This report has two parts to it discussing mineralogical examination of pitchblende concentrates and nitric acid digest residues. Part I gives the results of a cursory examination with the petrographic microscope of samples of pitchblende concentrates and residues to see if there is a relationship between the mineral composition of the samples and the filterability of the residue. Part II gives a revaluation of the data in Report BMI-241 on the mineral composition of two residues from the nitric acid digestion of pitchblende concentrates at the Rallinckrodt Chemical Works.

From abstract: "The composition of vapors from aqueous nitric acid solutions boiling at 200 mm mercury total pressure is established for solutions containing between - and 67.5 w/o nitric acid. The volatility characteristics of low concentrations of chloride in the same concentration range of nitric acid have been measured in solutions boiling at 200 mm mercury. The effects of chloride concentration and pressure of boiling are evaluated. A spectrophotometric method of the determination of chloride in nitric acid solutions is described."

Introduction: The U.S. Geological Survey is appraising the possibility, however slight, that the ground water beneath the Nevada Test Site, possibly contaminated by nuclear detonations, may carry radioactive fission products to places where they may constitute a public hazard.

Technical report describing a gasometrical method for the determination of H2 in extruded U rods.

Memorandum presenting an investigation of the effect of various metallic additives on the molten sodium hydroxide - nickel system. The hydrogen evolved from such systems was measured and the evolution was correlated with the effect of the metal on mass transfer. Results regarding a check with standard tests, purging, presence of two valences for chromium, reaction time of the additive, and pressure within nickel crucibles are provided.

Memorandum presenting static crucible tests with additions of the reducing agents sodium chromite Na(sub 3)CrO(sub 4) and manganese dioxide MnO(sub 2) indicate that salts soluble in sodium hydroxide may be added to inhibit mass transfer in nickel. The metals manganese, vanadium, and molybdenum were also investigated in static crucibles and found to be ineffective.

Report presenting outdoor static testing made on two high-solidity propellers of different design, one shrouded and the other unshrouded. Three shrouds were tested to determine the effects of shroud length and exit area. Results regarding the action of shroud, results and comparison of propellers, and comparison with theory are provided.

Report discussing flight tests of airplane-like models to determine the effect of airfoil section profile and thickness ratio on the zero-lift drag of low-aspect-ratio wings at supersonic speeds. Five rectangular wings with the same aspect ratio and a variety of airfoil thicknesses were tested to determine the effect of thickness ratio.

Report presenting a wind-tunnel investigation to determine the effects of a section modification on the aerodynamic characteristics of a wing with 35 degrees of sweepback. The wing was modified by increasing the leading-edge radius of the NACA 64A010 section and adding a small amount of camber to the forward portion of the chord. Lift, drag, pitching-moment, and trailing-edge-flap hinge-moment characteristics of the modified wing are compared with results from the original wing.

Memorandum presenting a comparison of the aerodynamic characteristics and flow phenomena at transonic speeds for a 45 degree sweptback wing mounted alternatively on a cylindrical body and an indented body. Indentation eliminated the zero-lift drag rise associated with the wing at a Mach number of 1. Results regarding the lift, drag, and pitching moment, flow surveys, level-flight characteristics, and flow phenomena are provided.

Report presenting spanwise lift distributions, lift coefficients, spanwise centers of pressure, shifts in aerodynamic center, coefficients of damping in roll, aileron rolling-moment coefficients, and rates of steady roll per unit aileron deflection have been calculated for nine M-, W-, and delta wings, as well as for comparable ordinary sweptforward, unswpet, and sweptback wings. Certain qualitative conclusions are drawn concerning the plan forms most suitable from the aeroelastic point of view. M and W plan forms exist which are superior aeroelastically and structurally to ordinary swept wings.

Report presenting an investigation in a duct system with fully developed pipe flow to determine the effects of vortex generators on the performance of a diffuser with whirling inlet flow. Testing was made with three different inlet whirl angles and rectangular, noncambered airfoils that varied in chord, span, angle setting, number, and location. Results for the 20.6 degree inlet whirl angle, 15.2 degree inlet whirl angle, 0 degree inlet whirl angle, and effect of inlet whirl angle on diffuser performance are provided.

From Summary: "A method is given for determining the horizontal tail loads in maneuvering flight. The method is based upon the assignment of a load-factor variation with time and the determination of a minimum time to reach peak load factor. The tail load is separated into various components. Examination of these components indicated that one of the components was so small that it could be neglected for most conventional airplanes; therefore, the number of aerodynamic parameters needed in this computation of tail loads was reduced to a minimum. In order to illustrate the method, as well as to show the effect of the main variables, a number of examples are given. Some discussion is given regarding the determination of maximum tail loads, maximum pitching accelerations, and maximum pitching velocities obtainable."

