"Yields of N¹⁷ relative to that produced in LiF have been measured in the 190-Mev deflected deuteron and the 380-Mev alpha beams of the 184-inch synchrocyclotron. The measurements have been performed in all the light elements from 0 through V, with the exception of Sc and the noble gases. In addition, yields were measured in the separated isotopes of Mg...Comparisons are made with other types of yield studies performed with neutrons and protons, and the areas of agreement are noted."

From Summary: "Icing and drag investigations were conducted in the NACA Lewis icing research tunnel employing a combination thermal-pneumatic de-icer mounted on a 42-inch-chord NACA 0018 airfoil. The de-icer consisted of a 3-inch-wide electrically heated strip symmetrically located about the leading edge with inflatable tubes on the upper and lower airfoil surfaces aft of the heated area. The entire de-icer extended to approximately 25 percent of chord. A maximum power density of 9.25 watts per square inch was required for marginal ice protection on the airfoil leading edge at an air temperature of 00 F and an airspeed of 300 miles per hour."

Report presenting an investigation of thrust augmentation by injection of water and water-alcohol mixtures in the combustion chambers at sea-level zero-ram flight conditions on 4000-pound-thrust axial-flow and centrifugal-flow turbojet engines. Thrust augmentation, compressor characteristics, fuel flow, and turbine-outlet-temperature distributions are presented for various injection rates and water-alcohol mixtures.

Report presenting an investigation to determine the low-speed large-scale characteristics of an aspect ratio 3 triangular-wing airplane model. The model consisted of the wing in combination with a fuselage of fitness ratio 12.5, a thin, triangular vertical tail with a constant-chord rudder, and a thin, unswept, all-movable tail.

The results of fuel-air ratio and temperature surveys made in the flame stabilizing zone of a 16-inch ram-jet combustor indicated that the distribution of combustible mixture immediately downstream of a flame holder should be mechanically controlled if a preferred mixture composition is to be maintained in that zone. A sloping-baffle combustor configuration gave combustion efficiencies of 90 percent or greater over a range of fuel-air ratios from 0.010 to 0.045.

A method is presented for analysis of the compressible flow between the hub and the shroud of mixed-flow impellers of arbitrary design. Axial symmetry was assumed, but the forces in the meridional (hub to shroud) plane, which are derived from tangential pressure gradients, were taken into account. The method was applied to an experimental mixed-flow impeller. The analysis of the flow in the meridional plane of the impeller showed that the rotational forces, the blade curvature, and the hub-shroud profile can introduce severe velocity gradients along the hub and the shroud surfaces. Choked flow at the impeller inlet as determined by the analysis was verified by experimental results.

Report presenting results of testing of a rocket model with cruciform 60 degree triangular wings in continuous rough air at transonic speeds. The wing arrangement tested appears to be useful for improving the accuracy of the results. Results regarding the characteristics of the rough-air response, variation of acceleration with Mach number, and evaluation of the cruciform arrangement are provided.

Report presenting a low-speed investigation to determine the static and damping derivatives of a 60 degree delta wing, a 45 degree swept wing, and an unswept wing from 0 to 90 degrees angle of attack. Results regarding the static longitudinal stability characteristics, static lateral stability characteristics, damping characteristics.

Report presenting an investigation of the effectiveness and loading characteristics of an aileron mounted on an unswept-wing-body configuration. A flap-type outboard aileron was tested with and without paddle balances at a range of Mach numbers and angles of attack. The aileron effectiveness, hinge-moment parameter, and effect of the paddle balances are presented.

Experiments are described in which the pile-induced changes in electrical resistivity and elastic modulus of graphite were investigated as functions of the sample temperature during bombardment and the amount of bombardment. The data are for relatively low bombardment times (up to ca. 20 L-units) and temperatures (up to 340*C) and are not sufficiently extensive to permit unequivocal conclusions.

The following documents are quarterly progress reports recorded in the chemistry division of the University of California's radiation laboratory.

Much of the shielding work carried out with the Bulk Shielding Reactor (BSR) has yielded data of particular interest for the design of swimming pool type reactors, However, it is often difficult for a reactor designer to locate such data since it may be recorded in a report primarily concerned with shielding problems. Therefore, this memorandum presents a bibliography of reports from the Bulk Shielding Facility arranged according to the application of data to the various aspects of reactor design.

Semiannual Progress report of the Oak Ridge National Laboratory Chemistry Division providing updates on various projects, experiments, and other work in inorganic and physical chemistry, nuclear chemistry, organic chemistry, chemical physics, chemistry of separation processes, radiation chemistry, and reactor chemistry.

Processing of Florida leached zone material for the recovery of alumina.

Report presenting some methods providing sizable reductions in drag for aspect ratios of current interest. The drag savings are maintained over a wide Mach number range, particularly for low-aspect-ratio wings. A significant part of the drag reduction is found to be due to the nonaxisymmetric distortion.

Report presenting an investigation of a four-blade single-rotation propeller in combination with an NACA 1-series D-type spinner-cowling combination at Mach numbers up to 0.83. Characteristics of the propeller operating in the presence of the cowling are compared with the characteristics of the propeller with the spinner.

"An experimental investigation has been made in the Langley stability tunnel to determine the low-speed yawing, pitching, and static stability characteristics of a 1/10-scale model of the Grumman F9F-9 airplane. Tests were made to determine the effects of duct-entrance-fairing plugs on the static lateral and longitudinal stability characteristics of the complete model in the clean condition. The remaining tests were concerned with determining tail contributions as well as the effect of duct-entrance-fairing plugs, slats, flaps, and landing gear on the yawing and pitching stability derivatives" (p. 1).

Report discussing testing of a 60 degree delta-wing configuration with an engine located in a pod contiguous to the underside of the fuselage to determine the effects of the flow field and drag, lift, and longitudinal stability. Jet-on drag coefficients were found to be lower than jet-off drag coefficients at transonic speeds. The transonic-area-rule concept was also found to be viable for predicting jet effects on drag for this type of configuration.

A previous study has been completed on the buildup and decay of xenon poisoning in the PRTR by simulating the reactor as a single region. The results of this study indicated that a study using a more refined model of the reactor would be valuable.

In the past year, exploratory data have been taken to determine the relative solubilities of hydrogen and deuterium in various solvents in the vicinity of room temperature and atmospheric pressure. This investigation is one phase of a program to determine the feasibility of separating deuterium from hydrogen by means of rectified absorption.

This twenty-sixth quarterly report of the research and development activities of the Radiological Sciences Department, Hanford Atomic Products Operation, as before, includes some items charged to control but included for general interest. Such are identified as "not charged to research". The previous report of this series was numbered HW-41026 January 11, 1956.