Abstract: "Approximate melting points have been determined for five samples of uranium tetrafluoride representing incompletely converted uranium dioxide and covering the range from about 2 to 20 w/o UO2, using the method of differential thermal analysis. The results indicate the melting temperatures are in the range of 920 to 980 C. No significant correlation between melting point and UO2 content was observed, possibly because of calcite formation. Similar results were obtained on synthetic mistakes of UF4 containing from 10 to 40 w/o UO2."

The following document describes the usage and results of sending pulsed beams of electrically charged particles with electrically wide range of pulse lengths and pulse repetition rates.

Abstract: This report presents the results of plant optimization studies and cost estimates of the reference design for a natural uranium, graphite moderated, gas-cooled reactor and power plant which was described in NAA-SR-1833.

Memorandum presenting an annotated bibliography of NACA reports containing information of interest to designers and manufacturers of controls for turbojet engines. The eleven major topics include starting, acceleration, flame-out, temperature control, stability and dynamics of small disturbances, combustion dynamics, engine inlet diffuser control, steady-state engine performance, fuel systems, sensors, and general control system theory.

"An exploratory investigation at Mach number 2.72 has been made to show the decrease in the drag of a round-nose model achieved by mounting a small cone on a rod ahead of the nose. The geometric parameters which were varied were the cone-base diameter, cone angle, and rod length. All models showed large decreases in drag compared to that of the round nose alone" (p. 1).

Memorandum presenting an investigation of a full-scale afterburner with high burner-inlet velocity conducted to determine burner performance with several variations in burner design. Variables receiving particular attention were flameholder design and burner length. Results regarding diffuser performance, performance of the reference two-V-gutter flameholder, designs to improve combustion for high-velocity conditions, and operational characteristics are provided.

"The steady pressure loads as well as the temperature change on adjacent surfaces due to the presence of a propulsive jet at subsonic speeds is shown to be insignificant. Whereas at supersonic speeds the temperature effect might be expected to remain insignificant, the steady pressure loads were shown to increase greatly on surfaces downstream of the propulsive jet exit" (p. 1).

Attenuation of tangent-pressure oscillation in liquid-oxygen-heptane rocket engine combustion chamber using longitudinal fin. Results regarding the engine performance with injector A, effect of fins with injector A, and destructiveness of screaming are provided.

Measured values of lift, drag, and pitching moment at M(sub o) = 1.53 are presented for seven wings varying in sweep angle from 60 degrees sweepforward to 60 degrees sweepback. All wings had a cambered, double-wedge section 5-percent thick and a common taper ratio of 0.5. The experimental results are compared with the predictions of the linear theory.

Performance of four 16-inch-diameter ram-jet units was determined at free-stream Mach numbers of 0.49 to 1.78 over range of gas total-temperature ratios of 1.0 to 6.1. Time histories of each flight and data on thrust, drag, diffuser efficiency, and combustion are presented. A maximum thrust coefficient of 0.88 and a maximum net acceleration of 5.13 g's were observed for the four units.

From Summary: "An analysis was made to determine the proportions of fins made of aluminum, copper, magnesium, and steel necessary to dissipate maximum quantities of heat for different fin widths, fin weights, and air-flow conditions. The analysis also concerns the determination of the optimum fin proportions when specified limits are placed on the fin dimensions. The calculation of the heat flow in the fins is based on experimentally verified, theoretical equations. The surface heat-transfer coefficients used with this equation were taken from previously reported experiments. In addition to the presentation of fin-design information, this investigation shows that optimum fin dimensions are inappreciably affected by the differences in air flow that are obtained with different air-flow arrangements or by small changes in the length of the air-flow path."

Memorandum presenting two-spool matching procedures which may be employed to analyze turbojet, turboprop, and stationary power plants. The procedures were applied to obtain the sea-level static equilibrium performance of a simple two-spool turbojet engine in which the compressor and turbine performances were based on experimental results. Results regarding engine performance at sea-level static conditions, component performance, and effect of compressor-discharge bleed are provided.

