Summary: "The low carbon 18-8 stainless steels containing approximately 1.7 per cent boron used for vertical safety rods at Hanford were found to be structurally stable in the temperature range 0-450 C. The addition of boron decreases the stability of this metastable austenitic alloy. Sufficient ferrite formation is induced by sub-zero temperature treatments to result in dimensional changes and a magnetic alloy. The difficulties encountered in machining this material are believed to be due primarily to segregation in the castings resulting in small areas of the hard intermetallic compound, FeB."

This report presents a brief review of reports concerning radiation hazards in the event of various reactor accidents. Conclusions regarding tolerance distance are reported.

Experiments are described in which the change in thermal conductivity of U-impregnated graphite under neutron irradiation was measured. Thermal resistivities relative to the thermal resistivity of undamaged impregnated graphite are reorted as functions of exposure. From applications of the expermental results to the North American Aviation low-power research reactor the peak tem. of the core is determined for a given reactor power and time of operation.

Weekly report discussing the state of the raw sugar market, including details for prices and market fluctuations related to weights in tons, regions, distribution, years, and figures.

The Bevatron status is: (1) Physical structure of magnet now assembled and being tested. Initial pulsing to rated field currents indicate that magnet is performing as designed. Currents of the order of 8500 amps peak have already been rendered. (About 15,000 gauss). (2) Pumpdown time to approximately 10{sup -5} mm Hg is of the order of 24 hours at present but is expected to improve to 12-15 hours as the high vapor pressure solvents are removed. Lofgren and Brobeck expect that it will be possible to make interval target, etc., changes between operating shifts without excessive loss of experimental time. (3) Injector and linear accelerator are now operating stably. Injected currents to Linac are approximately 3 x 10{sup -3} peak at 450 kev. Linac output is approximately 5% or 70 x 10{sup -6} amps peak with an angular divergence of 10{sup -3} rad. and a maximum energy spread of less than 0.8% at 9.8 kev. (4) Inflector and induction electrodes are to be installed after December 15, 1953. (5) Complete machine, both mechanical and electrical, will be ready for testing and 'de-bugging' approximately December 15; 1953. Initial operation as a research instrument should begin after the first of the year, …

Daily cash report for Imperial Sugar Company including a list of large withdrawals for the months surrounding the date showing the daily expenses and estimated balance for each entry. It also lists scheduled payments for bank loans.

Report of theoretical values of performance parameters for liquid hydrogen and flourine as a rocket propellant for a wide range of fuel-oxidant and expansion ratios. Parameters computed include specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity.

Report presenting an investigation to determine the effect of blade-section camber on the stall-flutter characteristics of three propellers using a 6000-horsepower propeller dynamometer. Up to a certain blade angle, there was an increase in flutter-speed coefficient with an increase in blade-section design lift coefficient. An increase in thrust was found to lead to an increase in tip Mach number in the flutter region of the propeller blades.

"Convective heat-transfer coefficients in dry air were obtained for an ellipsoidal spinner of 30-inch maximum diameter for both stationary and rotating operation over a range of conditions including airspeeds up to 275 miles per hour, rotational speeds up to 1200 rpm, and angles of attack of zero and 4 degrees. The results are presented in terms of Nusselt numbers, Reynolds numbers, and convective heat-transfer coefficients. The studies included both uniform heating densities over the spinner and uniform surface temperatures" (p. 1).

Memorandum presenting a direct-connect duct investigation conducted with a one-quarter segment of a 25.5 inch diameter annular combustor which had been previously developed for liquid fuel injection. The combustor was modified by changing the fuel injectors and the liner design for vapor fuel injection. Results regarding accuracy and reproducibility, combustion efficiency, combustor-outlet temperature profiles, and pressure losses are provided.

Report presenting a low-speed wind-tunnel investigation to determine the longitudinal aerodynamic characteristics of a thin delta wing equipped with various arrangements of double slotted, single slotted, plain, and split flaps. The wing was a flat plate with beveled leading and trailing edges and had a maximum thickness ratio of 0.045, and 60 degrees sweepback of the leading edge.

