From abstract; "Two basic instruments were developed for determining the concentration of uranium in solutions. Both instruments detect the gamma activity present in a sample solution, and interpret this analysis into direct presentation as parts per million."

A report about volcano response plans. It discusses a four-level color code with successive conditions. For instance, green means no risk while red means an eruption is occurring.

Report discussing waste line methods for separation plants at Hanford Works. A discussion of existing and proposed methods, including methods of protection for lines are included.

Abstract: Force, moment, and center of pressure information are presented for four models of the Hi-Lo configuration.

Report presenting an investigation of the possibility of utilizing the relatively good characteristics of the spike-type diffuser in the supersonic compressor. Results regarding the overall performance, inlet conditions, outlet conditions, entrance flow conditions, and estimated performance of subsonic portion of rotor passage are provided.

Report presenting an investigation to determine the effect of ground on the low-speed aerodynamic, control, and control hinge-moment characteristics of a 3-percent-thick, delta-wing-fuselage configuration. Aerodynamic forces and moments and hinge-moment data were obtained for a range of angles of attack, ground heights, and a designated Mach and Reynolds number.

From Summary: "Sound pressure levels, frequency spectrum, and jet velocity profiles are presented for an engine-afterburner combination at various values of afterburner fuel - air ratio. At the high fuel-air ratios, severe low-frequency resonance was encountered which represented more than half the total energy in the sound spectrum. At similar thrust conditions, lower sound pressure levels were obtained from a current fighter air craft with a different afterburner configuration. The lower sound pressure levels are attributed to resonance-free afterburner operation and thereby indicate the importance of acoustic considerations in afterburner design."

Memorandum presenting a performance investigation using hydrogen fuel in a full-scale afterburner conducted with particular study of fuel-injector configurations and afterburner length. A total of seven fuel-injector configurations, grouped by type as concentric ring or radial bar, were investigated at a specified burner-inlet velocity and range of burner-inlet total pressures.

Report presenting the results of an investigation at supersonic speed of the distribution of pressure over the surface of a swept airfoil of biconvex section at various angles of attack. The measurements are compared with supersonic lifting-surface theory, which generally indicated good agreement except over the regions of the airfoil influenced by the subsonic trailing edge and the tips. Results regarding the pressure distribution, boundary-layer studies, and normal force and pitching moment are provided.

In an experimental investigation of local recovery factors for a blade having a pressure distribution similar to that of a typical reaction-type turbine blade, it a was found that the recovery factors were essentially independent of Mach number, Reynolds number, pressure gradient, and position on the blade surface except for regions where the boundary layer was probably in the transition range from laminar to turbulent. The recommended value of local subsonic recovery factor for use in calculating the effective gas temperature for gas turbine blades was 0.89.

An approximate method for development of flow and thermal boundary layers in laminar regime on cylinders with arbitrary cross section and transpiration-cooled walls is obtained by use of Karman's integrated momentum equation and an analogous heat-flow equation. Incompressible flow with constant property values throughout boundary layer is assumed. Shape parameters for approximated velocity and temperature profiles and functions necessary for solution of boundary-layer equations are presented as charts, reducing calculations to a minimum. The method is applied to determine local heat-transfer coefficients and surface temperature-cooled turbine blades for a given flow rate. Coolant flow distributions necessary for maintaining uniform blade temperatures are also determined.

Report presenting an investigation of a nacelle at various chordwise positions and vertical locations on a semispan model of a wing with and without a fuselage through a range of Mach numbers. The investigation was made to determine the interference characteristics between the nacelle and the model and to determine the effect of the fuselage on nacelle interference.

Report presenting a method for predicting wing-tail interference as applied to the calculation of tail efficiency parameters, lift characteristics, and center-of-pressure locations for a series of generalized missile configurations. The calculations are also compared to experimental data. The rolled-up vortex concept appears to give good results in the prediction of tail efficiency with angle of attack for inline configurations.

Report presenting an investigation to develop a high-combustion-efficiency turbojet combustor with pressure losses typical of those encountered in current turbojet engines. A total of 13 air-entry hole modifications was investigated to obtain a combustor design with high combustion efficiencies and a satisfactory outlet radial temperature profile. Results regarding combustor development and the performance of Model 28I are provided.

Memorandum presenting flight and wind-tunnel measurements made of the low-speed stalling characteristics on a swept-wing jet aircraft. Included in the study are the effects on the stalling characteristics of a number of wing modifications. Results regarding the roll-off characteristics and maximum lift and stalling characteristics are provided.

Report presenting sound pressure levels, frequency spectrum, and jet velocity profiles for an engine-afterburner combination at various values of afterburner fuel-air ratio. Lower sound pressure levels were obtained from a current fighter aircraft with a different afterburner configuration. Results regarding the jet temperature, jet Mach number and velocity, and sound measurements are provided.

The following report describes a reactor that was designed to provide a research facility for testing various materials in a high intensity radiation field.

In the course of the development at Argonne of high purity uranium metal in ingot form, some questions arose as to the validity of the chemical analyses of some of the impurities (particularly those for carbon, boron, and silicon), with one analytical laboratory reporting concentrations in some instances of an order of magnitude greater than another laboratory. Since the low concentrations of impurities in this material involved, in some cases, the development of modified analytical procedures and standards, it was decided to check these discrepancies by having identically prepared samples analyzed by several AEC and associated laboratories. This report is a compilation of the results obtained.

From foreword: "This report represents the most current methodology available for wetland classification and culminates a long-term effort involving many wetland scientists."

Report presenting exploratory measurements of the fluctuations of wing bending moment during normal performance and wind-tunnel testing of a model of the Douglas D-558-II from Mach numbers 0.60 to 0.96. The effects of leading-edge chord-extensions and pylon-mounted underwing external stores were investigated. Results regarding the general nature of buffeting measurements, frequency distribution of buffeting response, interpretation of model buffeting measurements, and effects of changes in model configuration are provided.

From Introduction: "Presented in this report are the basic data obtained from investigation. The data are presented with limited analysis in order to expedite their availability to those concerned with jet-exit-afterbody design."

Report presenting a performance investigation using hydrogen fuel in a full-scale afterburner with particular study of fuel-injector configurations and afterburner length. A total of seven fuel-injector configurations, some concentric ring and some radial bar, were investigated at a specified burner inlet velocity over a range of burner-inlet total pressures.

From Summary: "An investigation has been conducted on a V-1650-7 engine to determine the cylinder temperatures and the coolant and oil heat rejections over a range of coolant flows (50 to 200 gal/min) and oil inlet temperatures (160 to 2150 F) for two values of coolant outlet temperature (250 deg and 275 F) at each of four power conditions ranging from approximately 1100 to 2000 brake horsepower. Data were obtained for several values of block-outlet pressure at each of the two coolant outlet temperatures. A mixture of 30 percent by volume of ethylene glycol and 70-percent water was used as the coolant."

"The temperature effects on the attenuation of K-band microwaves, at a frequency of 26,500 plus or minus 30 megacycles per second, through natural-gas and propane flames containing added alkali halide salts, were investigated over a temperature range from 1900 to 2500 K. The preliminary data of this investigation indicated that the attenuation varies appreciably with the sodium-line-reversal temperatures of the flames and is independent of the particular hydrocarbon fuels that were used for temperature sources and of the particular halide components of the compounds used in the concentrations employed to produce easily measurable attenuation. A reproducibility of plus or minus 25 K was obtainable" (p. 1).