A computer analysis of NURE-HSSR data.

LRL has the responsibility of demonstrating the feasibility of a reactor for use as a power plant for a low-altitude, high-Mach-number missile. This reactor is literally a very high power air heater which must work at temperatures in excess of 2000' F. The reactor is exposed to high loads so one of the primary problems is providing high temperature structure. Considerable effort has been devoted to developing ceramic structural elements. One of the materials considered for this purpose is silicon nitride. In ceramic structural elements operating over large temperature ranges, a major problem is coping with thermal stress. In this respect there is a similarity with the radome problem. The work on silicon nitride at LRL consisted of limited fabrication studies (principally for familiarization), measurement of properties of interest to the application, and funding of fabrication scale-up efforts.

Report documenting "the determination of the thermal stability of various fission product oxides and nitrates, and an investigation of the gas phase decomposition of ruthenium tetroxide" (p. 4).

Report giving tables of the linear contraction relative to 293 ºK, (L293ºLT)/L293, and the linear expansion coefficient, dL/L293dT, of thirty elements, forty-five alloys, twenty-two other inorganic substances and twenty plastics and elastomers in the temperature range, 0 to 300 ºK.

This report summarizes the research and development work carried out during December, 1959, and January and February, 1960, for Budget Activity 2790 - Separations Development for Non-Production Reactors. The major effort on Activity 2790 has been completed. Current efforts on the remaining problem areas will enable Hanford to begin reprocessing fuel elements from power reactors which employ depleted or slightly enriched uranium fuels in July, 1962.

Description of Purex plant process for irradiated uranium for the separation and decontamination of plutonium and uranium from each other and from fission products.

The thickness of an oxide film on phosphor bronze helices was determined by first establishing the oxygen content of the helix "as received" and after cleansing with nitric acid. Based on the assumption that the difference between these two values was the oxygen in the film, and that the film consisted entirely of cupric oxide, the thickness of the film was calculated from the density of cupric oxide, weight of the film, and surface area of film. A value of 1080 A was calculated as the thickness by this method.

The final percentage of xenon created by fission in uranium and plutonium is a function of the neutron flux intensity. The flux dependence results because axenon 133 and 135 can be converted to a a stable xenon isotope by neutron capture instead of decaying into cesium.

The 0.045m UO2SO4, 0.036m CuSO4, 0.025 m H2SO4 solution (HRT fuel composition) was chemically stable during 1, 866hr of operation at 280ºC and 1500 psi. The system was pressurized by boiling a 0.4 gpm stream of the fuel in a titanium heat exchanger at 313ºC.

Technical report describing the process to determine the fusion welding characteristics of Haynes Alloy #25 as applied to TLJ-100530, Corrosion Loops. Hayes Stellite Alloy #25 is a cobalt-base alloy for corrosion resistant high temperature applications. This material, when welded by the inert gas shielded tungsten arc method, produces sound ductile joints. Material thicknesses greater than 12 gauge require standard joint preparations, a V joint being preferred up to 1/4 inch and a U joint for greater thicknesses. Welding heat should be kept to a minimum followed by fast cooling. The molten metal is very fluid and may present difficulties when position welding.

Abstract: "Neutron nonelastic cross sections measured at different detector biases have been used to determine the cross sections for inelastically scattering 14 Mev neutrons into 9- to 14-Mev energy range. The cross section for producing these high energy neutrons, which may be attributed to direct interaction processes, is roughly 10% of the nonelastic cross section, for all elements. A comparison is made with data of Coon and co workers, who measured angular distributions for the same high-energy inelastically scattered-neutron group."

This is a bibliography referencing documents based on fused lithium salts within the years 1950-57.

Abstract: "Neutron nonelastic cross sections have been measured for 23 elements at 14 Mev, and for a selected set of these elements over the energy ranges 7 to 14 Mev and 21 to 29 Mev. Conventional sphere transmission techniques were used for the measurements. A comparison with optical model calculations of Bjorklund and Fernbach shows excellent agreement."

