Report issued by the APDA over simulator studies conducted on their Developmental Fast Breeder Reactor. The simulator studies were "designed to predict both the normal and abnormal operating characteristics of the APDA Developmental Fast Breeder Reactor" (p. 1). This report includes tables, and illustrations.

Report issued by the Bureau of Mines over metallurgical studies of the Quien Sabe antimony mine. History, geology, and physical features of the mine are presented. This report includes tables, maps, and illustrations.

Report presenting a study that evaluates various types of refractories for use in a refractory-lined vessel that would be used for continuous reduction of uranium tetrafluoride to uranium metal.

Abstract: "A method for determination of dibutyl phosphate in solvent streams containing tributyl phosphate is outlined. The method is based on analysis for total uranium of total phosphate after removal of uranium and phosphate in excess of that present as uranyl dibutyl phosphate. Results on plant solvent samples are presented. Difficulties with precipitation of [...] dibutyl phosphate, when fresh solvents were employed, are discussed. Small amounts of nonphosphate uranium-complexing agents were found in plant solvents. Diluent degradation is postulated as the source of these components. Emulsion-formation tendencies appeared to correlate better with concentrations of these contaminants than with dibutyl phosphate content."

From abstract: "The purpose of this note is to consider the feasibility of conducting kiloton-weapons tests in underground holes sufficiently deep so that the explosion will be effectively contained. Such a shot would have the advantage that it could be detonated independently of weather conditions, and thus would allow greater freedom in the test program."

Summary: The design of many contemporary aircraft, layout of base facilities, and operational characteristics of planes necessitate movements of these aircraft along prescribed paths. Undesirable effects on pavements have been observed at a number of places under this type of traffic from B-47 planes.

Report presenting a continuous sampling-probe technique used to determine the percentage of JP-5 fuel spray evaporated under conditions common in ramjet engines. Fuel was injected contraststream from a multiple-orifice injector and sampling data were obtained at several distances downstream of the injector. An expression is generated for a description of this phenomenon.

Report presenting three types of aerodynamic interference originating from forward components of airplanes, which are shown to contribute to decreased vertical-tail effectiveness.

From Introduction: "It is the purpose of this report to assemble principles of induction-system design for flight to a Mach number of 2 and to use existing data to show the consequences of compromising them."

Memorandum presenting an investigation of three models of a delta-wing airplane designed for a long-range subsonic cruise and a supersonic dash. Results regarding the aerodynamic characteristics of the models and effect of elevon deflection on aerodynamic characteristics of the four-engine model are provided.

Memorandum presenting three types of aerodynamic interference originating from forward components of airplanes, which are shown to contribute to decreased vertical-tail effectiveness. The vorticity originating from a slender fuselage ahead of the wing resulted in a marked reduction in vertical-tail effectiveness with angle of attack for one model.

Memorandum presenting a correlation of analyses of the effect of distributed surface injection on the heat transfer and skin friction associated with the turbulent boundary layer at high speeds to eliminate the effects of Mach and Reynolds number. Data for heat transfer and skin friction at three Mach numbers are compared with the analyses and the agreement is good.

Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of various vertical locations of the wing and horizontal tail on the aerodynamic characteristics in pitch and of a supersonic airplane configuration at Mach number 2.01. The model was equipped with a wing and horizontal tail, each having a 45 degree sweep and an aspect ratio of 4. The configurations investigated included a high-wing, a mid-wing, and a low-wing arrangement, each with four different horizontal tail locations varying from a position 0.208 semispan below to 0.556 semispan above the body center line.

Report presenting a preliminary study to determine the possibility of utilizing a wingless configuration as a guided missile. The results indicated that the maximum trimmed lift coefficient developed by the wingless missile was somewhat smaller than that of the winged missile at a Mach number of 2.4.

Report presenting an experimental investigation in the transonic blowdown tunnel to determine effects of center-of-gravity location on the transonic flutter characteristics of a 45 degree sweptback-wing plan form of aspect ratio 4.0 and taper ratio 0.6. Solid-construction models with streamwise NACA 65A004 airfoil sections and center-of-gravity locations at three different chords were fluttered at a range of Mach numbers.

Report presenting the effects of a straightening operation on the life of Inconel 500 buckets in a J33-9 engine. Results regarding engine performance and bucket-failure mechanism are provided.

Report presenting an investigation of an airplane configuration model with a 45 degree swept wing of aspect ratio 4.0 and a taper ratio 0.3 with a low swept horizontal tail to determine its longitudinal stability. Longitudinal aerodynamic coefficients and stability derivatives are presented as functions of Mach number over the test range. The results are compared to wind tunnel and rocket model data and generally show good agreement.

Report presenting an investigation at two Mach numbers for a range of Reynolds numbers to determine the pressure distributions at several spanwise stations for a series of 25.4-percent-chord trailing-edge controls on a trapezoidal wing with a 23 degree sweptback leading edge, aspect ratio of 3.1, and taper ratio of 0.4. The report contains the tabulated pressure data for the complete range of test variables.

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.

Report presenting an experimental investigation to determine the effect of boundary-layer control and inlet lip shape on the performance of a side-inlet air-induction system for a fighter-type airplane. Two methods of boundary layer control and three inlet lip shapes were investigated at a range of Mach numbers and mass-flow ratios. Results regarding net propulsive thrust are also 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 an investigation to determine the aerodynamic characteristics of a sting-mounted Douglas Aircraft Company store in the presence of an unswept semispan cantilevered wing of aspect ratio 4.0. Results regarding wing loads and store loads are provided.

Report presenting tests to determine the flight characteristics of an F-86A airplane equipped with an area-suction boundary-layer-control system on the flaps and to investigate the possible operational problems which may arise on a flight installation of boundary-layer control. Results regarding the airplane with slatted leading edge, suction requirements, airplane with suction flap and various leading-edge configurations, factors affecting flap lift increment, and operational characteristics of boundary-layer control are provided.

Memorandum presenting a preliminary free-flight study of the drag and stability of a series of short-span missile configurations with 80, 85, and 90 degrees of fin leading-edge sweep. Increasing the fin sweep decreased the drag markedly.