The following report analyzes results from studies made while applying chelating agents to ion exchange separations of the elements americium and curium.

Abstract: "A description of the demand computer and its functions is given. Methods of testing and adjusting, and gain and response curves for the system and its parts are included."

Quarterly progress report describing work related to a study of radiation physics problems involved in the design of high-level cesium-137 gamma sources. It outlines work completed and ongoing goals for the project.

Memorandum presenting testing of an NACA 65(sub 06)A004 airfoil to determine the effects of a solid-strip spoiler on buffeting forces. Fluctuations of both section normal-force coefficient and of section pitching-moment coefficient are presented as functions of angle of attack and of section normal-force coefficient. Generally, the spoiler decreased the fluctuating section normal-force and pitching-moment coefficients if comparison is made at constant angle of attack and increased these coefficients if comparison is made at constant section normal-force coefficient.

Report presenting an experimental investigation to assess the effects of sweep and taper ratio on the longitudinal characteristics of a wing-body combination at a range of Mach numbers. The results indicated that increased leading-edge sweep caused a progressive decrease in lift-curve slope and the variation of Mach number of the lift-curve slope and static longitudinal stability. Results regarding the effect of sweep, effect of taper ratio, and comparison with results of a previous investigation are provided.

Report presenting the results of a wind-tunnel investigation to determine the effects of a variation in wing taper ratio on the longitudinal characteristics of a wing-body combination at a variety of Mach numbers. The wings had an aspect ratio of 3, an unswept midchord line, and an NACA 64A003 profile. Results regarding the lift and pitching-moment characteristics and drag characteristics are provided.

"This report covers fire tests conducted on an experimental design of a wooden-jacket shield for radioisotope shipping containers" (p. i).

Report presenting studies of the final attack phase of an automatically controlled interceptor in flight and electronic simulators to investigate various airplane command and stabilization networks and to develop simple but adequate simulation techniques for the synthesis of automatic control systems. Results regarding automatic control with a simple command system, automatic control with the improved command system, and evaluation of the automatic control system in typical final attack maneuvers are provided.

Force and pressure-recovery characteristics of a nacelle-type conical-spike inlet with a fixed-area bypass located in the top or bottom of the diffuser are presented for flight Mach numbers of 1.6, 1.8, and 2.0 for angles of attack from 0 degrees to 9 degrees. Top or bottom location of the bypass did not have significant effects on diffuser pressure-recovery, bypass mass-flow ratio, or drag coefficient over the range of angles of attack, flight Mach numbers, and stable engine mass-flow ratios investigated. A larger stable subcritical operating range was obtained with the bypass on the bottom at angles of attack from 3 degrees to 9 degrees at a flight Mach number of 2.0. At a flight Mach number of 2.0, the discharge of 14 percent of the critical mass flow of the inlet by means of a bypass increased the drag only one-fifth of the additive drag that would result for equivalent spillage behind an inlet normal shock without significant reductions in diffuser pressure recovery.

it is desired to know the accuracy and precision of uranium content determination with the γ-photometer. Several possible sources of error (involving both bias and variability) arise when the problem is fully considered. As analysis of data collected for the evaluation of this technique has progressed, there has been a continued discovery of new sources of error and bias further complicating this evaluation. These possible sources have not yet all been systematically examined and thus a complete answer cannot be given at this time. The following is an attempt to state the problem and make recommendations concerning its over-all solution. These recommendations are not assumed to be the totality of those possible; however, they will provide a starting point.

"The influence of triangular-shaped end plates on the lift and the flow field of a canard-type control surface mounted on a symmetrical fuselage was investigated in the Lewis 8- by 6-foot supersonic wind tunnel at a Mach number of 2.00, body angle of attack of 2 degrees, and control-surface deflection angles of 3 degrees, 6 degrees, 8 degrees, and 10 degrees. The investigation demonstrated that the addition of end plates to a canard-type control surface increased its lift and rearranged the single vortex into a two-vortex system. Perforating the end plates reduced these effects and resulted in a decrease in lift and a change in the flow-field characteristics" (p. 1).

Report presenting an investigation in the transonic blowdown tunnel at Mach numbers from 0.63 to 1.41 to determine increments in lift, drag, and pitching moment of a sweptback semicircular air inlet installed in the root of a 45 degree sweptback wing. Results regarding internal pressures and inlet performances are provided.

Report presenting testing of two beams of three web types which were loading in bending and subjected to rapid skin heating at rates from about 50 to 70 degrees Fahrenheit per second. The investigation was meant to determine some of the effects that rapid skin heating would have on the buckling and failing strength of multiweb-wing structures. The three types of web tested included the channel web, corrugated web, and truss web.

