The proposed Yankee Atomic Electric Company Reactor is a pressurized light water reactor plant designed to produce ultimate1y 492 Mw of heat and 134 Mw of net electrical generation at full power. The initial core to be operated in the reactor is designed to produce 392 Mw of heat at full power which provides approximately 110 Mw of net electrical generation. The reactor is fueled with slightly enriched uranium dioxide UO/sub 2/, in the form of pressed and sintered 0.3 in. diameter cylindrical compacts stacked in 0.336 in. OD full length stainless steel tubes in a core 7.5 ft. in height. The reactor is cooled and moderated by light water. The design is subject to change in detail before manufacture. Design characteristics and reactor safeguard considerations are described. (C.H.)

The difference in rates of reaction of isotopic molecules may be utilized to produce appreciable isotope enrichments. When a competitive irreversible isotopic reaction is carried out to a high extent of completion, the residual unconverted substrate becomes exponentlally enriched in the heavier isotope. In deuterium systems, a substantial function of the D inventory is retained in the enriched residual substrate, so that conversion of the depleted product is unnecessary. For isotopes of heavier elements such as C/sup 13/, N/ sup 15/, and O/sup 18/ the retention is low, so that product conversion and recycling is desirable unless the starting material is of negligible value. Experiments are described in which enrichments of C/sup 13/ have been obtained using the reaction rate principle in dehydration of formic acid and hydrolysis of urea. Procedures are given for the preparation of decimolar barium carbonate at the level of 1.6% C/sup 13/, and molar barium carbonate at the 1.4% level starting with commercial materials. (J.R.D.)

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A representative selection of stainless alloys was exposed in sulfur- bearing cracked-ammonia atmospheres containing 43 vol. % water vapor. Experimentally controlled variables have included temperatures ranging from 1200 to 1800 deg F and S levels ranging from zero to 350 grains per 100 ft/sup 3/ of cracked ammonia. It has been found that high S levels do not result in any significant change in the corrosion behavior of materials evaluated. Increasing the temperature resulted in some modifications or Moth physical properties and scaling resistance; however, these changes are a function of the temperature and not an effect of S. (auth)

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Report presenting a flight test of pentaborane fuel in an air-launched ramjet engine with a design free-stream Mach number of 1.8. The ramjet used in the investigation had a revised spray bar-flameholder configuration. Results regarding propulsive thrust and propulsive-thrust specific fuel consumption are provided.

Memorandum presenting an evaluation of the performance increase resulting from the addition of 20 percent fluorine to the oxygen-RP-1 propellant combination in a 5000-pound-thrust rocket engine at a chamber pressure of 650 pounds per square inch absolute. Runs were made with the engine water cooled and regeneratively cooled.

Memorandum presenting the results of an investigation directed at determining the effectiveness of various amounts and spanwise extents of conical camber on the aerodynamic characteristics of a wing-body-tail combination employing a triangular wing of aspect ratio 2.2. Five cambered wings were tested, all of which were designed for a Mach number of 1.0. Results regarding drag characteristics and lift and moment characteristics are provided.

Memorandum presenting an investigation at high subsonic speeds of a model of a twin-engine swept-wing fighter-type airplane. The model was tested with several different tail configurations and with several wing and engine inlet modifications. Results regarding pitching-moment characteristics, lift and drag characteristics, and lateral derivatives are provided.

Boundary-layer-transition and heat-transfer measurements were obtained from flight tests of blunt and sharp cones having apex angles of 50 deg. The test Mach number range was from 1.7 to 4.7, corresponding to free-stream Reynolds numbers, based on cone base diameter, of 18. 3 x 10(exp 6) and 32.1 x 10(exp 6), respectively. Transition on both models occurred at a local Reynolds number of 1 x 10(exp 6) to 2 X 10(exp 6) based on distance from the stagnation point. Transition Reynolds numbers based on momentum thickness were between 320 and 380 for the blunt cone. The model surface roughness was 25 rms microinches or greater. Turbulent heat transfer to the conical surface of the blunt cone at a Mach number of 4 was 30 percent less than that to the surface of the sharp cone. Available theories predicted heat-transfer coefficients reasonably well for the fully laminar or turbulent flow conditions.

Report issued by the Bureau of Mines over explorations to find prospective copper mines near Valdez, Alaska. The results of the explorations are presented. This report includes tables, maps, and illustrations.

Report issued by the Bureau of Mines on a table developed for determining metastable transitions. The table is presented. This report includes tables, and illustrations.

"Slender-body theory is used in conjunction with late theory to analyze the static aeroelastic-divergence behavior of low-aspect-ratio rectangular wings of constant thickness when chordwise deformations are considered. In the analysis, the spanwise variation of the deflection is restricted to a parabola but the chordwise variation is allowed complete freedom. Results show the variation of the divergence speed and mode shape with the aspect ratio" (p. 1).

Report presenting a method for calculating the expected number of maxima or minima of a random process with non-Gaussian frequency distribution from the statistical moments of the process and its first two derivatives. The effects of skewness and kurtosis can also be calculated provided the required moments are known.

From Summary: "Three-dimensional views are presented of the first three natural vibration mode shapes of ten cantilever-wing models. A table of normalized deflections at six spanwise and five chordwise stations is included for each mode. These mode shapes were measured by a rather unique experimental technique using grains of sand as accelerometers."

Report presenting a wind-tunnel investigation at low speed to determine the effects of fuselage nose length and a canopy on the static longitudinal and lateral stability characteristics of a complete model with a fuselage with square cross sections, a 45 degree sweptback wing, and a 45 degree sweptback horizontal tail.

A number of nozzles which use the mixing interference of adjacent jets for noise suppression were investigated. Reductions in sound power of nearly 70 percent (5 db) with thrust losses of 1 percent were achieved. A method of calculating the limiting frequency affected by this type of suppression nozzle, that is , multiple-slot nozzles, is presented. Data are shown which indicate that further large reductions in sound power are not likely with mixing-interference nozzles.

The effect of spanwise variations in gust intensity on the power spectrum directly due to atmospheric turbulence is calculated for several analytic approximations to the correlation function or power spectra of atmospheric turbulence, for several spanwise weighing functions (span loadings), and for various angles of sweepback.

Report presenting cross-grain specimens made of 7075-T6 aluminum-alloy extrusion were subjected to repeated axial loads until fatigue cracks of various lengths were formed. The specimens were subjected to static tests to determine the residual static strength.