From introduction: "This report covers the development of nondestructive techniques for measuring quantitatively: (1) thickness of electrodeposited-nickel diffusion barriers, and (2) thickness of aluminum cladding on flat-plate fuel elements."

Abstract: "A measurement was made of the dissociation of vibrationally-excited H2+ ions by photons having quantum energy in the vicinity of 4 e.v. The calculated cross section from theory is 3 x 10-(-18) cm-2. The experimental result is 10-(-17) cm-2; a factor of 10 uncertainty is present because the photon intensity was unknown by that factor."

"This investigation was conducted to study the practicability of employing heat as a means of preventing the formation of ice on airplane wings. The report relates essentially to technical problems regarding the extraction of heat from the exhaust gases and its proper distribution over the exposed surfaces. In this connection a separate study has been made to determine the variation of the coefficient of heat transmission along the chord of a Clark Y airfoil. Experiments on ice prevention both in the laboratory and in flight show conclusively that it is necessary to heat only the front portion of the wing surface to effect complete prevention" (p. 3).

Report presenting an investigation of the lateral stability and control effectiveness of a model of a fighter-type airplane model with a low-aspect-ratio and 3.4-percent-thick wing with negative dihedral at a range of Mach numbers, sideslip angles, and angles of attack. Results regarding the lateral characteristics at zero angle of attack, lifting conditions, and lateral and directional controls are provided.

Memorandum presenting an experimental investigation of the cooling characteristics of a small air-cooled turbine blade for use in a turboprop engine in a static cascade facility. Three test blades were studiued at three combustion-gas temperatures. Results regarding gas-flow conditions in cascade test section, correlation of temperature data, and application of correlated data to the typical engine are provided.

Report presenting an experimental investigation in a simulated afterburner test rig to determine the effects of some configuration variations on afterburner combustion performance. Results regarding the reduced-diameter flameholder, inclined radial-gutter flameholder, tapered-shell afterburner, and turbulence generators are provided.

Report presenting an investigation in the full-scale tunnel of the low-speed longitudinal characteristics of a 47.5 degree sweptback wing-fuselage combination with various extensible leading-edge-flap and plain trailing-edge-flap arrangements. Results regarding the basic longitudinal characteristics, extensible leading-edge flaps, plain trailing-edge flaps, and flap combinations are provided.

Report presenting results of a tank investigation of a 1/8-size powered dynamic model of the Grumman JRF-5 airplane fitted with tandem hydro-skis and auxiliary wing-tip skids suitable for operation on water, snow, and ice. Results regarding take-off and landing tests are provided.

In determining the experimental performance of an air-cooled turbine, the heat-transfer characteristics must be evaluated. The suggested formulas that are required to determine these characteristics are presented. The formulas have a form in which dependent parameters are expressed as unknown functions of independent parameters. Methods of experimenting to determine these functions are suggested. In some cases general heat-transfer discussions that lead to the suggested forms of the formulas are given.

This report presents the results of an investigation to ascertain the lift, drag, and pitching moment of a wing-body combination having a triangular wing of aspect ratio 2 with NACA 0003-63 thickness distribution in streamwise planes and twisted and cambered for a nearly elliptical span load distribution. Results are shown for Mach numbers from 0.60 to 0.90 and from 1.30 to 1.70 at Reynolds numbers of 3.0 million and 7.5 million.

Report presenting some highlights of recent experimental studies of flutter at high speeds. Flutter problems have become more varied with the advent of transonic flight and importance of aeroelasticity, and the flutter field has merged with other aspect of aeroelasticity such as divergence and buffeting. The two main subjects of flutter, classical flutter and stall flutter, are explored in these studies.

Paper presenting a preliminary account of some research conducted on the general problem of flow separation. The research is fundamental in nature, partly theoretical, and partly experimental. Measurements are made of subsonic and supersonic speeds for a variety of two dimensional model shapes involving separation.

From Introduction: "This report extends the short-bearing pressure-distribution function of Michell and Cardullo to give equations for the various bearing characteristics. This short-bearing approximation makes available formulas relating eccentricity ratio to applied load, attitude angle, angular position of peak film pressure to unit pressure on projected area."

