varying compression-surface angle while retaining a fixed-geometry diffuser at several Mach numbers and zero angle of attack. A 12 degree compression ramp was faired into the diffuser contour in this conventional manner. Results regarding the inlet flow field, application to reduced engine speeds, and a inlet performance with a sudden expansion in the diffuser are provided.

This paper is intended as a preliminary report on the Homopolar configuration (axial magnetic field with radial electric field), which is the rotating configuration most thoroughly studied thus far. The analysis presented in this paper applies principally to the "ideal" Homopolar, that is, the configuration free from electrode-sheath drops and other disturbing but remediable phenomena. Design considerations for various interesting plasma appliances are derived and documented with preliminary experimental results. The experiments have been carried out under high-density (pinch-type) conditions which favor the creation of a totally rotating plasma and the actual physical measurement of the characteristics of such a plasma. When larger models of the Homopolar are built, it will be possible to use the present pinch-type technique of plasma formation at much lower density, just as has been done in the case of the toroidal stabilized pinch.

The "ORACLE", Oak Ridge Automatic Computer and Logical Engine, was installed at Oak Ridge National Laboratory :in 1953 and.has been in operation since that time. This manual describes the machine's design, the number systems it uses, and its basic operations.

Report presenting the aerodynamic characteristics of a new type of lateral control through a range of Mach numbers. The control consisted of airfoils mounted vertically at the tips of the wing and could be rotated to induce rolling moments or lift on the wing surface. Results regarding lateral-control characteristics and lift-control characteristics are provided.

Core specimens of Zr alloys such as Nb--Zr and Fe-Nb-Zr were in-pile corrosion tested. Operating conditions are summarized for these and former similar tests. The corrosion solution contained UO/sub 2/SO/sub 4/, CuSO/sub 4/, and H/sub 2/SO/sub 4/, with a make-up solution composed of UO/sub 2/SO/sub 4/, CuSO/sub 4/, H/sub 2/SO/sub 4/, and Cr. Corrosion rites ire tabulated and presented graphically. (J.R.D.)

The economiics and physics of four schemes of pIutonium recycle in the Calder Hall type reactor are considered. The four possible schemes are: (I) to blend the Pu produced In a run with fresh naturaI U for a subsequeut run; (2) to alloy the Pu with somie diIuent metal and fabricate the alloy Into high heat- transfer elements morc like MIR or PWR-sced type elements and"spike' a subsequent load of fresh natural U elemients with these Pu elemicnts; (3) to recycle half the spent U as well as the Pu; and (4) to thke advantage of the extra reactivity gained fromi the recyeIed Pu to deerease the Iattice spacIng, thereby increasing the conversion ratio with the hope of increasirg the attaInabIe exposure. It was concluded that schcme (1) is the miost economiical. (W.D.M.)

A description of hot laboratory metallography and techniques of operation are presented. These facilities and techniques provided a means of examining fuel elements that contain UO/sub 2/ after irradiation to high burnups. Some unusual irradiation characteristics of UO/sub 2/ were observed, and each effect is discussed. A complete explanation of the causes of such effects has not yet been obtained. (auth)

A preliminary definition of a fabrication process for ferritic stainless steel-UO/sub 2/ fuel clad with Type 430 stainiess steel has been achieved. The procedure is an adaptation of an earlier process for preparing austenitic fuel elements, and consists of the cold-binder extrusion of a plastic powder dispersion which is fired in dry hydrogen, fitted with welded end caps, and electroplated with nickel. This core is inserted into a length of type 430 stainless steel cladding and the assembly is bonded by hot-swaging at 800 C. The irradiation performance of such a fuel element was examined by means of an MTR test. The results of this test strongly indicated that the desired lowering of UO/sub 2/ particle operating temperature was realized and that ferritic stainless steel is not unduly susceptible to irradiation dannage. (auth)

A Monte Carlo program for the IBM 704 is described. It is intended to be primarily useful in the computation of intensive reactor parameters. The program is suited to cylindrical geometry wherein parallel tubular regions are arbitrarily located in a matrix of concentric circular annular regions. Normally the annular regions correspond to moderator and/or reflector regions and the interjected tubular regions to fuel elements. The program requires a 32,768 word core memory amd four tape units. Package PK-1 from the library of General Electric packages is also required. (auth)

Report presenting an investigation to determine the effectiveness of experimental control signals applied to a theoretical inlet throat Mach number control system and normal-shock-position control system for varying the inlet geometry of a twin-duct prototype aircraft. Results regarding inlet instability, control requirements, individual throat Mach number control signals, average throat Mach number control signals, theoretical thraot Mach number control analysis, effect of angle of attack, and theoretical normal-shock-position control are provided.