From Introduction: "As part of a comprehensive investigation of the J40 turbojet engine conducted at the NACA Lewis altitude wind tunnel, the steady-state engine performance of the prototype J40-WE-8 turbojet engine without afterburner was obtained and is presented herein. A basic redesign of the compressor and other modifications in the compressor and the combustor were incorporated in the XJ40-WE-6 turbojet engine (references 2 and 3). In this report the modified engine is designated "the prototype J40-WE-8 without afterburner."

Theoretical values of performance parameters for liquid hydrogen and liquid fluorine as a rocket propellant were calculated on the assumption of equilibrium composition during the expansion process for a wide range of fuel-oxidant and expansion ratios. The parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ration of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity. The maximum value of specific impulse was 364.6 pound-seconds per pound for a chamber pressure of 300 pounds per square inch absolute (20.41 atm) and an exit pressure of 1 atmosphere.

Report presenting an investigation to determine the effects of pouring temperature and grain size on the uniformity of lives and initial failure times of groups of AMS 5385 gas turbine blades and to relate the individual lives of the blades to grain size. This is due to the fact that the uniformity of lift of cast alloy gas-turbine blades is generally unsatisfactory. Results regarding the metallurgical examination are provided.

Report presenting an experimental investigation using a 16-inch impulse-type supersonic-compressor rotor as a separate component, which obtained a maximum total-pressure ratio of 5.42 and an adiabatic efficiency of 0.76 at 101-percent design speed. The rotor could operate over a wide range of back pressures, but it did not obtain the design impulse condition. Results regarding the rotor-component investigation and stage investigation are provided.

Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 to determine the static longitudinal stability and control characteristics of a 1/16-scale model of the Douglas D-558-II research airplane. The results indicated a high degree of longitudinal stability that decreased slightly with increasing Mach number and lift coefficient.

Report presenting a flight investigation of a small, all-movable tail to determine whether it is an effective longitudinal control for a cruciform, delta-wing missile at a range of Mach numbers from 0.67 to 1.81. The stability, control, hinge-moment, and drag characteristics are provided.

Report presenting a direct-connect duct investigation conducted with a one-quarter segment of a 25.5-inch-diameter annular combustor that had been developed for liquid fuel injection. The combustor was modified by changing the fuel injectors and liner design for vapor fuel injection. Results regarding accuracy and reproducibility, combustion efficiency, combustor-outlet temperature profiles, and pressure losses are provided.

An experimental investigation of the performance of a single-conical-shock diffuser was conducted at a Mach number of 5.4 and a Reynolds number based on model diameter of 375,000. Total-pressure recoveries of 13.7 and 13.1 percent were obtained at angles of attack of 0 degrees and 3 degrees, respectively. The corresponding kinetic energy efficiencies were 86.4 percent at an angle of attack of 0 degrees and 86.0 percent at an angle of attack of 3 degrees.

Report presenting the aerodynamic characteristics of several wing-fuselage combinations measured at a Mach number of 0.25. Each combination consisted of a triangular wing with an aspect ratio of 2.0 and body of revolution with a fineness ratio of 12.5. Results regarding wings in the presence of bodies, wing-body combinations, and dorsal fins are provided.

Report presenting testing of a wing with 0 degree sweepback of the 0.25-chord line in combination with a body of revolution at Mach numbers from 0.60 to 1.11 for angles of attack up to 24 degrees. Results regarding lift characteristics, pitching moment, drag characteristics, and lift-drag ratio are provided.

Report presenting an investigation to determine the performance of 17 cooling-air ejectors at primary-jet pressure ratios from 1 to 10, secondary pressure ratios to 4.0, and a temperature ratio of unity. Results regarding pumping characteristics, effect of spacing ratio on pumping, effect of diameter ratio on pumping, thrust characteristics, effect of spacing ratio on thrust, effect of diameter ratio on thrust, comparison of cylindrical and conical ejectors, comparison of performance with small model ejectors, and a comparison of performance with full-scale installation are provided.

Report presenting an investigation in the high-speed tunnel to determine the effects on the chordwise pressure distributions of deflecting a flap-type aileron on a swept wing. The semispan 35 degree sweptback wing had an NACA 65A006 airfoil section, an aspect ratio of 4, and a taper ratio of 0.6.

An investigation of the performance characteristics of annular-diffuser designs applicable to turbojet afterburners. The best vortex-generator installations improved the diffuser static-pressure rise and downstream radial distributions without significantly altering the loss coefficients. Results regarding the axial inlet flow and whirling inlet flow are provided.