This report discusses mechanical properties and heat treatment of some uranium-titanium alloys. These alloys were tested for use as fuel-element material.

This report discusses a meeting held on November 8, 1956 at BMI, Columbus, Ohio, for the following purposes: To determine the best method of electroplating uranium cores for extrusion cladding; to determine if there were any shortcomings in the SRL method of plating which could be the cause of the poor bonding experienced with internally extrusion-clad tubes; and to make what corrections and revisions were necessary in SRL plating procedure to assure the optimum quality of nickel electroplate on the basis of present information.

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Attempts were made to prepare a diphenoquinone having substituents in 2,2'-positions in order to prevent the planarity of the molecule and get a diradical of oxygen. The 2,2'-dimethyl-5,5'-di-t-butyldiphenoquinone was prepared and was shown to be in equilibrium with a small amount of diradical. This compound slowly polymerizes.

Report discussing floods and sediments near Corpus Christi Bay, Texas, based on data gathered between 1927 and summer 1956. It includes specific measurements and analyses, broken into sections under three phase headings: (1) Floods of North Beach: Record, Causes, Types and Probability, (2) Sedimentation and Maintenance, and (3) Area Flood Protection by Strengthening Barrier Islands.

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Heat transfer and isothermal friction characteristics of the experimental ART fuel-to-NaK heat exchanger have been determined for three degrees of spacer density. The data appear to indicate that for a given heat exchanger pressure drop, the heat transfer cocfficient is almost independent of the spacer density; as the spacer density is decreased, the Reynolds modulus increases to such an extent that the Nusselt modulus does not change significantly. For a given available pressure drop, with decreased spacer density, a larger flow rate exists allowing the same heat removal rate with a lower axial temperature change or a greater heat removal rate with the same axial temperature change. (auth)

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From Introduction: "The purpose of the flight investigation described herein was as a "proof" check of the system and to determine what effect several variables which could not be practicably simulated would have on the operation."

Report presenting the experimental values of damping in roll of the Bell X-1A airplane and its components at 5 Mach numbers at zero angle of attack. The wing was found to be the predominant contributor to the damping in roll throughout the range of Mach numbers, but the contributions of other airplane components were significant in the range of 2.22 to 2.41.

Memorandum presenting an analysis comparing engine performance determined by use of a method involving adjustment of engine cycle calculations using JP-4 fuel with performance obtained using hydrogen as a fuel.

Force and pressure distribution studies to high angles of attack on all-movable triangular and rectangular wings in combination with body at supersonic speeds. The ranges of aspect ratios were, for the triangular wings, 3/8 to 4, and for the rectangular wings, 1 to 3.

Memorandum presenting an experimental investigation conducted at Mach numbers 1.5, 1.8, and 2.0 to determine the effects of several throat boundary-layer bleed configurations on the performance of a 25 degree half-conical side-inlet system. The effects of several flush-slot configurations and a porous-surface bleed were determined over ranges of angle of attack and bleed-duct and main-duct mass flow.

Memorandum presenting an investigation conducted on the size and density of the boric oxide exhaust cloud from a J47-25 turbojet engine operating on trimethyl-borate fuel at sea-level static conditions. Movies and still photographs were taken from the ground and from a helicopter. Results regarding the visual observation and oxide fallout and concentration are provided.

Report presenting an investigation of the effects of changing indentation design Mach number on the aerodynamic characteristics of a 45 degree sweptback-wing-body combination designed for high performance at a range of Mach numbers. Theoretical results of zero-lift wave drag for the wing-body combination agreed well with the experimental data. Results regarding the bodies, systematic series of wing-body combinations, -2 degree angle of incidence, M = 1.4 revised body, and transition are presented.

Report presenting flight testing over a range of Mach numbers to determine the rolling behavior of a swept-wing airplane with lateral-longitudinal coupling. Results regarding the size of the tail area, speed effects, engine gyroscopic effects, and wing-tip extensions are provided.

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