Report presenting an investigation of the Reynolds number for transition on the outside of a hollow cylinder with heat transfer from the boundary layer to the wall at Mach number 6.9. At a given Mach number, it appears that the Reynolds number based on leading-edge thickness is an important parameter in comparisons of flat-plate transition data from various installations.

This report describes the preparation and testing of corrosion on brazed, vacuum-tight aluminum joints for finned aluminum tubing to contain uranium slugs.

An investigation of corrosion in the 327 Building's water storage basin was made to determine whether the static storage of aluminum jacketed fuel elements could cause corrosion effects that would interfere with studies of in-pile corrosion.

"An investigation has been made in the Langley 8-foot transonic tunnels on the aerodynamic characteristics of a 0.15-scale model of the North American Aviation 255-inch fin-stabilized external store over a maximum Mach number range of 0.60 to 1.2 and on the effects of mounting lugs, of fin orientation, of fin aspect ratio, and of fixed-transition. The Reynolds number (based on a body length of 37.50 inches) varied from 9.8 x 10(exp 6) to 13.1 x 10(exp 6). The results indicate that the static margin of the finned store at low lift coefficients was only 9 percent of body length at subsonic Mach numbers and was reduced to zero at a Mach number of 1.0" (p. 1).

This report presents the results of tests made in the 7-by 10-foot wind tunnel and in the 20-foot tunnel of the National Advisory Committee for Aeronautics to determine the drag of a number of airplane wheels, wheel fairings, and landing gears designed or selected for an airplane of 3,000 pounds gross weight. All tests were made on full-size models; those in the 7-by 10-foot tunnel were made at air speeds up to 80 miles per hour and those in the 20-foot tunnel were made at air speeds up to 100 miles per hour. Although most of the landing-gear tests were made in conjunction with a fuselage and at 0 degree pitch angle, some of the tests were made in conjunction with fuselage plus wings and a radial air-cooled engine and at pitch angles from -5 degrees to 6 degrees to obtain an indication of the general effect of these various items on landing-gear drag.

"An investigation of the endurance characteristics, at high Mach number, of the J65-W-7 engine was made in an altitude chamber at the Lewis laboratory. The investigation was made to determine whether this engine can be operated at flight conditions of Mach 2 at 35,000-feet altitude (inlet temperature, 250 F) as a limited-service-life engine. Failure of the seventh-stage aluminum compressor blades occurred in both engines tested and was attributed to insufficient strength of the blade fastenings at the elevated temperatures" (p. 1).

"The vertical open-throat wind tunnel of the National Advisory Committee for Aeronautics is described in this report. The tunnel was built mainly for studying the spinning characteristics of airplane models, but may be used as well for the usual types of wind-tunnel tests. A special spinning balance is being developed to measure the desired forces and moments with the model simulating the spin of an airplane. Satisfactory air flow has been attained with a velocity that is uniform over the jet to within plus or minus 0.5 per cent" (p. 499).

A 0.1-size powered dynamic model of a large, high-speed flying boat was landed in Langley tank no. 1 into oncoming waves 4 feet high (full size). The model was tested with two afterbodies of differing lengths (4.12 and 6.63 beams). The short afterbody had a constant angle of dead rise of 22.5deg and a keel angle of 6.5deg. The long afterbody had warped dead rise and a keel angle of 8.5deg. The vertical accelerations were slightly greater and the maximum angular accelerations and maxim= trims were slightly less for the model with the long afterbody than for the model with -the short afterbody. A wave length of 210 feet (full size) imposed the highest accelerations on the model with either the long or the short afterbody.

Discusses distribution,sexual and age differences, specimens, and classification of North American grizzly and big brown bears. Describes and lists locations of species and subspecies. Mentions Vetularctos, a new genus related to Ursus.

A program translates an algebraic language like Algol into the machine language of an electronic computer must perform the following functions.

The IBM-70% code GHT has been programmed for the 7090computer, to be run under control of the IBM-7090 FORTAN Monitor System. By eliminating the use of tapes for intermediate number storage, it has been possible to reduce computing time by a factor of 26 over the 704. A minimum of three tapes are required; one for input, one for output, and the System tape. One scratch tape is required for transient problems, and one punch tape is required if the steady-state temperature distribution is to be punched on cards.