From abstract: "The distribution of uranyl nitrate was measured from aluminum nitrate and nitric acid solutions into diluted tri-n-butyl phosphate. This information is useful for designing solvent extraction processes for recovery of uranium from aluminum nitrate or nitric acid solutions."

Memorandum presenting the results of wind-tunnel oscillation tests to measure the rotary derivatives of a research airplane configuration at supersonic speeds. Measurements were made of the damping in yaw, pitch, and roll, the static longitudinal and directional stability derivatives, the effective-dihedral derivative, the rolling moment due to yawing, and the yawing moment due to rolling. The configuration was found to be statistically stable throughout the Mach number range, although its stability was becoming marginal at high angles of attack at Mach number 3.5.

Note presenting analytical results obtained for boundary-layer mass flow, momentum, total-temperature, and total-pressure recovery ratios of a scoop inlet with a height equal to the boundary-layer thickness and operating in a turbulent boundary layer, for flat and conical surfaces with wall cooling. The results indicate that design of boundary-layer intake devices or diverters must reflect the effects of wall cooling by either variable or compromised size.

A series of two-group calculations has been made on the Oracle for the purpose of obtaining critical-mass and flux distribution data for various ORR core configurations. The 3G3R code of Bate, Einstein, and Kinney was used, together with the RSP code developed by Nelson. This made it possible to obtain results for the three-dimensional case. The results, which are presented graphically, are intended to serve as a guide for the design of experiments until such time as actual measurements are available. The calculations were performed for the "clean cold" case, and it should be realized that the presence in the core of experiments and of fission products built up during operation will materially alter the flux patterns found. It is believed that the critical-mass data are accurate to within 10%. Within the fuel region it is believed that the thermal-flux patterns are the also accurate to this degree. Comparison of the results with MTR critical experiments, however, indicates that the thermal flux in the reflector in the vicinity of the fuel-reflector interface may have been underestimated by a factor of as much as 1.3. It should also be recalled that in a two-group calculation the "fast flux" is often a …

"A supplementary investigation has been conducted in the Langley 20-foot free-spinning tunnel on a l/24-scale model of the Grumman F11F-1 airplane to determine the spin and recovery characteristics with alternate nose configurations, the production version and the elongated APS-67 version, with and without empty and full wing tanks. When spins were obtained with either alternate nose configuration, they were oscillatory and recovery characteristics were considered unsatisfactory on the basis of the fact that very slow recoveries were indicated to be possible. The simultaneous extension of canards near the nose of the model with rudder reversal was effective in rapidly terminating the spin" (p. 1).

Report presenting an investigation to determine the effect of a distributed granular-type roughness on boundary-layer transition at several temperatures. The roughness was not found to introduce any disturbances of significant magnitude to influence transition. Surface cooling did not increase the value of the critical roughness Reynolds number for a distributed granular-type roughness either.

There have been numerous independent suggestions to use high speed shocks to heat deuterium gas to thermonuclear temperature (E. Teller, R.R. Wilson, H. Grad, W. Marshall)², and extensive experimental work in this field is being carried on by, e.g., Kolb³, and S. Janes⁴. Our own work in this field has been directed towards a fundamental understanding of the strong shock process in the limit of no particle collision, to find out if within this limit the ion heating following the passage of the shock is large enough to give rise to a thermonuclear reaction.

Memorandum presenting a fineness-ratio-2.71 right circular cylinder and a fineness-ratio-4.0 circular cylinder with a rounded nose and a flared afterbody tested in free flight over a range of Mach and Reynolds numbers. Time histories, cross plots of force coefficients, rolling velocity, and longitudinal-force coefficient are presented for both cylinders.

Report presenting testing of a fineness-ratio-2.71 right circular cylinder and a fineness-ratio-4.0 circular cylinder with a rounded nose and flared afterbody over a range of Mach and Reynolds numbers. Time histories, cross plots of force coefficients, rolling velocity, and longitudinal-force coefficient are provided for the two cylinders.

This report summarizes the research and development work carried out during June, July, and August, 1959, for Budget Activity 2790- Separations Development for Non-Production Reactors. The effort on Activity 2790 - Separations Development for Non-Production Reactors. The effort on Activity 2790 will enable Hanford to begin reprocessing in January, 1962, the fuel elements from power reactors which employ depleted or slightly enriched uranium fuels.