Report presenting an investigation to determine the performance characteristics of a transonic stage designed to produce transonic inlet Mach numbers relative to a succeeding stage. Results regarding rotor performance, stator performance, and stage performance are provided.

"The steady pressure loads as well as the temperature change on adjacent surfaces due to the presence of a propulsive jet at subsonic speeds is shown to be insignificant. Whereas at supersonic speeds the temperature effect might be expected to remain insignificant, the steady pressure loads were shown to increase greatly on surfaces downstream of the propulsive jet exit" (p. 1).

Report presenting an investigation in the high-speed tunnel of the effects at high subsonic speeds of horizontal-tail height on the aerodynamic and loading characteristics in sideslip of a 45 degree sweptback, untapered tail assembly. Configurations investigated include the fuselage alone, the fuselage plus vertical tail, and with a horizontal tail mounted at 0, 50, and 100 percent vertical-tail span. Results regarding the lateral force coefficient, rolling-moment coefficient, and a comparison of experimental and theoretical results are provided.

Memorandum presenting a wind tunnel investigation to determine the effects of an airfoil section modification consisting of a greatly increased leading-edge radius and slight forward camber on the aerodynamic characteristics of a thin swept-wing-body combination at Mach numbers from 0.06 to 1.9. The tests showed that full-span modification of the wing resulted in very marked improvement in stability, drag, and high-lift characteristics for the configuration at low speeds due to the maintenance of attached flow over the wing to high lift coefficients.

Report presenting an acceleration control that operates on fuel flow and uses directly measured acceleration as the control signal as applied to an axial-flow turbojet engine. A study to determine the feasibility and dynamic characteristics of the control was undertaken. Results regarding the open-loop characteristics and closed-loop characteristics are provided.

Final report documenting a high-sensitivity airborne gamma radiation and magnetic field survey of the Houston National Topographic Map segment (NH 15-7 quadrangle) including a description of the program and results.

Report discussing a study regarding the identification and property analysis of plutonium (IV) monobutyl phosphate, which formed as a white precipitate in another study of the effects of monobutyl phosphate on plutonium(IV) in tributyl phosphate extractions.

Introduction: "Evidence of masonite deterioration in test hole plugs was interpreted to mean that a previous estimate of the minimum lifetime of the masonite in a Hanford biological shield might be somewhat optimistic. The importance of understanding the effects of radiations on masonite for both present and future pile shields dictated that masonite be sampled from an operating pile shield and studied. The results and techniques are discussed in the following sections of this report."

The following document describes the process of rare beryllium extrusion using graphite introductory cones with the purpose of finding a lubricant which would decrease excessive friction between the billet and prose parts.

The most important component required for the Astron experimental facility is a high energy, high current, pulsed electron accelerator. A thin cylindrical layer of high energy electrons trapped within an axially symmetric magnetic field is the key feature of the Astron thermonuclear device. The trapping magnetic field is constant in time. Therefore, it is not possible to inject electrons and trap the electrons in this field unless during the injection phase a part of the electron energy is absorbed by some friction process. This is accomplished by means of eddy currents generated on suitable passive circuits by the current of the injected electron bunch. This method has ben described elsewhere. However, in order to achieve an effective loss mechanism the current of the injected electron beam must be over one hundred amps. Such high current beams are difficult to handle except if the electron energy is high enough so that the electrostatic repulsive force is compensated to great extent by attractive magnetive forces. Hence the electron energy required is 5 Mev or higher. Other requirements on the electron layer yield the same result.

This report describes the economic geology of the Wiles area Ranger District, Texas.

Report documenting standard x-ray diffraction powder patterns for various compounds, intended to replace previous data or provide information for new substances. It describes the methods and, for each substance, outlines any previous data as well as information about the sample used and structural data, with a table of diffraction patterns.