This report seeks to "develop a practical method of evaluating the eddy diffusivity of heat transfer for liquid metals, so that it can be incorporated into the more or less standard theoretical methods to give heat transfer coefficients which are in reasonable agreement with experimental facts"--from introduction.

Abstract: "The self-consistent equations have been found for a plasma which lies in a mainly unidirectional magnetic field, which has a circular symmetry and which has a harmonic variation in the direction of the magnetic field. The equations have been solved in two cases, 1) where the harmonic variation of the field is finite and the plasma is weak, and 2) where the plasma is strong but the harmonic variation of the field is weak. The configurations thus found can form an important starting point for calculations of the stability of plasmas."

Abstract: The Coast Guard initiated a study to determine if a Dump Control Subsystem was feasible for use with an Ocean Dumping Surveillance System. This report contains a summary of the dump mechanisms on various Ocean Dumping vessels and recommended designs for Dump Control Subsystems.

Report of example scenarios and useful equations for determining the production of radioactive isotopes by pile or other radiations.

"In order to evaluate the post combustion behavior of boric oxide, pentaborane-air mixtures, burned to completion at a combustor pressure of 3 atmospheres, were expanded through a 7.1-inch-long convergent-divergent nozzle having a 4-inch-diameter throat and an exit-to-throat area ratio of 1.68. The experimentally determined thrust performance was in good agreement with the ideal equilibrium performance at stagnation temperatures of 3300 deg R and lower. The boric oxide vapor at the combustor exit required about 400 degrees F supercooling before any condensed phase was observed" (p. 1).

From Introduction: "An analysis of an engine having a division of work such that the power of the reciprocating engine is just sufficient to drive the compressor is reported herein. This combination of a reciprocating-type internal-combustion engine that drives its own supercharging compressor and generates gas for further expansion through a turbine will be called a piston-type gas generator in this report."

Report presenting an investigation of a turbojet engine with compressor-inlet total pressure at various values below that of the exhaust pressure to determine engine performance under conditions simulating operation with inlet-duct losses. Results regarding general performance, application to inlet-duct losses, application to airplane boundary-layer control, and application to turbojet-engine thrust control are provided.

Memorandum presenting wind-tunnel tests at high subsonic Mach numbers conducted on a model of a pursuit airplane with a 45 degree sweptback wing. Tests were made to determine the effect of the wing trailing-edge angle, the fuselage contour at the wing-fuselage intersection, and an extension at the leading edge of the wing root.

Report presenting testing on the NACA 16-009 airfoil and on eight airfoils of the NACA 6A series, which shows that the chordwise loading due to lift at a Mach number of 1.0 is insignificantly affected by thickness distribution within the range of airfoil shapes presented and only slightly affected by thickness. Results regarding the experimental loading on symmetrical airfoils, method of estimating pressure distribution, experimental loadings on cambered airfoils, and scope of method are provided.

Report presenting flight measurements on a swept-wing jet aircraft to determine the effects of adding forward camber and an increased leading-edge radius on the low-speed stalling characteristics, the high-speed static longitudinal stability, and the airplane drag. The modified leading edge produced values of maximum lift somewhat greater than the slats on a normal airplane, but the stall was unacceptable because of an abrupt roll-off.

A brief summary is made of the performance of a series of variable-geometry type scoop inlets investigated at the Lewis Laboratory on a model of the X-3 airplane fuselage. Data are presented for a range of inlet mass-flow ratios over a Mach number range from 0 to 2 and from 0 degrees to 12 degrees angle of attack. Rounded-lip inlets are found to give satisfactory performance to a Mach number of 1.5. Use of sharp rather than blunt lip configurations is shown to provide considerable gains in available thrust at Mach number 2.0 but penalize take-off performance to the extent that auxiliary air intakes may be required.

Report presenting the results of an experimental investigation of three plane wings in combination with a body, which represented both low- and high-wing arrangements. The three wings had different plan forms: a tapered unswept plan form, a tapered 45 degree sweptback plan form, and a triangular plan form. Results regarding the effect of Reynolds number and effect of vertical position of the wing are provided.

Report presenting an analysis of two turbojet engines, including the component performance of the compressors and turbines, in order to determine the effect on engine performance and operation of bleeding the compressor to furnish cooling air for the turbine rotor blades. Results regarding the compressor and turbine performance characteristics and engine performance characteristics are provided.

Report presenting ignition-delay determinations of furfuryl alcohol and mixed butyl mercaptans with various white fuming nitric acids were made at several temperatures with a modified open-cup apparatus and a small-scale rocket engine of approximately 30-pounds thrust.

