The following report examines methods to determine uranium nitrate hexahydrate on pretreated hexone in the range of 0 to 40 g./l. by infrared absorption measurements.

"Tests were made of a 1/18-scale dynamically similar model of the Lockheed Constellation airplane to investigate its ditching characteristics and proper ditching technique. Scale-strength bottoms were used to reproduce probable damage to the fuselage. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and fuselage configurations were simulated" (p. 1).

From Summary: "An investigation was made by the NACA wing-flow method to determine the drag, pitching-moment, lift, and angle-of-attack characteristics at transonic speeds of various configurations of a semispan model of an early configuration of the XF7U-1 tailless airplane. The results of the tests indicated that for the basic configuration with undeflected ailavator, the zero-lift drag rise occurred at a Mach number of about 0.85 and that about a five-fold increase in drag occurred through the transonic speed range. The results of the tests also indicated that the drag increment produced by -8.0 degrees deflection of the ailavator increased with increase in normal-force coefficient and was smaller at speeds above than at speeds below the drag rise."

Objective: "The observations summarized in the present report were made to determine the stability of ferrous and sulfamate ions and sulfamic acid in RA Column scrub solution (RAS) and in aqueous solution comparable to the RA Column feed tee composition (RAFS). Knowledge of the stability of the reducing agent (ferrous iron) is necessary to properly plan the method of preparation and introduction of this component into the RA system and to assure dependable and reproducible performance."

"Data on the aerodynamic excitation of first-order vibration occurring in a representative three-blade propeller having its thrust axis inclined to the airstream at angles of 0 degree, 4.55 degrees, and 9.80 degrees are included in this report. For several representative conditions the aerodynamic excitation has been computed and compared with the measured values. Blade stresses also were measured to permit the evaluation of the blade stress resulting from a given blade aerodynamic excitation" (p. 1111).

Report presenting the effect of Mach number on the characteristics of the downwash and wake behind an unswept, tapered wing of aspect ratio 2.67 with full-span, 25-percent-chord, leading- and trailing-edge flaps has been determined from wind-tunnel tests. Results regarding downwash characteristics and wake characteristics are provided.

Report discussing a pressure-distribution investigation of a wing of a supersonic aircraft in the presence of a fuselage at a specified Mach number and aerodynamic chord. The wing had a quarter chord swept back 40 degrees, an aspect ratio of 4, a taper ratio of 0.5, and 10-percent-thick circular-arc sections perpendicular to the quarter-chord line. The results were compared to a similar investigation at a different Mach number.

Memorandum presenting a review of the current and anticipated lubricant problems as related to aircraft turbojet engines, which has indicated that the current and anticipated bearing operating temperature ranges to be met are specified. The most promising approaches, including types of lubricants and temperatures, are provided.

Report documenting the suitability of California for plant locations to produce synthetic liquid fuels, based on raw materials such as oil-impregnated strippable deposits, coal, and natural gas.

Field tests were conducted to measure short-period pollutant concentrations at several stack heights during conditions of marked atmospheric instability and low wind speeds. The source was a mechanical smoke generator located at the 185-ft level of a tower.

Report presenting a large-scale diamond-wing-body configuration flown at a range of Mach and Reynolds numbers. The model had a diamond-plan-form wing with an NACA 65A003 airfoil section, a total aspect ratio of 2.31, and 0 degrees sweep of the midchord. Results regarding zero-lift drag and low-lift longitudinal characteristics are provided.

This report describes the specifications, materials and the sequence of operations used to found and fabricate the first charge of enriched uranium fuel in the Experimental Breeder Reactor.

"Flights to explore the high altitude and Mach number regions were made with the Douglas D-558-II research airplane in August 1951. Maximum pressure altitude recorded was 77,500 feet and the maximum geometric altitude obtained from radar data was 79,500 feet above sea level. The maximum Mach number obtained was 1.87. When a standard atmosphere is assumed, this value represents a true airspeed of 1238 miles per hour; or at the existing temperature, 3 degrees Fahrenheit above standard, this represents an airspeed of 1243 miles per hour" (p. 1).

