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Samples of PuO/sub 2/ were examined by x-ray diffraction for crystallite size and perfection. The PuO/sub 2/ was formed by thermal decomposition of the oxalate. Measurement of the integral widths of diffraction lines gave values of broadening which were used to calculate the effective crystallite thickness. (J.R.D.)

Description of Invention: Chloride-induced corrosion is a serious problem in the Purex acid recovery operation and in the evaporative concentration of process streams and waste solutions. In the case of Purex acid recovery, it has been shown that trace chloride will volatilize with the nitric acid and reflux in the acid fractionator, thus causing especially severe corrosion at that point. These traces of chloride may enter the process form several sources, i.e., as an impurity in the technical grade chemicals used in making up the various aqueous process streams, by hydrolysis or radiation decomposition of carbon tetrachloride (a promising diluent for tributyl phosphate), or by incomplete removal of the hydrochloric acid employed in some flowsheets for effecting the dissolution of certain difficulty soluble nuclear reactor fuel elements.

In connection with studies of the chemical reactivity of PuO_2 to hydrofluorination, samples were examined by X-ray diffraction for crystallite size and perfection. The PuO_2 was formed by thermal decomposition of the oralate. The reactivity of this oxide, as well as that of other solid oxides is affected by the conditions of preparation. Besides the obvious influence of surface, including lattice strain and other structural irregularities in the particles. Each particle is composed of a number of crystallites. The extent of crystallites size and perfection will be indicated by the width of a diffracted X-ray beam. Since separation of these two caus4es would require a detailed analysis, the observed broadening was interpreted on the assumption of crystallite size effects alone. However, the variable factor in preparation method was temperature, and it is to be expected that crystallite growth with annealing will occur in part at the expense of energy stored in nonequilibrium states of the crystal, i.e., imperfections. The objectives of this study were to establish a convenient method for determination of PuO_2 crystallite size and to obtain estimates of the crystallite sizes of seven given samples.

Coatings examined were selected industrial finishes reported to have good resistance to corrosion and included epoxy resins reinforced with fiberglass. For screening purposes,this preliminary work was done on commercial sheet Mg to which had been applied a dichromate finish. The coatings were tested for impact resistance, corrosion resistance, abrasion resistance, and thermal shock resistance. Conclusions for further work are outlined.

"Approximately 2,000 flights of rocket-propelled models have been made in which model configuration, model size, type and number of booster rockets, number of booster stages, and booster arrangements varied. A brief summary of the results obtained with some of the more unusual arrangements, descriptions of boosting hardware and techniques, and discussions of some factors responsible for the choice of these configurations are presented in this paper. The results show that unconventional boosting techniques may be used successfully when conventional tandem arrangements are unsuitable or unwieldy" (p. 1).

Report presenting an investigation at Mach number 5.20 to determine the longitudinal aerodynamic characteristics of a number of flat-bottom bodies which were investigated for possible hypersonic applications. The bodies were tested at positive and negative angles of attack to simulate flat-bottom and flat-top arrangements.

Report presenting a wind-tunnel investigation at low speeds of a thin aspect-ratio-1.85 pointed-wing-fuselage model with double slotted flaps, including the effects of a straight and delta horizontal tail on the static longitudinal stability and the effect of a delta vertical tail on the static lateral stability. Results regarding the longitudinal aerodynamic characteristics and lateral stability characteristics are provided.

Report presenting an investigation of a helicopter pressure-jet system. The effects of tip speed, fuel-air ratio, and pressure ratio on the propulsive characteristics of the pressure-jet system have been determined for a range of tip seeds, blade-root stagnation-pressure ratios, and fuel-air ratios. Results regarding tip-burner specific propulsive horsepower, propulsive horsepower per unit mean duct area, tip-burner specific fuel consumption, ratio of propulsive horsepower to equivalent air horsepower, effect of whirling on tip-unit thrust, effect of whirling on the tip-burner inlet pressure, effect of auxiliary fuel flow, power-off drag of tip units, and overall specific fuel consumption of pressure-jet system are provided.