Report presenting data obtained from an investigation of the Douglas-D558-II airplane to determine its buffeting characteristics at high lift and supersonic speeds. From Summary: "Buffeting was encountered at normal-force coefficients greater than about 0.7 in the Mach number range from 0.96 to 1.27 but at Mach number of 1.57, a peak normal-force coefficient of 0.80 was attained with no indication of buffeting. The increase in buffet intensity with lift is very gradual at supersonic speed compared with the buffet intensity-lift variation at subsonic Mach numbers."

Report presenting an investigation to determine the effects on internal performance of several geometric variables intended to produce a short, high-performance convergent-divergent nozzle. Some of the characteristics investigated included variations in the throat-contour radius, combinations of the shape of the convergent section and throat-contour radius, divergence angle, and shape of the divergent section.

Report presenting an investigation at Mach numbers 1.9 and 3.0 to demonstrate that a central core of air of high stagnation temperature can be produced in the test section of a supersonic wind tunnel. This makes performing wind tunnel testing cheaper and controls for more variables. Results regarding the core studies at Mach number 1.9 and 3.0 and diffuser performance at Mach number 1.9 are provided.

Report presenting an investigation performed at Mach number 2.96 to study the effects of some internal boundary-layer-control systems on the pressure recovery and stability characteristics of a side inlet with half a double-shock external compression surface. Counterbody bleed did not appreciably improve the performance of the inlet, and the maximum pressure recovery obtained was 62 percent. Results regarding the inlet performance with internal bleed and inlet performance with flow injection on external compression surface are provided.

Report presenting an experimental investigation of a series of fixed-geometry exhaust nozzles which simulated a variable exit, which was conducted in the 8- by 6-foot supersonic wind tunnel at Mach numbers 0, 0.6, 1.5, 1.7, and 2.0. Gross thrust performance of the long-shroud exit configurations was considerably better than the short-shroud. Results regarding flow coefficients, thrust characteristics, flight performance analysis of data, and shroud drag are provided.

From Summary: "The exhaust of a 6-inch-diameter ram-jet engine mounted in the Lewis 1- by 1-foot, Mach 3.1 supersonic tunnel was scavenged successfully with a 6.6-inch-diameter scoop. Limiting values of exhaust-to-stream static-pressure ratios and scavenge-system total-pressure ratios were determined for complete scavenging of the products of combustion. The scavenge-system operation influenced the engine exhaust-nozzle pressures under conditions of unstable scavenge flow."

From introduction: "This report deals with a part of the research and development studies which preceded the manufacture of fuel elements for the Gas Cooled Reactor Experiment (GCRE)." The studies evaluate the effects of varying the type and size of UO2 particles, stainless steel matrix powders, blending procedures, compacting pressures, sintering times, temperatures and atmospheres, roll-cladding temperatures and reduction rates, total cold reduction, and heat-treating times and temperatures has been made for UO2 stainless steel dispersion fuel elements."

"An investigation was made into the various processes for the fixation of mixed fission products as solids in order to determine the extent they could be utilized as heat sources for thermoelectric generators. Generators of up to ten watts can be designed and built with state-of-art'' thermoelectric materials and mixed fission products soon to be available from the ldaho Falls calcination pilot plant. Mixed fission products from other processes and plants to be on stream'' in this decade will be capable of fueling practical generators into the kilowatt range using thermoelectric materials available in the same time period. A survey was made on current research and development efforts on waste fixation processes. Studies showed that a wide range of power densities (from 0.002 to 0.2 watts per cubic centimeter) will be available from calcined fission product wasted. An experimental program for the consolidation of low density, Idaho Chemical Processing Plant alumina type wastes is reviewed. Preliminary results indicated that densification factors of three to four are readily obtainable for such wastes."

The Spectroscopy Research Laboratory is concerned with research and development in the fields of nuclear magnetic resonance, microwaves, infrared and optical spectroscopy, spectrochemistry, and x rays. Research is directed toward fruitful methods of isotope analysis; new element and compound analytical methods having application to immediate Laboratory or long-range commission needs; and fundamental research on isotopes, elements, and compounds. The work is reported on a project basis to give a more complete picture of the purpose, activity, and status of each program. More detailed information on reported or inactive projects may be obtained from the previous semiannual report.

The theoretical and practical aspects of the accelerating mode (TM01) in iris-loaded waveguides have been covered extensively in many reports and publications. The pulse shortening observed in linacs and the possible application of an iris-loaded waveguides as the deflecting structure for rf particle separators stimulated the interest in the nature of higher order modes. Some experimental results on higher order modes in iris-loaded waveguides are available in references. Results of studies done at CERN are not yet published; they were however communicated to the authors and represented the basis of work done at Brookhaven. A preliminary account of BNL results was given in reference. The purpose of this report is to describe the model measurements which were necessary to determine the geometry of a brazed or electroformed prototype for a deflecting waveguide. At the same time, a systematic investigation of other than the deflecting mode was done to ensure a nondegenerate field solution at the operating frequency. The measurements are compared with computational results obtained on the IBM 7090 at BNL.