Report presenting an investigation of three phases: an experimental investigation of a thin airfoil with blowing over a trailing-edge flap, a comparison of the results of the experimental investigation with the results of other similar investigations, and a theoretical study of the relationships among the air-flow and power parameters for the general blowing case. The investigation utilized a two-dimensional model of the NACA 0006 airfoil equipped with a nose flap and six alternate trailing-edge flaps.

This document describes a method in determining solid solubilities using strain-aging techniques, explaining a non-uniform yielding of the alloy in question.

The following report provides data taken of problematic situations that have led to accidental prompt-critical radiation bursts in critical assemblies laboratories, as well as a few risky instances. The purpose of this report is to prevent these mistakes from happening in the future.

During a compilation of ore reserves at Bull Canyon, it was apparent from the grade of submarginal mineralization that this material might be a low-grade reserve of importance. Mr. Lewis Hazen requested a memorandum of the results of the analysis; this memorandum is a response to that request.

A method is described for preparing plaster of Paris replicas of irradiated fuel slugs. An impression mold is made by pouring the plaster about a fuel slug held in a specially designed holder. The slug is removed from the holder and the impression mold issued to cast a replica, also made of plaster of Paris. The replicas, including one end only, are accurate reproduction of the original slug for surface features down to about one-half mil and for dimensions within one or two mills. Two dental impression plasters were found to give satisfactory results. With the limits mentioned, the process will serve the purpose of preserving models of radioactive specimens for use as "museum pieces." However, the procedures are very exacting in achieving such results.

Changes made in the Thorex process flowsheet were a decrease in the extraction column acidity to decrease thorium losses and the addition of a second thorium solvent-extraction cycle to provide the increased decontamination required when thorium irradiated to 2000-4000 g of U233 per ton is processed. Bonded slugs could not be dissolved by the Thorex flowsheet procedure. Various laboratory scale studies on feed preparation, first-cycle variables, and radiation damage to the solvent are reported.

From abstract: "The preparation of pure molybdenum(IV) bromide was accomplished conveniently by the reaction between molybdenum(III) bromide and liquid bromine at ca. 55°. Molybdenum(IV) bromide was found to be soluble in liquid bromine, and this property was utilized to separate and purify the molybdenum(IV) bromide. The solution of MoBr4 in bromine was a poor electrical conductor. No evidence was found for the formation of MoBr4 from MoBr3 and bromine vapor at 2-4 atm. and temperatures from 180 to 400°. However, MoBr4 was completely decomposed at 110-130°, in vacuo, with formation of MoBr3 and bromine."

From introduction: "The analysis of mixtures of fission products with a mass spectrograph offers certain advantages. A chemical separation of the fission products found in the solution at Hanford is not necessary with the mass spectrograph technique. A sample of the mixtures can be placed on the sample holder and then the sample holder is mounted in the mass spectrograph. This reduces the amount of handling of the active solutions to one relatively simple and short operation. The health hazards involved in the analysis can be further reduced by increasing the efficiency of the spectrograph as much as possible, thus making possible an analysis of a sample of lower total activity. The mass spectrograph described here is an attempt to realize the advantages pointed out above. Particular attention has been given to increasing the increasing the efficiency of the instrument."

Report containing experiments conducted at the Oak Ridge National Laboratory's Critical Experiments Facility. These experiments involved "determining the critical parameters of the assembly with varying amounts of neutron absorber in the D20 reflector, measuring the relative neutron flux distribution for various conditions of reflector poison and fissile solution concentration, determining the ratio of the absolute thermal-neutron flux in the center of the assembly to the power in the fissile solution , and determining the effect on reactivity of reducing the hydrogen density in the central region of the assembly" (p. 1).

Report presenting the longitudinal stability characteristics of a simple infrared homing missile determined in flight with a rocket-powered model. Static and dynamic longitudinal stability derivatives of the cruciform, interdigitated, canard-wing missile configuration were determined using the pulse-rocket technique for a range of Mach numbers.

Flight tests were conducted on a North American P-51D airplane to establish the maximum lift coefficient and the buffeting boundary line as a function of Mach number.