Report discussing the performance of a 20-inch-diameter ram-jet engine at Mach number 3.0 over a range of simulated altitudes from 60,500 to 66,500 feet. Information about the maximum combustor efficiency, range of exhaust-nozzle total pressures, lean blow-out, diffuser total-pressure recovery, and internal thrust coefficient is provided.

Memorandum presenting an experimental investigation of a two-dimensional, 6.6-percent-thick, 6-foot-chord airfoil section equipped with suction slots for laminar-boundary-layer control. The section was designed to have favorable pressure gradients between the suction slots. The laminar boundary layer on the airfoil had the same extreme sensitivity to minute details of the model surface condition as has been found in other investigations.

Report presents the correlation of extensive data obtained relating properties of wrought N-155 alloy under static, combined static and dynamic, and complete reversed dynamic stress conditions. Time period for fracture ranged from 50 to 500 hours at room temperature, 1,000 degrees, 1,200 degrees, and 1,500 degrees F.

"At subsonic speeds the pressure drag arising from the thickness of the body or wings is negligible so long as the shapes are sufficiently well streamlined to avoid flow separation. In that range there exists no possibility of either favorable or adverse interference on the pressure distributions themselves. If one body is so placed as to receive a drag from the pressure field of another then the second body is sure to receive a corresponding increment of thrust from the first" (p. 1).

Report presenting an investigation to study some factors affecting the drag of relatively large nonlifting bodies of revolution at transonic speeds in the 8-foot transonic tunnel. Drag and surface pressure measurements were made for two geometrically similar bodies of revolution of 8-inch and 4-inch maximum diameter at zero angle of attack through a range of Mach numbers.

Report presenting an experimental investigation to determine some of the characteristics of an inset tab as an aerodynamic balance in the Mach number range between 0.7 and 1.4 using a zero-lift rocket-propelled model in free flight. Results regarding the variation of the aileron floating angle, the wing-tip helix, the balancing effect, and the penalty occurred throughout the Mach number range are provided.

Report presenting an investigation of the performance of a 20-inch-diameter ram-jet engine at Mach number 3.0 in a free-jet facility over a range of simulated altitudes. Results regarding the diffuser characteristics, combustor performance, thrust output, and operational characteristics are provided.

Memorandum presenting an investigation of the stability and controllability in space of an arrangement comprising a man standing on a small platform which is rigidly connected to a jet nozzle with its thrust axis perpendicular to the platform and its thrust opposed to the pull of gravity. Results regarding the initial flights with the platform, flights with landing gear, flights with landing gear and inertia, flights with landing gear and gyroscope, flights with landing gear and control stick, flights with landing gear and seat, and discussion of the balancing process are provided.

Memorandum summarizing the lift and drag characteristics of a series of five low-aspect-ratio triangular-wing or modified triangular-wing airplane models. The series consists of three triangular wings of aspect ratios 2, 3, and 4 and two modified triangular wings of aspect ratio 2 with taper ratios of 0.20 and 0.33. The experimental lift and drag characteristics of the five models are compared with existing theory.

From Summary: "From a theory developed on a quasi-one-dimensional-flow basis, it was found that the stability of the ram jet is dependent upon the instantaneous values of mass flow and total pressure recovery of the supersonic diffuser and immediate neighboring subsonic diffuser. Conditions for stable and unstable flow were presented. The theory developed in the report was in agreement with the experimental data of the reports both of Sterbentz and Evvard and of Ferri and Nucci."

Report presenting an investigation in the transonic tunnel to determine the effects of varying Reynolds number on the pressure distribution on a transonic body of revolution at angles of attack through the transonic speed range. The effect of change in sting cone angle on the pressure distributions and a comparison of experimental incremental pressures with theory is also provided.

Report presenting an experimental investigation of a two-dimensional, 6.6-percent-thick, 6-foot-chord airfoil section equipped with suction slots for laminar-boundary-layer control. The airfoil section was designed to have favorable pressure gradients between the suction slots. Results indicated that the laminar boundary layer on the airfoil had the same extreme sensitivity to minute details of the surface condition as has been observed in other similar investigations.