"A solution to second order in thickness is derived for harmonically oscillating two-dimensional airfoils in supersonic flow. For slow oscillations of an arbitrary profile, the result is found as a series including the third power of frequency. For arbitrary frequencies, the method of solution for any specific profile is indicated, and the explicit solution derived for a single wedge" (p. 611).

A study of the effects of gamma radiation with respect to the formation of nitro-hydrocarbons on the Purex and Redox systems shows that no appreciable formation of nitro-paraffins occurs.

The following progress reports continues the investigation of the HCl-acetone process for extracting uranium, discovering that it is applicable to most Western ores, yielding high uranium recoveries. The economics of the process have been improved by substitution of sulfuric acid for part of the hydrochloric acid requirements.

The stall-limit line at low speeds was improved somewhat by closing the inlet guide vanes 6 deg, while the design-speed maximum flow and pressure ratio were reduced. The first-stage characteristic curve was moved to lower values of both flog coefficient and equivalent pressure ratio. The second-stage pressure ratio was decreased slightly at high speeds, while the later stages were unaffected.

From abstract: Absolute cross sections for the production of charged secondary particles is the bombardments of aluminum, nickel, silver, and gold by 332-Mev protons, 187-deuterons, and 380-Mev alpha particles have been determined.

A preliminary design study, Phase I of the ALPR project, has been made in accordance with the Army Reactors Branch specifications for a nuclear "package" power plant with a 200-260-kw electric and 400 kw heating capacity. The plant is to be installed at the Idaho Reactor Testing Station as a prototype for remote arctic installations. The "conventional" power plant as well as the exterior reactor components are described in the accompanying report and cost estimate by Pioneer Service and Engineering Company, Architect-Engineers for the project."Nuclear" components of the reactor are designed by Argonne National Laboratory as described in the present report.

Progress report of the Oak Ridge National Laboratory Biology Division providing updates on various projects, experiments, and other work. This report includes a summary of scholarly output from the division and departmental activities in cytology and genetics, mammalian genetics and development, microbial protection and recovery, mammalian recovery, pathology and physiology, general physiology, biochemistry, enzymology and photosynthesis, microbiology, plant biochemistry, and biophysics.

Memorandum presenting an investigation of the effect of Mach number variation from 1.8 to 7.4 on boundary-layer transition on a slender fin-stabilized ogive-cylinder body in free flight at a constant length Reynolds number of 13.8 million. Results showed that increasing Mach number had a very favorable effect of increasing the extent of the laminar boundary layer for a given surface roughness. Results regarding Mach number and surface roughness, effects of pressure rise, and long laminar runs are provided.

Memorandum presenting an investigation in the 9-inch supersonic tunnel to determine the effects of a sonic jet exhausting from a wing-mounted nacelle on the body drag of a body-wing-nacelle combination for various longitudinal, spanwise, and vertical nacelle locations and jet pressure ratios. The results indicated that the maximum variations in the total and fore drags of the body due to jet interference were about one-fourth of the basic body drag.

Report presenting an investigation made in the 4- by 4-foot supersonic pressure tunnel to determine the effects of body camber and body indentation on the longitudinal characteristics of a delta-wing-body combination at Mach number 1.61. Three bodies were tested with a 3-percent-thick 60 degree delta wing: a basic parabolic body, a body indented so as to have an improved wing-body area distribution at Mach number 1.8, and a body which was both indented and cambered. Results indicated that none of the changes had any appreciable effect at Mach number 1.61 on the minimum drag or maximum lift-drag ratios of the configurations tested.

Memorandum presenting the results of an experimental investigation to determine the pressure-distribution characteristics of a conically cambered wing with and without pylon-mounted engine nacelles for Mach numbers of 1.6 and 1.9. The pressure data obtained during this investigation indicate that the low-pressure region existing on the upper surface over the forward part of the wing was spread over a larger proportion of the local chord than would be the case for an uncambered wing.