From summary: "The hazards due to possible chemical explosion and detonation of the dissociation gases in homogeneous-reactor systems have been considered."

Report describing the temperature in the Brookhaven concrete shield proposed for the X reactor. The report details the methods and equations used to find the values that determined that the effect of the gun barrel assembly in cooling the concrete is negligible.

From abstract: "The present paper proposes a lattice test pile, (or LTP) as an alternate to the continuing program of building up and tearing down of exponential piles."

Memorandum presenting an experimental investigation of the elastic compressive buckling strength of plates with various configurations of integral stiffening. Some of the configurations tested included ribbing that was longitudinal, transverse, longitudinal, and transverse, and skewed at various angles to the sides of the plates to form a diamond or waffle-like pattern. The results indicate that the waffle-like stiffening is of sufficient structural interest to merit further study of the plastic buckling and fabrications aspects.

Report presenting experimental data from force and pressure tests on a large-scale, semispan, wing-fuselage model. Longitudinal force and moment characteristics are given for the model with various combinations of slat spans. The wing had 45 degrees of sweepback, an aspect ratio of 6, a taper ratio of 0.5, and an NACA 64A010 section normal to the quarter-chord line of the unswept panel and had partial-span slats, aileron, and double-slotted flaps equipped.

Memorandum presenting an investigation conducted in a modified turbojet engine to determine the cooling effectiveness of an air-cooled turbine-rotor blade employing a corrugated metal sheet brazed to the inner surface of the blade shell to increase the internal heat-transfer area. The corrugated fin blade had a lower integrated average wall temperature at the section investigated than the more promising shell-supported blade types previously investigated. Results regarding the temperature distribution investigation and pressure loss investigation are provided.

Memorandum presenting a study of the effect of free methyl radicals on the slow oxidation of both ethane and propane by means of a photochemical decomposition reaction in a static system. The introduction of methyl radicals into a mixture of propane and oxygen or ethane and oxygen substantially lowered the initiation temperature of the combustion of the hydrocarbon.

From Summary: "A supersonic free-jet facility (Mach number 3) capable of accommodating full-scale ram-jet engines has been constructed and evaluated. A 24-inch circular nozzle produces a jet of sufficiently uniform velocity that a good simulation of the engine internal flow is obtained. An annular diffuser placed around the engine recovers part of the total pressure of the jet flow passing outside the engine so that the pressure ratios which must be imposed across the facility to start and maintain the jet are kept to reasonable values."

Report presenting an investigation in the high-speed tunnel to determine the hinge-moment and control-effectiveness characteristics of a tapered, 35 degree sweptback, semispan wing equipped with an outboard 43-percent-span flap. Results regarding the lift, rolling-moment, and pitching-moment characteristics are provided.

Report presenting an experimental investigation to determine the performance of side inlets with external compression ramps and rectangular cowls mounted on the fuselage forebody of a proposed supersonic airplane. Results regarding supersonic Mach number range, subsonic Mach number of 0.63, and static or take-off conditions are provided.

Report presenting testing of an impulse-type supersonic compressor rotor with stators tested in Freon-12 over a range of equivalent tip speeds and weight flows. A static pressure ratio of 1.83 and an efficiency of 84.7 percent were obtained at 69.1 percent of the design speed of 1604 feet per second in air.

Report discussing some new requirements for satisfactory handling qualities due to the drastic changes in the speed range and configuration of airplanes. Longitudinal characteristics, lateral and directional stability and control characteristics, dynamic lateral and directional stability, and control effectiveness are described. Four categories of characteristics that may affect pilot control are included and ranked by level of severity.

Memorandum presenting a 10-stage axial-flow compressor designed for use as a research unit in which the problems associated with the compounding of high performance stages could be studied. The overall performance characteristics of the compressor, as determined experimentally, are included.