Report presenting an investigation in the 10- by 10-foot supersonic wind tunnel to evaluate the performance of a shrouded injector burner with perforated domes employed in a 28-inch ramjet using gaseous hydrogen as fuel. Steady-state data were obtained at a pressure altitude of 77,000 feet and zero angle of attack. Results indicated that burning could be initiated under severe distortion conditions and that satisfactory combustor operation was accomplished up to a pressure altitude of 110,000 feet with no adverse effect on combustion efficiency.

Memorandum presenting an investigation conducted in the 10- by 10-foot supersonic wind tunnel to evaluate the performance of a shrouded injector burner with perforated domes employed in a 28-inch ramjet using gaseous hydrogen as fuel. Steady-state data were obtained at a pressure altitude of 77,000 feet and zero angle of attack. Results of the investigation showed that burning could be initiated under severe distortion conditions and that satisfactory combustor operation was accomplished up to a pressure altitude of 110,000 feet with no adverse effect on combustion efficiency.

The following report follows an investigation made to determine the composition of uranium-rich ternary eutectic alloys most suitable for reactor application in the as-cast condition. These determinations were made based metallographic examination and thermal analysis of as-cast alloys.

A study of the fabrication failures for zirconium and zircaloy-2 process tubes was made. In the tube reducing operation, a non-uniform reduction in area for the cross section was found to be a major cause of failure. In annealing studies, a cycle of 2 hours at 820 deg C in vacuum followed by furnace cooling produced the greatest ductility of extruded zircaloy-2 for the annealing treatments studied. The ductility of cold worked and annealed zircaloy-2 was found to be superior to that of extruded and annealed material. The strain rate of a cold working process was found to affect the ductility of zircaloy-2.

It is proposed to test gaps corresponding to deuteron energies in the range of 0.45 to 4.5 Mev. The accelerator to be modeled is a 48 mc/sec cylindrical cavity in the TM010 mode with [formula] repeat length, [formula] gap, 0.25 megavolt per cavity foot peak r.f. gradient and strong focusing magnets alternating polarity at each drift tube.

Report presenting an investigation of the aerodynamic loading characteristics of a wing-fuselage combination in the slotted test section of the transonic tunnel. The test was part of a systematic investigation of the effects of varying the amount of sweepback on wings in order to determine their suitability for transonic flight. Results regarding span load characteristics, normal-force characteristics, wing-tip angle of twist, spanwise distribution of section pitching-moment coefficient, pitching-moment characteristics, and fuselage characteristics in presence of wing are provided.

Memorandum presenting results obtained from time-history records of normal accelerations, airspeed, and altitude. Additional data have been obtained from the operations of two types of commercial transport airplanes together with data on two other types of transport airplanes.

Report presenting the application of an aerodynamically pulsed horizontal tail to determine experimentally the longitudinal aerodynamic characteristics of a rocket-powered model in free flight. Results regarding time history, lift and drag, and tail effectiveness and downwash are provided.

Report presenting flight measurements in sideslips of the static lateral and directional stability characteristics of the Douglas D-558-II airplane. It is part of an investigation to determine the stability and control characteristics and aerodynamic loads acting on the wing and horizontal tail of an airplane from stalling speed up to a maximum Mach number of 0.90. Results regarding variations of rudder, total aileron, elevator control positions and control forces, aileron position, and aerodynamic hinge moments are provided.

Report presenting the aerodynamic properties of a model of a jettisonable nose section with a circular cross section as determined at low speed from an investigation in the 20-foot free-spinning tunnel. The results indicated that the aerodynamic characteristics of the nose were greatly affected by proximity to the fuselage. Even for a stabilized nose, it may be necessary to eject the nose forward forcibly in order to prevent high accelerations along the backbone of the pilot.

Report presenting an investigation to evaluate the effects of split flaps, elevons, sharp leading edges, drooped-nose flaps, and extended-nose flaps on the lift, drag, and pitching-moment characteristics at low speed of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees and an aspect ratio of 3.5. Results regarding the plain wing and wing-fuselage combinations, Reynolds number, split flaps, elevons, leading-edge devices, and highest lift coefficient attained before longitudinal instability are provided.