Uranium was plastically deformed 90% at room temperature by unidirectional rolling to a foil 0.002-inches thick. Specimens were recrystallized in the alpha region and several pole figures obtained from 0 to 40 degrees. From these, the preferred orientation was found to be in a spread of idealized (11) [010] about [010].

A production test composed of preformed zirconium samples was prepared by R. S. Kemper of the Physical Metallurgy Unit⁽¹⁾ to determine the effect of exposure time and the influence of prior mechanical cold work on changes occuring [sic.] during irradiation. The first section was delivered to Radiometallurgy Unit is April, 1954, for examination after an exposure of 190 MWD/AT.

"Results are presented of a free-flight investigation between Mach numbers of 0.7 to 1.3 and Reynolds numbers of 3.1 x 10(exp 6) to 7.0 x 10(exp 6) to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. This missile has a wing, body, and vertical tail, but has no horizontal tail. The basic wing plan form has an aspect ratio of 5.5, 45 deg of sweepback of the 0.406 streamwise chord line, and a taper ratio of 0.4" (p. 1).

Memorandum presenting results of a free-flight investigation over a range of Mach and Reynolds numbers to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. The missile has a wing, body, and vertical tail, but has no horizontal tail. Results regarding basic data, drag, trim, lift and static stability, damping, and static pressure are provided.

Report presenting drag measurements on models of 20 isolated external stores and nacelles flown from the helium gun at a range of Mach numbers. Results regarding fineness-ratio and shape effects, drag correlation, and friction drag are provided. Generally, the shape variations among the various types of stores and nacelles had the expected effects on isolated body drag.

Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.6 in which separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The store was separately sting-mounted on its own six-component internal balance and was traversed through a wide systematic range of spanwise, chordwise, and vertical positions.

Report presenting an evaluation of convective heat-transfer coefficients from skin temperatures measured along the body of a research model designated NACA RM-10. Heat-transfer data is presented for a range of Mach and Reynolds numbers based on the axial distance from the nose to the point at which the temperature measurements were made. Results regarding the recovery factor, heat transfer, correlation with different aircraft models, and Reynolds analogy are provided.

"Tests have been conducted in the Langley 8-foot transonic tunnel on a 0.04956-scale model of the Convair F-102A airplane which employed an indented and extended fuselage, cambered wing leading edges, and deflected wing tips. Force and moment characteristics were obtained for Mach numbers from 0.60 to 1.135 at angles of attack up to 20 degrees. In addition, tests were made over a limited angle-of-attack range to determine the effects of the cambered leading edges, deflected tips, and a nose section with a smooth area distribution" (p. 1).

Report presenting performance testing of a supersonic compressor designed for a tip speed of 1400 feet per second, a pressure ratio of 2.0, and a corrected weight flow of 30.5 pounds per second. The overall performance results of the rotor alone at design speed gave a pressure ratio of 2.17, an adiabatic efficiency of 89 percent, and a weight flow of 28 pounds per second. A comparison with the predicted design results is provided.

Report presenting an investigation of transient operation of a turboprop engine in an altitude wind tunnel at 35,000 feet over a range of Mach numbers to determine the effect of flight speed upon the dynamic response of the engine. The generalized time constant of the engine-propeller combination varied with flight speed and power level.

An electrical conductivity technique was developed to determine the dilution-displacement rate of an electrolyte in a well from which data the velocity of the water through the well can be calculated. The electrical current flow between two of the electrodes in a well drops proportionately with the dilution and the displacement of the electrolyte by fresh water entering the well. The drop of electrical current flow over a period of time was applied to a derived equation to obtain a value for ground water velocity. The technique gives results comparable to other methods and some problems of the standard methods of measuring ground water velocity are eliminated. However, a correction factor for porosity of the aquifier must be used in the derived equation. Porosity values are not adequately known in most cases, therefore the ground water velocity figures are generally relative rather than absolute.

A method to determine the correction to Grüneisen's law corresponding to the effect of the electrons at high pressure. It is assumed that the lattice contribution to the pressure is small and that the equation of state of the solid can be approximated by results of the statistical Thomas-Fermi atom model for the electron pressure.

