In studies of the fabrication of fuel subassemblies for the supercritical-water reactor, the limited ductility of stainless steel-UO₂ fuel sheet made the fabrication of corrugated-flat-plate-type subassemblies impractical. A fabricable MTR-type assembly, 5/8 in. square and 30 in. long, was developed. Methods for edge cladding fuel sheet were developed and a brazing alloy, GE-75, was found to be corrosion resistant in supercritical water.

Abstract: "Small amounts of acetic acid, equivalent to 400 ul. of 0.3 to 0.13 g/L. can be titrated coulonatrically in the presence of a 10 to 25-fold excess of HN03 in 70%, isopropanol. An accuracy of +/- 0.1% and a precision of +/- 8.5% (99% limite) are obtained.

Report discussing a model of a delta-wing configuration with four engines mounted two to a nacelle below the wing that was tested a variety of Mach numbers and Reynolds numbers. The wing static-pressure coefficients, wing pressure coefficients, and lift coefficient of different configurations are described.

Report presenting an investigation to determine the effects of forging at 1950 degrees and 2150 degrees Fahrenheit as well as the effects of several heat treatments on the performance of Inconel 550 in a turbojet engine. Differences in engine performance of the different turbine blades could not be associated with consistent differences in microstructure or grain size. Results regarding blade performance, blade elongation during engine operation, microstructure of as-heat-treated blades, grain size, metallurgical studies of failed blades, stress-rupture tests, and hardness are provided.

Report presenting an impulse-type supersonic compressor designed for turning to the axial direction that was tested in air with three different sets of stator blades at eight angle settings.

Memorandum presenting a determination of the effects on engine performance of using turbojet engines for boundary-layer control by suction at the engine inlet or by bleeding air from the compressor outlet for three current production engines. Results regarding bleed, suction, and variable-area turbine are provided.

Memorandum presenting the flow characteristics of two supersonic-impulse-turbine-blade sections designed for a turning angle of 160 degrees. Results regarding the full-contour blade, free streamline blades, and a comparison of the performance are provided.

Report presenting an investigation to determine the effects of flap size and location on an unswept semispan wing in combination with a half-fuselage. The wing had an aspect ratio of 2.5, a taper ratio of 0.625, and 6-percent-thick modified double-wedge airfoil sections. Results regarding wing characteristics and flap characteristics are provided.

Memorandum presenting an exploratory investigation to determine the aerodynamic effects of camber on a 60 degree apex delta-wing model conducted in the 300 mph 7- by 10-foot tunnel. Camber variation was accomplished through the deflection of full-span round and 25 degree beveled leading-edge flaps on a flat-sided triangular plan-form wing.

Report presenting an investigation of the low-speed longitudinal, lateral, and directional stability characteristics if a 1/4-scale model of a preliminary Bell X-5 airplane design with modifications to the basic model configuration. Results regarding the dive brakes, trailing-edge fillets, extended wing tips, fences, wing incidence, and fins are provided.

Report presenting low-speed tests of an airfoil model with a freely hinged flap attached to spoilers which passed through slots in the airfoil ahead of the hinge line. Testing indicated that buzz is not caused simply by buffeting of a flap by separated flow. Results regarding the oscillations experienced with the spoiler and flap in several positions are provided.

Report presenting an analysis of the problems associated with matching secondary-air requirements of ejector exhaust nozzles and auxiliary inlets has been made for free-stream Mach numbers up to 2.0. The analysis indicated that inlets located in the free stream supply higher pressure recovery than ejectors generally require for optimum net internal thrust at Mach numbers above about 1.4. Net-thrust gains can be achieved by immersing the auxiliary inlet in a boundary layer where the inlet-momentum penalty is less.

These logs record the subsurface stratigraphy and correlate the geologic formations.

"Time of flight spectrometers for the study of neutrons emitted in charged particle reactions have become important in recent years, following the development of suitable photomultiplier tubes and electronic circuits for nanosecond (ns) timing measurements. The principle of operation is simple. The particles exciting the nuclear reactions in which the neutrons are produced fall on the target in bunches of the order of a nanosecond in width. the arrival of product neutrons at a organic scintillation counter (proton recoil) detector placed a few meters from the target gives signals which can be used to determine the flight time of the neutrons from target to detector. A time-reference pule corresponding to the arrival of beam pulses at the target is required."

The flux standard is a device which will give a known flux-linkage change to be used as a calibration. At the Radiation Laboratory, two types of flux standards are used, a stationary type and a portable type.

From Abstract: "This document is the final report of research carried on in the Electron Physics Section of the National Bureau of Standards during the period from February 1, 1955 to March 1962 in developing an electron optical method for the visualization of low-pressure gas flow."

Report documenting the measuring of strontium-90 levels contained in the bones of children and adults of various age brackets across the United States.

Abstract. Some diffusion parameters of water are computed with various thermal-neutron scattering laws. It is found that the diffusion cooling coefficient, in particular, is reasonably sensitive to the scattering law, but that the diffusion cooling coefficients predicted by the Radkowsky and Nelkin kernels are in fortuitious agreement. The coefficients computed for the Nelkin kernel, when treated in a manner consistent with the way in which experimental data are treated, are in reasonable agreement with the results of a recent experiment.

Report discussing a comparison between a centrifugal-flow-type turbojet engine with an adjustable-area exhaust nozzle and with a series of fixed-area nozzles of various throat diameters. The adjustable-area nozzle was found to be as efficient as the fixed-area nozzles in testing. Information about the corrected static thrust, fuel flow, and tail-pipe gas temperature for both types of nozzles is provided.

Report presenting a study of the flow characteristics of two supersonic-impulse-turbine-blade sections designed for a turning angle of 160 degrees. The primary difference between the two sections was the cutting away of a large portion of the convex surface and the presence of a free streamline as the boundary of flow in the passage. Results regarding the full-contour blade, free-streamline blade, and a comparison of the two are provided.

Report presenting the status of spin research for recent airplane designs as interpreted. Some of the major problem areas discussed include interpretation of results of spin-model research, analytical spin studies, techniques involved int he measurement of various parameters in the spin, effectiveness of controls during spins and recoveries, influence of long noses, strakes, and canards on spin and recovery characteristics, and correlation of airplane and model spin and recovery characteristics.

Report presenting an investigation of a free-flight model of a delta-wing configuration with four engines mounted two to a nacelle below the wing with rocket turbojet simulators operating at a range of Mach numbers. Results regarding wing pressure coefficients, fuselage pressure coefficient, airplane aerodynamic characteristics, and airplane trim are provided.

Flow-metering devices used by the NACA and by the manufacturer of the J33 turbojet engine were calibrated together to determine whether an observed discrepancy in weight flow of approximately 4 percent for the two separate investigations might be due to the different devices used to meter air flow. A commercial adjustable orifice and a square-edge flat-plate orifice used by the NACA and a flow nozzle used by the manufacturer were calibrated against surveys across the throat of the nozzle. It was determined that over a range of weight flows from 18 to 45 pounds per second the average weight flows measured by the metering device used for the compressor test would be 0.70 percent lower than those measured by the metering device used in the engine tests and the probable variation about this mean would be +/- 0.39 percent. The very close agreement of the metering devices shows that the greater part of the discrepancy in weight flow is attributable to the effect of inlet pressure.

A vane-type angle-of-attack indicator suitable for measurements at both subsonic and supersonic speeds has been developed by the National Advisory Committee for Aeronautics. A brief history is given of the development, and a wind-tunnel calibration of the indicator is presented, together with a discussion of the corrections to be applied to the indicated readings.