"A summary of the locations, extents, and intensities of turbulent areas encountered during a flight investigation of the jet stream is presented. The data were obtained from NACA VGH time-history records" (p. 1).

A report about the fabrication of dummy fuel-pls assemblies which are to be used in the engineering test loop at the MTR.

Report presenting an experimental investigation of several airplane configurations at Mach 3.0 in a continuous flow tunnel. The configurations had circular fuselage cross sections and a sweptback wing and either two nacelles or two side inlets.

Report presenting a two-dimensional high-speed cascade investigation of thin low-cambered NACA 65-series blade shapes at operating conditions typical of compressor tip sections. Testing occurred with porous walls and solid walls. Results regarding the variation of turning angle with Mach number, variation of turning angle with angle of attack, momentum loss, and schileren photographs are provided.

"Autocorrelation and frequency analyses of a series of aperiodic time events, in particular, filtered noises and sibilant sounds, were made. The position and band width of the frequency ranges are best obtained from the frequency analysis, but the energies contained in the several bands are most easily obtained from the autocorrelation function. The mean number of zero crossings of the time function was determined from the curvature of the latter function in the vicinity of the zero crossing, and also with the aid of a decimal counter. The second method was found to be more exact" (p. 1).

Report discussing testing on a high-thrust turbojet engine capable of operation at high flight speeds. The report presents the overall performance and blade-element performance of the engine at a specified hub-tip radius ratio and specific weight flow of air.

Report presenting an investigation in the supersonic pressure tunnel to determine the effects of various vertical positions of a wing and horizontal tail on the static longitudinal aerodynamic characteristics of a trapezoidal wing model. Results regarding effect of wing vertical position and tail-on characteristics are provided.

"Static longitudinal and lateral stability characteristics of a swept-wing fighter-bomber airplane model with a top inlet have been determined experimentally. In addition, vertical-tail effectiveness, spoiler effectiveness, effects of several store configurations, and effects of mass flow were investigated. Tests were made at Mach numbers of 1.6, 1.8, 2.0, 2.2, and 2.35 and Reynolds numbers, based upon mean aerodynamic chord, of between 2.0x10(exp 6) and 2.5x10(exp 6)" (p. 1).

From introduction: "This report provides background information regarding the study results presented in the first volume of this report and provides information resulting from the studies made on the gas cooled reactor concept."

Report presenting the thermodynamic and transport properties of high-temperature air in closed form starting from approximate partition functions for the major components in air and neglecting all minor components. The compressibility, energy, entropy, specific heats, speed of sound, coefficients of viscosity and thermal conductivity, and Prandtl numbers for air are provided for a range of temperatures and pressures.

Technical report was prepared by the Health and Safety Laboratory (HASL) with the objective of presenting a current picture of the Strontium Program. Abstract: Strontium 90 levels in fallout, milk, canned fish and tap water are summarized for data available up to February 30, 1958. Original data submitted during the month of February is included as an appendix. Data are presented to show the amount of Strontium 90 in fallout at sampling stations within and outside the United States.

Technical report was prepared by the Health and Safety Laboratory (HASL) with the objective of presenting a current picture of the Strontium Program. Abstract: Strontium 90 levels in fallout, milk, canned fish and tap water are summarized for data available up to February 28, 1957. Original data submitted during the month of February is included as an appendix. Data are presented to show the amount of Strontium 90 in fallout at sampling stations within and outside the United States.

Report presenting an anakysis of the quantitative effect of incomplete propellant vaporization on rocket-engine performance. Results regarding the effect of incomplete vaporization on engine performance and an interpretation of experimental data are provided.

"It is found that Prandtl-Meyer flow, in which chemical reactions are occurring and are in equilibrium, can be simply and exactly calculated. The property of air which governs the flow is found to be a quantity which depends only on the ratio of enthalpy to the square of the speed of sound; the analogous quality for an inert gas depends only on the ratio of specific heats. the maximum angle through which the flow may turn is generally larger when chemical reactions are occurring than it is in nonreacting air" (p. 1).