Report presenting an investigation to determine the effect of systematic variations in inlet-air and fuel parameters on the smoking characteristics of a single tubular turbojet-engine combustor. The most pronounced effect on smoke was observed with increase in inlet-air pressure which produced large increases in smoke concentration. Results regarding the reproducibility of smoke measurements, effect of fuel-air ratio and inlet-air parameters on smoke density, effect of fuel parameters on smoke density, full-scale engine tests, and combustion efficiency are provided.

This report describes the manufacture of 25 Aluminum clad, 10 w/o plutonium-aluminum alloy and 5 w/o plutonium-aluminum alloy cored specimens for Argonne National Laboratory-University of California irradiation tests in the Materials Testing Reactor. The manufacturing method: preparation of cores and cladding material, assembly and welding of compacts, outgassing, roll bonding, shearing, identification marking and final fabrication into napkin "rings" is described in detail. Of ninety-six specimens fabricated, ninety-one were completed as finished specimens. Forty-four of these contained 5 w/o plutonium alloy cores and forty-seven contained 10 w/o plutonium alloy cores. Five specimens ere rejected for bond blistering.

Report presenting an investigation into the effects of interference at supersonic speeds on the aerodynamic properties of wing-body combinations to determine the pitching moments. The correlation points of various wing-body shapes are provided and suggestions for modifications are made.

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Report presenting an investigation of the properties of molybdenum disilicide in which a fine-grain material and a large-grain material were produced using different methods. Results regarding the fine-particle sintered material, coarse-grain, hot-pressed material, a comparison of the two materials, and the effect of oxygen on sintering and mechanical properties are provided.

Report presenting a free-flight investigation of drag on four full-scale models of 16-inch-diameter ramjet engines over a Mach number range of 0.6 to 1.43. Data was obtained at different internal airflow rates by inserting annular restrictors in the outlet of the models. Results regarding the variation of the total-drag coefficient, effect of Mach number on drag coefficients, and magnitude of drag coefficients are provided.

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The purpose of this work was (1) to investigate the possibility of producing zirconium-clad zirconium-uranium alloy objects by casting the core alloy directly into zirconium and zirconium-3 w/o tin jackets, producing a diffusion bond at the jacket-core interfaces, and (2) to produce small scale heat thru-put test specimens by this method.