"Experimental results are presented for transonic flow post cone-cylinder, axially symmetric bodies. The drag coefficient and surface Mach number are studied as the free-stream Mach number is varied and, wherever possible, the experimental results are compared with theoretical predictions. Interferometric results for several typical flow configurations are shown and an example of shock-free supersonic-to-subsonic compression is experimentally demonstrated" (p. 963).

From introduction: This report is a technical evaluation of four reactor power plant designs proposed by various AEC contractors.

Abstract: "Dissolution of carnotite in several readily liquefiable gases, including ammonia, sulfur dioxide, chlorine, and nitrogen dioxide, was found to be negligible, even in the presence of uranium complexing agents. No low-boiling liquids have been found which will dissolve carnotite directly. Treatment with various sulfur chloride will convert carnotite to a form soluble in water or in certain organic solvents. Also, carnotite can be readily dissolved in HCl-acidified ethanol, methanol, or acetone. Amenability tests on nine western ores with HCl-methanol solvent indicated that uranium extractions greater than 90 per cent could be obtained if sufficient acid was used to insure some free acidity in the pregnant liquor. Temple Mountain and Sinbad-Muddy River ores were exceptions to this, uranium extractions being only about 50-60 per cent. Vanadium extractions were invariably lower than uranium extractions. Chemical analyses are presented for nine western ores."

Abstract: "This report describes the results of X-ray diffraction examination of reaction products from a series of experiments performed by Mallinckrodt Chemical Works as an acid in understanding the process of bomb reduction of UF4. UF4 is initially reduced to UF3 by magnesium at 560 C., and subsequently to metal at 600 C. MgF2 from the initial reaction forms a coating on the magnesium which retards the final spontaneous reaction."

Introduction: Among the many corrosion problems encountered in the production of uranium tetrafluoride and uranium metal from ores and concentrates, some of the most serious occur where hydrofluoric acid must be handled.

This report describes progress in testing non-aqueous extraction methods for leaching Western ores of uranium and vanadium.

The following progress report is part of a series of reports on the study of nonaqueous extractive methods for western uranium ores. This report continues studies on HCl-methanol leaching of Western ores, primarily on Temple Mountain ores.

From introduction: "This report presents the results of an experimental program to evaluate engineering problems which might be encountered when circulating NaOH-UO3 slurry through a thermal cycle."

From abstract: "The circumstances are described pertaining to an explosion in a TNX evaporator during the concentration of a uranyl nitrate-nitric acid solution. TBP and Amsco diluent were probably present in the evaporator charge. A laboratory program involving small-scale atmospheric and closed-vessel distillations of various mixtures of UNH, HNO3, Amsco, TBP, and water indicate that an exothermic reaction between TBP and UNH, or between TBP and HNO3, or both, was responsible for the explosion. The danger areas of temperature, TBP concentration, pressure, and heating rate are defined and recommendations are made for safe evaporator operation.

The spontaneous fission rate of plutonium-240 has been redetermined and found to be 1.51 X 106 events/g/hr.

Hanford uranium contains minute angular inclusions which affect the microstructure, reactivity, and other important factors controlling the serviceability of the metal. Small quantities of the inclusions have been isolated by chemical means, and the x-ray diffraction patterns and chemical analyses of the isolated materials have been determined. As a first step in the identification of the inclusions present in rolled uranium, a search was made for a chemical method of separating the inclusions from the matrix metal.

About twenty-five to thirty per cent of the uranium slugs canned in the Metal Preparation Section do not meet specifications and are rejected. These rejected slugs are recovered by a chemical process and prepared for re-canning. The current recovery process consists essentially of a sodium hydroxide-sodium nitrate bath for chemically removing the aluminum can and the bonding medium, followed by hydrofluoric acid and nitric acid baths to remove the remaining compound layer and to pickle the slugs before they are returned to the process canning line. Recent studies have indicated the possibility of using a more economical means of recovery. this includes the mechanical removal of the aluminum can and most of the bonding medium, followed by a chemical removal of the residual compound layer by a solution of sodium hydroxide.