Quarterly report describing the progress and development of improved zirconium alloys for service in superheated water and steam. This report covers the period between October 1 to December 31, 1961 and was conducted by the United States and the European Atomic Energy Community (EURATOM).

This document will be concerned with the design, operation and maintenance of an automatic fuel element stamping machine. In order to take advantage of automatic unloading and length checking at the Acme-Gridley lathes in the 313 Building, automatic stamping of fuel elements is desirable. This, along with the need for a permanent canning line identification, resulted in a request for a machine to automatically stamp HAPO fuel elements on a production basis.

Organic compounds with high boiling points and low corrosion qualities have been considered for use as reactor coolants and moderators. Those being considered, however, have a greater tendency to leak than does water. A program to evaluate mechanical closures to be used for a leak-tight system for organic fluids has been established. Report HW-59446 covered descriptions of the facility used in this study and the primary results of tests covering two liquids, fittings, and instrumentation. This report will cover final results and other pertinent information.

The decontamination of the present Hanford reactors involves a once-through cleaning operation. Considerable interest has also been shown in determining the feasibility of this once-through technique for cleanup of certain portions of the NPR system. This report contains information on a series of tests performed in the 242-B single pass flow facility. Information concerning the following are presented: (1) Efficiency of decontaminating KER Loop 1 and 2 contaminated specimens. (2) Efficiency of decontaminating present reactor pigtails by different methods. (3) Areas that need further study.

Formulas derived from earlier work satisfactorily predicted low frequency ground effects resulting from the Pre-Gnome explosions, but they not predict high accelerations associated with high frequency ground waves. The Pre-Gnome experiments taken since indicated that accelerations and ground amplitudes are proportional to the explosive charge, but physical conditions limit extrapolation on this basis to relatively low yields. Predicted accelerations resulting from the 10 kt Gnome explosion in potash mines eight or more miles away will be somewhat less than from routine blasts in the mines. The compressional wave speed in the salt stratum of the area is about 14,000 feet per second.

A knowledge of the surface tension of metals is a valuable tool in many aspects of physical metallurgy. Surface tension is a prime factor in such phenomena as swelling, nucleation and growth, and corrosion by liquid metals, and is also of importance in brazing. casting, and sintering. This survey was initiated to facilitate the selection of an experimental technique for determining the surface tension of uranium in support of current swelling studies of irradiated uranium. It is believed that swelling in uranium in support of current swelling; studies of small bubbles of fission gases (krypton and xenon), and the forces resisting the expansion of these bubbles are the elastic and plastic flow energies and surface tension of the metal. Experimental techniques for the determination of surface tension of solids are still in the development stage, but three techniques appear to be most feasible. These methods are: (1) the mechanical method, in which a tensile lead is used to counterbalance the contractile force of surface tension; (2) the thermal etching method, involving measurement of the dihedral angle at the root of etched grain boundaries; and (3) the electron diffraction method, which analyzes surface tension by the amount of lattice distortion it …

Memorandum presenting an investigation in the 7- by 10-foot tunnel to determine the effect of wing-root leading-edge and scoop-type jet-engine air-inlet configurations on the static longitudinal stability characteristics and the duct-flow characteristics of a scale model of the MX-1764 airplane. The addition of the inlet configurations to the model generally resulted in slight reductions in longitudinal stability and increases of maximum lift coefficient.

Report presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine the effect of wing-root leading-edge and scoop-type jet-engine air-inlet configurations on the static longitudinal stability characteristics and the duct-flow characteristics of a model of the MX-1764 airplane. The inlet configurations generally resulted in slight reductions in longitudinal stability and increases of maximum lift coefficient.

Report presenting an investigation in the flutter research tunnel to determine the oscillating forces and moments on a two-dimensional wing equipped with an oscillating circular-arc spoiler. The study indicated that force and moment coefficients and their phase angles are affected by Reynolds number, Mach number, and reduced frequency.

From Summary: "A compilation has been made of available information on the problem of support interference at transonic and supersonic speeds. This compilation indicates that at supersonic speeds there are sufficient experimental data to design properly sting supports and shrouds having negligible interference. At transonic speeds the interference problem becomes more acute, and more experimental information is needed."

Report presenting testing of three scale models and a full-scale configuration of systems for ducting cooling air through a turbojet engine tail cone to a cooled turbine rotor in order to determine pressure-loss characteristics.

