Maintenance of polarization of polarized protons in a linear accelerator is known to be feasible. Circular accelerators present a different problem, and the investigation of the interaction of orbit dynamics and particle polarization in general is undertaken. The equation of motion of the spin vector of a charged particle in a magnetic field as formulated by Bargmann, Michel, and Telegdi is utilized in the study of depolarization for several accelerators. High values of depolarization are obtained, and means for avoiding such depolarization are suggested. (D.C.W.)

"Flow-angle and pressure surveys behind five, thin, pointed-tip wings of varying plan form have been made at Mach numbers 1.62 and 2.41. Schlieren studies at a Mach number 1.93 for the same five plan-form wings were made to illustrate the behavior of the vortex sheet. The surveys were conducted at 1.5, 3, and 4 root chords behind three triangular wings of 50 degree, 63 degree, and 72 degree leading-edge sweep angle, and behind the 50 degree triangular wing reversed" (p. 1067).

The method of spherical harmonic tensors developed Mark for solving the Boltzmann transport equation in isotropic media is herein extended to anisotropic media for cylindrical geometry. A formal solution is given for the case of two concentric cylindrical media, A and B, but no numerical work has yet been done. The following treatment differs from a similar one by the H. K. Ferguson Co. in that the external medium B is assumed to be both a neutron absorber and finite in extent rather than a non-absorber and infinite in extent.

The problem of separation of beams of particles of different masses but of the same momentum at Bev energies is the subject of a great deal of study at several high energy laboratories. In this note we shall describe the problem and tabulate a few of the cogent parameters. Frequently the student of high energy interactions is faced with a beam of miscellaneous particles coming from an accelerator. By standard techniques this beam can be rendered approximately parallel and an inch or so in diameter. By passage through a magnetic field the beam can be analyzed in momentum. Now it frequently happens that the particles in which the experimenter is particularly interested make up only a small fraction of the beam and the exigencies of the proposed experiment may well demand that the background of undesired particles be drastically reduced. The problem is difficult because the velocities of the various particles are almost equal to each other and to the velocity of lights; this makes time-of-flight techniques relatively ineffective. The energies of the particles are almost equal so electrostatic separation also is difficult. Since the beam is already analyzed in momentum, further separation by magnetic means is impossible.

Report presenting two-group theory calculations to determine the effect of nonuniform uranium loading as compared to uniform loading on the reflector control effectiveness attainable in a large thermal reactor usable for aircraft power application. Results regarding reactivities and investments, uranium distributions, and power distributions are provided.

The solids in Purex lww were first observed during flowsheet tests for recovery of fission products from plant wastes. Since the nature of this solid was not apparent from the flowsheet composition of lww, some work was performed to characterize this material. Although this work has been conducted over a period of about one year, it has been subordinate to the main one of testing flowsheets for fission product recovery. The solids have been observed in each of about six samples of plant lww that have been studied, and the centrifuged volume of solids has been about four percent in each case.

The following report provides the results of an accelerated corrosion test that was performed to compare the effect of two coagulants on the corrosion rates of aluminum slug jacket alloy and 72S. Additionally, some analytical data on the water from the two treatments were obtained and are presented in this report.

The following report provides measurements of the crystalline structure of neptunium metal.

Abstract. Some rather idealized considerations are given regarding the depth a warped rod presses into the ribs at the places of contact. It appears that this distance may, under some conditions, be of the order of 70 times greater than for a straight rod resting uniformly on the ribs.

From Summary: "Drag measurements at transonic speeds on rectangular airfoils and on airfoils swept back 450 are reported. These airfoils, which were mounted on cylindrical test bodies, are part of a series being tested in free drops from high altitude to determine the effect of variation of basic airfoil parameters on airfoil drag characteristics at transonic speeds. These rectangular and swept-back airfoils had the same span, airfoil section (NACA 65-009), and chord perpendicular to the leading edge. The tests were made to compare the drag of rectangular and sweptback airfoils at a higher aspect ratio than had been used in a similar comparison reported previously."

