This report describes the results of a study to determine the mechanical properties of joining stainless steel tubes to stainless steel tube sheets and evaluating the joint types made by various combinations of rolling and welding.

A number of questions have arisen in regard to the interpretation of personnel monitoring results reported to users of the Brookhaven neutron monitoring service. The original announcement was rather brief and did not contain most of the technical characteristics upon which an evaluation of results must be based. The following paragraphs have been composed with the hope that they will clarify the meaning of the exposure reports.

Memorandum presenting an investigation of variable-area auxiliary inlets intended to provide for the variation of engine air requirements with speed and altitude. Three auxiliary scoop inlets were tested in combination with a nose inlet at a range of Mach numbers tested at zero angle of attack.

Report presenting free-flight and free-jet testing of a twin side-inlet configuration, including a pilot's canopy and a wheel-well fairing, between a range of Mach numbers from 0.8 to 1.55. Using side inlets provides two important advantages: the inlet can be located closer to the engine and it frees up the nose for other uses. Results regarding the effects of oscillating flow, external-drag coefficient, and total-pressure recovery are provided.

Report presenting an experimental investigation of pressure disturbances caused by the reflection of two-dimensional shock waves from a slotted boundary at Mach numbers between 1.0 and 1.5. Simple-wedge airfoils with three different apex angles were used to generate shock waves and the static pressures ere measured at various points along the surface of each airfoil.

Report presenting testing of a multiweb wing structure, representing an airplane or missile wing, under simulated supersonic flight conditions to determine the transient temperature distribution. The aerodynamic loads caused the model to fail near the end of the test. The failure is analyzed and it is determined that the model failed as a result of the combined action of aerodynamic heating and loading.

Report presenting a connected-pipe investigation to evaluate a can-type combustor configuration and to develop the configuration to give a wide operable fuel-air ratio range of high combustion efficiency. Results regarding the wind-tunnel tests and connected-pipe tests are provided.

Report presenting theoretical values of rocket performance parameters for two mixtures of liquid ammonia and hydrazine with flourine as oxidant for a variety of parameters. Parameters included are specific impulse, combustion chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity.

Report presenting theoretical values of rocket performance parameters for two mixtures of liquid ammonia and hydrazine as fuels with liquid fluorine as oxidant. The parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity.

Report presenting an investigation to determine the effects of geometric dihedral on the aerodynamic characteristics of wing-fuselage combinations with wings of aspect ratio 4, taper ratio 0.6, and angles of sweep of 3.6 and 45 degrees at the quarter-chord line. Little analysis is provided, but the results indicate that the effect of geometric dihedral on the effective-dihedral parameter is slightly larger than predicted at angles of attack of about 6 degrees.

From a theory developed on a quasi-one-dimensional-flow basis, it is found that the stability of the ram jet is dependent upon the instantaneous values of mass flow and total pressure recovery of the supersonic diffuser and immediate neighboring subsonic diffuser. Conditions for stable and unstable flow are presented. The theory developed in the report is in agreement with the experimental data of NACA-TN-3506 and NACA-RM-L50K30. A simple theory for predicting the approximate amplitude of small pressure pulsation in terms of mass-flow decrement from minimum-stable mass flow is developed and found to agree with experiments.

Data were obtained in non-flowing and flowing (continuous) batch adsorption systems to serve as a guide to the operating conditions that should be used in a resin-in-pulp adsorption system for the recovery of uranium from ores.

"An investigation has been made in the NACA Lewis icing research tunnel to determine the aerodynamic and icing characteristics of a full-scale induction-system air-scoop assembly incorporating a flush alternate inlet. The flush inlet was located immediately downstream of the offset ram inlet and included a 180 deg reversal and a 90 deg elbow in the ducting between inlet and carburetor top deck. The model also had a preheat-air inlet" (p. 1).

Memorandum presenting an investigation in the icing research tunnel to determine the aerodynamic and icing characteristics of a full-scale induction-system air-scoop assembly incorporating a flush alternate inlet. Results regarding the ram-inlet tests, alternate-inlet tests, and preheat-air tests are provided.

A "particle" of charge Ze moves with velocity v, mass M, energy [formula], through a "substance" of atomic number Zo, density N atoms/cm3. We have to consider the process of slowing down, and the nature of the trail of ions produced. Very slow particles are of little interest, as their range is very short. If Z is large, or if the particle is an electron, there are complications which we postpone. Thus, our considerations will apply particularly to protons, deuterons, o< -particles, and mesons.

Ionization measurements of water vapor in vapor-liquid equilibrium were made with a series of chambers on a tritiated water sample which was prepared by burning T2 to T2O and diluting it with H2O. A correction was made for the difference of vapor pressures of HTO and H2O. The effect of HTO adsorbed on chamber walls and electrodes was eliminated from the final result. Using Gerbes data on the number of electron volts to produce an ion pair in air, agreement obtained between the measured source strength and the source strength as computed from pressure, temperature, volume, purity, and dilution data on the original gaseous T2 sample.

An experimental investigation has been conducted in the Langley stability tunnel at low speed to determine the pitching stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient, control deflections, and propeller blade angle were investigated. The tests were made through an angle-of-attack range from about -4deg to 29deg, and the thrust coefficient range was from 0 to 0.7. In order to expedite distribution of these data, no analysis of the data has been prepared for this paper.

Report describing potential correlations of magnetic susceptibilities of the elements thorium, uranium, and plutonium with their crystal structures.

Report presenting results of a systematic study in the 8- by 6-foot supersonic wind tunnel to determine the effect that area distribution in the subsonic diffuser might have on stability and overall performance of conical-type supersonic diffusers. Drag, pressure recovery, and mass flow are presented for five diffusers designed for maximum mass flow at Mach number 2.0.

Report presenting a series of turbine wheel designs made for a turbojet engine with an axial-flow compressor. The designs were made to determine the influence of air-cooling on overall engine design, weight, critical-material content, and complexity and to assist with construction of research model full-scale turbines.

"Eighty pounds of butylsilanes required for test purposes was synthesized by reducing butyltrichlorosilane with lithium aluminum hydride in dioxane solution. This was safely and successfully accomplished by operating in steel equipment under an atmosphere of oil-pumped nitrogen to minimize the hazards involved in conducting this operation on a large scale. The apparatus and procedure used to carry out the necessary manipulations are described in this report" (p. 1).

Summary: "The quantity of water adsorbed by graphite at various relative pressures has been determined and the data are presented in graphical and tabular form."

A series of measurements of ε in slightly enriched uranium, light water lattices is presently under way at Brookhaven. Figure 1 shows ε as a function of water-to-metal ratio for .600" diameter rods, of 1.3% enrichment. Because of interaction between neighboring groups of rods, ε increases rapidly as the water-to-metal ratio decreases.

The previous calculation of the energy spectrum of the high energy deuteron beam from the stripping of He3 (UCRL-2150) was thought to be in error, especially as regards the low energy tail, on the basis of some experiments with the neutron time-of-flight detector, which indicated a considerably narrower spectrum than that calculated in UCRL-2150. Since the value used for the attenuation cross section of deuterons in uranium is considerably lower than that presently considered correct a new calculation was made using this latter cross section. Since the equations used in this new calculation differ somewhat from those used in the previous report a brief derivation is given here.