Discussing uranium deposits drilled at the Seven Mile Canyon in grand county, Utah.

Report presenting an investigation at transonic speeds using the wing-flow method to determine the longitudinal-control effectiveness and downwash characteristics of a 1/30-scale semispan model of the Bell X-5 airplane with three different degrees of sweepback. Lift, drag, and pitching moment are presented for various angles of attack for several horizontal-tail settings and with the tail off for each angle of sweep tested.

Report presenting the effect of external fuel tanks and externally mounted rocket packets on the drag characteristics of a model of a tailless fighter airplane. Lift, drag, pitching-moment, and rolling-moment coefficients and lift-drag ratios are presented in tabular form and the drag characteristics and lift-drag ratios are also presented in graphic form.

Memorandum presenting the results of a wind-tunnel investigation of the static stability and control characteristics of a model of a fighter airplane employing a low-aspect-ratio swept-back wing with trailing-edge elevons, a swept-back vertical tail, but no horizontal tail. The results indicated that, for the test conditions at which the investigation was conducted, the model, with elevons undeflected, was longitudinally and directionally stable.

Memorandum presenting a thermodynamic method of determining the work input to a centrifugal compressor operating with water injection. The method was used to compute the work input to a double-entry centrifugal compressor, which was operated at a design equivalent impeller speed over a range of inlet-water ratios and varying weight flow.

Report presenting an experimental investigation of the effectiveness of a horizontal tail on two 47.7 degree sweptback wing-fuselage combinations of aspect ratios 5.1 and 6.0. Various combinations of components were tested, including leading-edge flaps, drooped-nose, split flaps, and double slotted flaps, in addition to the flaps-neutral configuration. The primary purpose of the study was to determine the longitudinal stability characteristics of these wings in combination with the fuselage and tail and to determine if the tail is effective in overcoming the unstable variations in pitching moment prior to maximum lift.

Memorandum presenting an investigation on the effectiveness of different slot configurations, which uses the method of making the flow of the cooling air visible. Two methods were used for this purpose: one utilized the traces caused by a reaction between pain spread over the blade surface and a gas mixed with the cooling air, while the second utilized smoke mixed with the cooling air to make it visible. A continuous slot was found to give the best coverage of the cooling-air film.

Report presenting a flight investigation at high subsonic, transonic, and supersonic speeds and at high Reynolds numbers to determine the zero-lift drag of an arrow wing-body combination and of the body without the wing. Results regarding the drag coefficient, Reynolds number, and normal-force coefficient against Mach number are provided.

Ilford type C-2 nuclear research emulsions were exposed in the x-ray beam from the Berkeley synchrotron at four synchrotron energies. The relative yields of the photo-produced nuclear stars were determined as a function of synchrotron energy and prong number.

Memorandum presenting an investigation of the effect of skewed plain nose flaps on a thin, low-aspect-ratio triangular wing in combination with a high fineness-ratio fuselage conducted at low speeds and high Reynolds numbers. The plan form of the flaps was such that the flap chord varied from zero percent of the wing chord at the model center line to 100 percent at about 91-percent wing semispan. The results indicated that the nose flaps provided a significant delay in the occurrence of both the leading-edge type of separation and tip stalling.

Report presenting testing using a Northrop X-4 to obtain stability and control data during airplane acceptance tests. The data includes a time history of a complete pull-up, time histories of several level and accelerated flight runs, and the effect of dive-brake extension on the longitudinal and lateral trim.

The data obtained from the flight of a simplified (dummy) rocket-propelled model of the MX-656 have been analyzed to determine the booster-model characteristics and the model-alone characteristics up to a Mach number of 1.3. The data indicate that the model-booster combination is satisfactory. The model alone is longitudinally stable i n the Mach number range covered by the test (0.9 to 1.3) with the center of gravity at -15 percent of the mean aerodynamic chord. With the stabilizer setting at 0 deg. the variation of normal-force coefficient with Mach number is not large. The total-drag-coefficient variation with Mach number is not unusual. About 12 percent of the total drag at a Mach number of 1.3 can be attributed to body base drag.

Report presenting an investigation at subsonic and transonic speeds in the high-speed 7- by 10-foot tunnel to determine the aerodynamic characteristics of a 42.7 degree sweptback wing with a 20-percent-chord and 50-percent-span outboard aileron. The investigation was performed in transonic flow over a bump on the tunnel floor and in subsonic flow on one of the tunnel side walls.