This report is a description of a method of propelling airplanes by the reaction of jet propulsion. Air is compressed and mixed with fuel in a combustion chamber, where the mixture burns at constant pressure. The combustion products issue through a nozzle, and the reaction of that of the motor-driven air screw. The computations are outlined and the results given by tables and curves.

Report presenting an investigation of zero-lift drag of a fin-stabilized wing-body combination from high-subsonic to supersonic speeds in a range of Reynolds numbers. The wing was unswept about the 74.5-percent-chord line, an aspect ratio of 3.04, a taper ratio of 0.394, and 4.5-percent-thick modified hexagonal airfoil sections. Results regarding total drag, wing-plus-interference drag, and base pressure are provided.

The Lindemann assumption of direct contact of neighboring atoms at fusion is replaced by the criterion that melting occurs when the root-mean-square amplitude of thermal vibration reaches a critical fraction ρ, presumed the same for all isotropic monatomic solids, of the distance of separation of nearest-neighbor atoms. The Debye-Waller theory of the temperature dependence of the intensity of Bragg reflection of x-rays is used, without further assumptions, to derive a generalized Lindemann law. In contrast to the Lindemann form, all physical quantities involved in this formulation are evaluated at the fusion point, and departure of the average energy of an atomic oscillation from the equipartition value is taken into account by the quantization factor of the Debye-Waller theory. If the Grüneisen constant γm of the solid at fusion is evaluated by its definition from the Debye frequency of the solid, use of the generalized Lindemann law and Clapeyron's equation permits one to express γm in terms of the bulk modulus of the solid at melting and the latent heat and volume change of fusion. By means of Grüneisen's law applied to the solid at fusion, γm can be expressed likewise in terms of the corresponding bulk modulus, thermal expansion, volume, …

Abstract: Both direct and coincidence counting apparatus are described. The elimination of cosmic ray events by coincidence plus gamma ray shielding permits the reduction of counting rates far beyond that obtainable with shielding alone. By selection of materials and development of new components and techniques, the residual background count of beta counting equipment can be reduced to a very low value. Geiger counter equipment for routine laboratory measurements is described, have a background count of 0.7 c/m. Scintillation counters are shown to have a background of 0.2 c/m at 30% efficiency. A portable Geiger counter with a 3.7 c/m background is also described.

This report discusses the mathematical and statistical questions concerned with the estimation of a leak rate from data collected during a reactor containment vessel pressure test such as that performed on the PRTR vessel in May, 1959. A mathematical method is suggested in Section 3 for the construction of a total number of gas molecules in the containment vessel time series using vessel absolute pressure and temperature readings at several positions within the vessel. A formula for the precision of the series is given in terms of the individual instrument precisions. The question of accuracy and its relationship to the temperature gradient within the vessel is also considered.

From Summary: "Flight tests have been made to determine the longitudinal stability and control and stalling characteristics of a North American P-51H airplane. The results indicate that the airplane has satisfactory longitudinal stability in all the flight conditions tested at normal loadings up to 25,000 feet altitude. At Mach numbers above 0.7, the elevator push force required for longitudinal trim decreased somewhat because of compressibility effects."

From introduction: "This article constitutes the third of a series of three papers on the "direct" measurements of the meson masses by the "Hp vs. Range" mass ratio method...The study here reported is a logical extension of the pion-proton mass ratio technique."

Abstract. a method of recovering thorium from slag from the bomb process of producing thorium has been developed. HCl and NaOH are the only chemicals required in quantity. Materials required for a representative slag are given.

"In connection with the study of aircraft and propeller noises, the National Advisory Committee for Aeronautics has developed an instrument for sound-frequency analysis which differs fundamentally from previous types, and which, owing to its simplicity of principle, construction, and operation, has proved to be of value in this investigation. The method is based on the well-known fact that the Ohmic loss in an electrical resistance is equal to the sum of the losses of the harmonic components of a complex wave, except for the case in which any two components approach or attain vectorial identity, in which case the Ohmic loss is increased by a definite amount" (p. 605).

This report studies tritium oxides and tritium in water vapor, a product of P-10.

"An extended analysis was made of the previously reported performance investigation of the original compressor from the XJ-41-V turbojet engine and a similar compressor revised a to obtain a 33-percent increase in the geometric passage area at the vaned-collector entrance. This analysis was based on the concept of the vaned-collector entrance as the throat section of a nozzle. Because of nonuniform air distribution at the vaned-collector entrance, approximately 90 percent of the available flow area was utilized in the original compressor and 94 percent in the revised compressor" (p. 1).