From introduction: "During the second quarter of fiscal year 1952, the Isotope Production and Process Development Department placed primary emphasis on the collection of lithium, iron and calcium isotopes."

From summary: "During 1951 NDA has, at the request of ORNL, been studying the supercritical-water reactor as proposed for aircraft propulsion in Wash-24...This study has concerned itself only with the reactor and shield." The report describes the reactor and the processes involved in developing it. The goal of the development of this reactor is identified as a path to supersonic flight.

This study soughs to determine the x-ray activity of two samples of stainless steel prepared from tubing used in the ANL-140, in-pile experiment (P-13). This information is necessary in order to predict the activity of the P-13 rig at the time of removal. The primary contribution to the over-all activity will be from Ta{sup 181} and Co{sup 59} impurities.

Introduction: "Knowledge of the mechanical properties of uranium at elevated temperature is essential in order to understand and predict the fabrication characteristics and pile behavior of this metal. This report presents the experimental data obtained from beta heat-treated specimens which were originally machined from one production, alpha-rolled uranium rod."

Report discussing the details of a radiation burst in a spherical reactor using plutonium nitrate fuel that occurred on November 16, 1951 at Hanford Works.

Since the issuance of HW-17398, Separations Section Operating Standards - Part I relating to the Bismuth Phosphate Process on March 1, 1951, several changes in the process have been found desirable and have been reduced to practice. This document presents these changes.

From abstract: The subsurface isorad method is an attempt to locate areas favorable for uranium ores by the use of contour maps which show localities having greater radioactivity. The construction of isorad maps entails the measurement of the area under the curve of a gamma-ray logo The figures obtained indicate relative amounts of gamma radiation and are used to locate the isorad contours. This work was started at Temple Mountain in the San Rafael Swell area during the spring of 1952. The purpose of this investigation is to determine the most effective and economic hole spacing for subsurface isorad work.

Fission product activities and heat generated by fission product decay as a function of time, in waste solutions obtained by processing uranium irradiated under the present Hanford schedule, were calculated. From these data, curves showing expected heat evolution in stored Redox Process Wastes, during and following filling of the waste tanks, were prepared assuming various modes of operating the plant and various production rates. Total heat available for evaporation of water from the tanks was also determined. Under the most favorable plant operating conditions considered, calculated heat available for evaporation will be sufficient to reduce the waste volume by a factor of two. Experimental work showed that the wastes may be reduced in volume (evaporation) by a factor greater than four. Thus, supplemental heat would be required to attain the maximum volume reduction.

From Introduction: "The Ames Aeronautical Laboratory has in progress an experimental investigation of the aerodynamic characteristics of wings of interest in the design of high-speed fighter aircraft. This program included an investigation in the Ames 6-by 6-foot supersonic wind tunnel at both subsonic and supersonic Mach numbers of a wing-body combination having a 3-percent-thick, unswept, tapered wing with circular-arc sections and an aspect ratio of 3.1 (reference 1).

"The rocket-propelled-model technique has been applied to the investigation of low-lift buffeting. Results of preliminary tests show that severe buffeting, wing dropping, and normal-force changes occur almost simultaneously near zero lift over a Mach number range near 0.9 on unswept wings 12 percent thick. On unswept wings 7 percent thick, buffeting did not occur; however, mild wing dropping and normal-force changes were experienced" (p. 1).

Report presenting an investigation of an air-cooled internal-strut-supported blade in a modified production turbojet engine to determine the cooling effectiveness of this type of blade and the cooling-air pressure loss through the blade under engine operating conditions. Experimental results are presented and compared with the results of an analytical investigation.

Report that is part of a program to investigate the aerodynamic characteristics in pitch, yaw, and steady roll of various model configurations with variations in the wing geometric parameters. The paper presents the aerodynamic characteristics in pitch of wing-fuselage combinations with wings of aspect ratio 4, taper ratio of 0.6, and sweep angles varying from 3.6 degrees to 60 degrees. Results regarding lift characteristics, pitching-moment characteristics, drag characteristics, and lift-drag ratios are provided.

Report presenting testing of rocket-powered models at supersonic speeds to determine some of the surface conditions on the zero-lift drag of fin-stabilized parabolic bodies of revolution. Two types of models and three types of surface roughness were tested. Results regarding mean-drag coefficients, side-pressure coefficients, and total-drag coefficients are provided.