Report presenting an investigation in the supersonic wind tunnel to determine the effectiveness of experimental control signals applied to a theoretical inlet throat Mach number control system and normal-shock-position control system for varying the inlet geometry of a twin-duct, side-inlet, fuselage forebody model of a prototype aircraft. These types of control systems have been found to be particularly helpful in supersonic flight. Results regarding inlet stability, control requirements, individual throat Mach number control signals, average throat Mach number control signals, effect of angle of attack, and theoretical normal-shock-position control are provided.

References to accelerators and accelerator technology in the technical literature from July 1954 through June 1957 are listed in Section 1, the bibliography. Most of the references are taken from Nuclear Science Abstracts, Chemical Abstracts, Physics Abstracts, and Electrical Engineering Abstracts. In Section H, accelerator installations throughout the world are listed together with the types of particles accelerated and the energy and other characteristics of the machines. (auth)

Report presenting eight thin magnesium fins, seven with the leading edges swept back 17 degrees and one with the leading edge swept back 45 degrees, in the preflight high-temperature jet. The investigation was made to determine the effectiveness of various protective coverings designed to alleviate aerodynamic-heating effects and intended for application on the first stage of rocket-propelled multistage hypersonic models.

Report presenting testing of three uninstrumented tapered magnesium fins with the leading edges swept back 17 degrees in an ethylene-heated high-temperature jet. The testing was carried out to investigate some effects of leading-edge diameter and leading-edge shape on the aerodynamic heating by noting the time for melting to begin on the fins. Results indicated that increasing the diameter of cylindrical leading edge increased the time required for melting to start.

Report presenting pressures measured during a free-flight test at zero angle of attack over a rocket model with a modified Von Karman nose in combination with a cylindrical center section and a 10 degree half-angle flare.

Memorandum presenting a five-stage rocket-propelled model flown up to a Mach number of 10.9 and a corresponding free-stream Reynolds number of 6.57 x 10(exp 6) based on nose diameter. Temperatures were measured at 16 stations on the inside of a flat-faced cylinder made of copper. Results regarding the flight test, wall temperatures, heat-transfer data, measurement repeatibility and effects of angle of attack, comparison of measured and theoretical stagnation-point heating rates, and measured and theoretical heating rates over the front and side of the nose are provided.

"Several multiplier phototubes produced by England, Russia, or Switzerland were evaluated for amplification, photocathode sensitivity, photo-electron collection efficiency, cathode uniformity, and dark current. A description of the various tubes by designation numbers is given, along nth a description of techniques and equipment used in testing."

Report presenting the results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration without analysis for a range of Mach numbers. Data are presented for a variety of angles of attack and canard angles.

"The momentum integral equations are derived for the boundary layer on an arbitrary curved surface, using a streamline coordinate system. Computations of the turbulent boundary layer on a slightly yawed cone are made for a Prandtl number 0.70, wall to free-stream temperature ratios of 1/2, 1, and 2, and Mach numbers from 1 to 4. Deflection of the fluid in the boundary layer from outer stream direction, local friction coefficient, displacement surface, lift coefficient, and pitching-moment coefficient are presented" (p. 1).

Report discussing findings on net thrust, fuel flow, and related performance indices for hydrogen-rich operation of nacelle-type and submerged ramjet engines at various Mach numbers. Testing concluded that the system could be helpful in a flight path involving acceleration from low to high flight speeds. Some trends of the effect of the operation conditions are noted, but no conclusions are drawn because of the preliminary nature of the report.

Report issued by the Oak Ridge National Laboratory discussing quarterly progress made by the Homogeneous Reactor Project. Progress of operations, design, development, and analysis is presented. This report includes tables, illustrations, and photographs.

None

Report presenting an investigation of the effect of temperature using di(2-ethylhexyl) sebacate lubricant and dry powder lubricants on rolling-contact fatigue life on AISI M-1 tool-steel balls in the rolling-contact fatigue spin rig at maximum theoretical Hertz stress levels of 650,000 and 725,000 pounds per square inch in compression.