Report presenting the low-speed longitudinal stability characteristics of a wing with 45 degrees of sweepback of the quarter-chord line, an aspect ratio of 8, a taper ratio of 0.45, and NACA 63(sub 1)A012 airfoil sections parallel to the air streams investigated in the 19-foot pressure tunnel. Results regarding the basic wing, wing with fences, wing with trailing-edge flaps, wing with leading-edge flaps, a combination of both flaps, fences with the flaps deflected, leading-edge roughness, and the wing-fuselage combustion are provided.

Memorandum presenting an investigation conducted to explore the characteristics of metal-hydrocarbon combustion, to determine the effect of fuel-air ratio on the combustion efficiency, and to determine how the metal and hydrocarbon separately contribute to the overall combustion of several slurries. Results regarding an evaluation of the sampling method, combustion efficiency, effective metal weight fraction, effective hydrogen-carbon ratio, and heat of combustion per pound of air are provided.

Memorandum presenting a concept in aircraft design, which states that provision of a rolling moment in the direction of the turning rotation will be very effective, and may be necessary, for termination of any spin obtained. Current research indicates that wing sweep, use of heavy jet and rocket engines, in the fuselage, and long fuselage nose lengths are the primary causes of the changes in the nature of the spin and in the requirements for recovery.

"Measurements, principally with a hot-wire anemometer, were made in fully developed turbulent flow in a 10-inch pipe at speeds of approximately 10 and 100 feet per second. Emphasis was placed on turbulence and conditions near the wall. The results include relevant mean and statistical quantities, such as Reynolds stresses, triple correlations, turbulent dissipation, and energy spectra" (p. 1).

Abstract: "The complete freezing point diagram for the system uranium hexafluoride-hydrogen fluoride has been determined. In addition, liquid-liquid solubilities of these compounds have been measured up to the consolute temperature of 101 C. A miscibility gap starts at 61.2 C. over the compositions range 10 to 80 mole per cent uranium hexafluoride. The lowest melting point of this binary system under its own pressure, i.e. the eutectic, is -85 C."

Quarterly summary report of studies conducted through the Radiation Laboratory, University of California. Some results reported in the report may be of a preliminary or incomplete nature.

The document provides reports on medical and health physics, particularly on the biological studies of radiation effects, the metabolic properties of various materials, radiation chemistry, health chemistry, and health physics.

This quarterly progress report describes the ongoing research at the Metallurgy Division at the Oak Ridge National Laboratory. In particular, this report discusses the thorium research program, the slug problem, the preferred orientation and anisotropy in metals, fundamental studies of alloying, and the ANP program.

The dynamic characteristics of turbojet engine with variable exhaust nozzle area were investigated over a range of altitudes and flight Mach numbers. These characteristics generalize to standard static level condition. Data resulting from approximate step disturbances in either manipulated variable suggested functional relationships from which functions can be derived. The constants of the transfer functions are listed for five combinations of engine speed and exhaust nozzle area. The minimum data needed to completely define the transfer functions were: experimentally determined dynamic characteristics, such as engine time constant and initial rise ratio, resulting from either manipulated variable; static characteristics determined from steady-state performance curves.

Report presenting an investigation of the aerodynamic interference effects associated with a missile configuration, consisting of a pointed body of revolution with one or two ramjet engines strut-mounted in a vertical plane through the center line of the body, at several engine locations relative to the body and a range of angles of attack. The experimental data indicated increases in slope of the normal force curve with outward movement of the engines. Results regarding the characteristics of isolated components, characteristics of representative configurations, interference effects, and effect of engine location on lift-drag ratio are provided.

Experimental drag measurements at zero angle of attack for various theoretical minimum drag nose shapes, hemispherically blunted cones, and other more common profiles of fineness ratios of about 3 are compared with theoretical results for a Mach number and Reynolds number range of 1.24 to 7.4 and 1.0 x 10 to the 6th power to 7.5 x 10 to the 6th power (based on body length), respectively. The results of experimental pressure-distribution measurements are used for the development of an empirical expression for predicting the pressure drag of hemispherically blunted cones.