Report presenting an investigation of 47 experimental tubular designs embodying variable primary-air openings to control the fuel-air ratio in the combustion zone at simulated high-altitude operating conditions for a representative 5.2-pressure-ratio engine. The performance characteristics considered were combustion efficiency, operating range, and pressure loss. Results regarding the effect of fuel injector design, effect of primary-air baffles, and performance characteristics of the best models are provided.

The objective of this report is to set forth the design of automatic mechanical equipment developed for use with HAPO nondestructive test instruments.

Memorandum presenting performance investigations of 13 fuels - five hydrocarbons, four oxygenated hydrocarbons, and four substituted hydrocarbon-type fuels - conducted in a single tubular turbojet combustor in order to determine a possible relation between combustor performance and fuel properties. Combustor temperature rise and combustion efficiency were determined at a variety of air-flow rates, inlet-air total temperatures, and a range of heat-input values.

Report presenting an investigation of methods of increasing the stable subcritical range of a twin-duct double-ramp inlet mounted on the sides of a fuselage forebody in the supersonic wind tunnel. Results regarding the stabilization with high performance and low-mass-flow stabilization are also provided.

Report presenting an investigation of the estimated minimum cooling requirements and related performance of turbojet engines equipped with high-performance single-stage turbines with air-cooled corrugated-insert blades over a range of turbine-inlet temperature, tip speed, and hub-tip radius ratio for Mach number 2 at 50,000 feet. The effects of stress-ratio factor, flight Mach number, altitude, turbine rotor impeller efficiency, and outside heat-transfer coefficient on cooling requirements were also investigated.

Report presenting an investigation to determine the effect on performance of two methods of throat-area modulation of two convergent plug nozzles. Data were obtained over a range of pressure ratios. Results regarding the performance of the translatable outer-shell-type plug nozzle, performance of the iris-outer-shell-type plug nozzles, sensitivity to throat-area variation, and air-flow parameter are provided.

This report describes the evaluation of physical properties of AGHT and 185-W graphites that are important to pile construction and operation. On the basis of these data, purified AGHT graphite was allocated to either filler block positions in the central regions of the K piles or to the upper or lower reflectors. This decision was based on the similarities of physical properties between AGHT graphite and the other moderator components. A similar allocation could be made for 185-W graphite for some future pile if it can be successfully purified or if purification is not required.

Free jet tests of 48 inch diameter ramjet combustor with annular can-type flame holder.

Report presenting an investigation in an NACA free-jet facility of a ramjet engine with an experimental 48-inch-diameter combustor. Three combustor lengths and three fuel-distribution systems were investigated over a range of fuel-air ratios and at two air flows. Results regarding the combustor performance and ignition data, velocity profile, and starting characteristics are provided.

"A ram-jet engine with an experimental 48-inch-diameter combustor was investigated in a free-jet facility. The combustor design comprised a large-volume annular pilot region and an array of sloping baffle- or gutter-type flameholders. The combustor was intended to operate at a fuel-air ratio of about 0.037" (p. 1).

Report presenting an investigation in a free-jet facility of a ramjet engine with an experimental 48-inch-diameter combustor. Three combustor lengths, three lengths of the shroud which separated the bypass air from the burning stream, and four fuel-distribution systems were investigated over a range of fuel-air ratios and a range of engine air flows. Results regarding the engine performance and ignition data, effect of fuel profile on combustion efficiency, total-pressure ratio, and distribution of static pressure in the main air stream are provided.

A large (size 2) Purex pulse generator was installed in the 321 Building Tan Farm to pulse solutions in the prototype Purex HA Column. Flow sheet considerations indicated a need for information on leakage rates with various size weep holes in the pulse generator piston. In addition to leakage tests, experiments were conducted to determine the air required under the piston to hold the column contents away from the pulse generator piston thereby preventing leakage during shut down and the determine the time required to bleed the air trapped in the pulse leg when the column is first filled. [...] Leakage past the piston was not appreciably affected by pulse frequency. [..] Bleeding the air out of the pulse leg under start-up conditions, even with the piston weep hole plugged, was rapid. The longest time required to bleed the pulse leg was 36 minutes, which included a column-filling time of 30 minutes.