"Drag characteristics of a series of related conical and circular-arc afterbodies are presented for Mach numbers from 0.6 to 1.3. Drag was obtained from pressure measurements on the boattail and solid base. The boattail angles tested ranged from 0 degrees to 45 degrees for ratios of base diameter to maximum body diameter ranging from 0 to 1.0" (p. 1).

Report presenting an investigation in the free-flight tunnel to determine the dynamic longitudinal stability and control characteristics of tandem-coupled bomber-fighter airplane models. Results regarding bomber alone tests, freely coupled combination, and rigidly coupled combination are provided.

"Data for a liquid-cooled engine with a displacement volume of 1710 cubic inches were analyzed to determine the effect of exhaust pressure on the engine cooling characteristics. The data covered a range of exhaust pressures from 7 to 62 inches of mercury absolute, inlet-manifold pressures from 30 to 50 inches of mercury absolute, engine speeds from 1600 to 3000 rpm, and fuel-air ratios from 0.063 to 0.100. The effect of exhaust pressure on engine cooling was satisfactorily incorporated in the NACA cooling-correlation method as a variation in effective gas temperature with exhaust pressure. Large variations of cylinder-head temperature with exhaust pressure were obtained for operation at constant charge flow" (p. 1).

The stator-blade angles in the twelfth to fifteenth stages of a 16-stage high-pressure-ratio axial-flow compressor were decreased 3 deg The over-all performance of this compressor is compared with the performance of the same compressor with standard blade angles. The matching characteristics of the modified compressor and a two-stage turbine were also obtained and compared with those of the compressor with the original blade angles and the same turbine.

Report presenting the results of an investigation to determine the pressure ratios required to operate a slotted tunnel through a range of Mach numbers where the speed variation is affected by removal of air from the main stream by auxiliary pumping, use of a main-stream-operated ejector located downstream of the test section, and a combination of these methods. Testing was conducted in order to improve the accuracy of transonic wind-tunnel testing.

Report presenting a flight and preflight evaluation of an automatic thrust-coefficient control system in a twin-engine ram-jet missile. A flicker-type single-loop servocontrol system is shown to be a usable way of controlling ram-jet thrust coefficients.

"A number of noise-suppression nozzles were tested on full-scale engines. In general, these nozzles achieved noise reduction by the mixing interference of adjacent jets, that is, by using multiple-slot-nozzles. Several of the nozzles achieved reductions in sound power of approximately 5 decibels (nearly 70 percent) with small thrust losses (approx. 1 percent). The maximum sound-pressure level was reduced by as much as 18 decibels in particular frequency bands" (p. 1249).

The following report describes the investigations of the microwave solution and the Astron solution, to produce high current electron beams.

Report presenting an investigation at Mach number 1.61 to determine the hinge-moment characteristics of seven tip controls on a 60 degree sweptback delta wing. Testing occurred over a range of angles of attack and control deflection. The results indicated that the most important parameter in designing delta-wing tip control is the ratio of control-surface area ahead of the hinge line to total control-surface area.

A prototype sampler for obtaining samples of high radioactive UO2SO4 solution for use in the HRT is presented. It was successfully operated in conjunction with a low pressure water system and a high pressure, high temperature UO2SO4 system.

From introduction: "The following recommendations represent the best estimate, based on present knowledge, of the requirements for generally applicable or "universal" instrument for the continuous monitoring of radioactive process streams in terms of their gamma activity."

This report follows calculations performed to determine the effect of epithermal capture on the value of eta to be used in lattice calculations.

"A ring circuit is a succession or two-port networks and at least one three-port network, each feeding the next at one port and the last feeding the first so that the sequence closes on itself leaving at least one input port. The input admittance is derived in terms ef various matrices describing the circuit for one- and two-input port rings."

Report presenting an investigation of a supersonic aircraft configuration and various combinations of its components at a range of Mach numbers. Longitudinal- and lateral-force characteristics of the configurations, as well as longitudinal- and lateral-stability derivatives, are provided.