Report presenting testing of the zero-lift drag of several wings at supersonic Mach numbers. The delta wings had the lowest drag over the entire Mach number range. Results regarding the variation of Reynolds number with Mach number, total drag coefficient, wing-plus-interference drag coefficients, and skin friction drag are provided.

Memorandum presenting an investigation of the static aerodynamic and dynamic damping-in-roll characteristics of an aircraft rocket with cruciform fins of trapezoidal plan form as determined experimentally at a range of Mach numbers. The fins had tow holes cut through each fin panel, and the effects of the holes or slots were investigated by testing with both solid and slotted fins.

Testing occurred using the NACA wing-flow method at a range of Mach numbers to determine the aerodynamic characteristics of three triangular wing-fuselage models which differed only in wing thickness-chord ratio. The wings had an aspect ratio of 2.31 with 6-, 9-, and 12-percent-thick biconvex sections and a fuselage with a fineness ratio of 12. Results regarding the normal force, chord force, and pitching moment for various angles of attack.

"A modified triangular wing of aspect ratio 2.53 having an airfoil section 3.7 percent thick at the root and 5.98 percent thick at the tip was designed in an attempt to improve the lift and drag characteristics of triangular wings. Free-flight drag and stability tests were made using rocket-propelled models equipped with the modified wing. The Mach number range of the test was from 0.70 to 1.37" (p. 1).

Report presenting an investigation to determine the effects of sweepback and taper ratio on the cavitation and hydrodynamic force characteristics of hydrofoils. Four hydrofoils were used, all of which had different taper ratios and degrees of sweep. Results regarding the effect of cavitation on hydrodynamic characteristics, effect of sweep on cavitation and force characteristics, effect of taper ratio on cavitation and force characteristics, and a comparison with wind-tunnel data are provided.

The process tube assembly functions to provide a water-cooled channel through the reactor into which uranium slugs are inserted for processing. The channel consists of a cylindrical tube with 2 ribs towards the bottom of the inside diameter which supports the slugs in a central location. Thus providing an annular space around the slugs for the cooling water used to remove the heat generated by fission of the uranium. Because of the relative movement between the graphite and the biological shield as the result of graphite growth and thermal expansion, the portion of the process tube which extends through the biological shields at the front and rear faces must be protected against sharp bends that would prevent movement of the slugs through the tube. This requires a design which will permit such relative movement, and maintain shielding around the opening through the shield. In addition, the process tube assembly requires provisions for introducing the cooling water flow at each tube at the inlet or front face and for discharging the coolant at the outlet or rear face. Provisions are also required for opening the tube at the inlet and outlet faces to charge and discharge the slugs. This paper discusses …

The following document focuses on the study of the absorption spectra of americium chloride. Large samples and a spectrograph of great dispersion were used.

Abstract: "A rapid yet safe method for the dissolution of sodium-potassium alloys prior to chemical or instrumental analysis has been devised. The alloy is submerged beneath the surface of an inert organic reagent and dissolved at a controlled rate by adding methanol drop-by-drop. A blanket of inert gas is maintained over the reaction flask. The procedure has been successfully used to dissolve samples of NaK in the range of 0.05 to 25 grams."

From introduction: "A simplified calculation has been carried out in order to gain some insight into the flux distribution, peak to average power density, efficiency of a catching blanket and the effect of a reflector in the proposed converter reactor."

The distribution coefficients of Pu(VI) and Pu(III) have been measured as a function of the TTA, hydrogen ion, and nitrate ion concentrations in the TTA-benzen-nitric acid system. The extraction constants for Pu(VI) and Pu(III) are 1.4 X 10(-2) and 2 X 10(-5), respectively.

"Tests have been made at the Langley Aeronautical Laboratory on a 6000-horsepower propeller dynamometer installed at a ground test facility to determine the effect of a half-scale model of the Wright Aeronautical Development Center 30,000-horsepower whirl rig upon the aerodynamic characteristics of a three-blade NACA 10-(3)(062)-045 propeller. The model of the whirl rig was mounted in front of the 6000-horsepower propeller dynamometer. Static propeller tests were made for 0deg, 5deg, 10deg, 15deg, and 20deg blade angles over a range of rotational speeds from 600 to 2200 rpm in 100-rpm increments" (p. 1).