The experiment outlined in this proposal has the possibility of giving an answer to the important question, 'Does the neutrino exist'? It is unfortunate that at the present time, there is no convincing experimental that neutrinos exist. Two recent articles review the status of various experiments which could give information about neutrinos. In general, these experiments give results in agreement with the predictions of beta decay theory. But actually, if even the most complete of the 'recoil type' experiments could be performed satisfactorily, all that could be concluded would be the following: the energy and momentum relationships in beta decay are consistent with the theory that the known energy deficit is carried away by a single particle. But to emphasize the fact that this would not constitute a proof of the real existence of that particle, the following quotations from the review articles should be noted. Crane says, 'All of the evidence about the neutrino is, as already pointed out, indirect in character since neutrinos have not yet been caught after leaving the nucleus. It can, of course, be argued on very general grounds that, if energy is not conserved between nucleus and electron, momentum should not be expected to …

Contains results of calculations made to determine the neutral oscillatory stability boundaries, period and time to damp of the oscillatory mode, and motions following disturbances. The calculations were made for Mach numbers of 0.75 and 2.3 at an attitude of 35,000 feet and for the landing condition at sea level.

Critical review of the information on zirconium, with estimates of the uncertainty in the values.

Memorandum presenting an investigation of a typical inlet stage of a multistage axial-flow compressor that was designed on the basis of an analysis of basic design variables. The stage, consisting of 19 rotor blades and 20 stator blades with 40 inlet guide vanes, had a hub-to-tip-radius ratio at the rotor inlet of 0.50 and a rotor-blade outside diameter of 14 inches. Results regarding the overall compressor performance, comparison of compressor performance with design, and rotor-row performance are provided.

A report discussing an experiment conducted to determine the effect of radiation on the melting point of Tempilaq, a commercially available, temperature-indicating liquid.

A method is developed whereby the fundamental mechanisms are investigated by which processing, heat treatment, and chemical composition control the properties of alloys at high temperatures. The method used metallographic examination -- both optical and electronic --studies of x-ray diffraction-line widths, intensities, and lattice parameters, and hardness surveys to evaluate fundamental structural conditions. Mechanical properties at high temperatures are then measured and correlated with these measured structural conditions. In accordance with this method, a study was made of the fundamental mechanism by which aging controlled the short-time creep and rupture properties of solution-treated low-carbon n-155 alloy at 1200 degrees F.

An investigation was conducted on an 0.08-scale semispan model of the Chance Vought XF7U-1 airplane in the Langley high-speed 7- by 10-foot tunnel in the Mach number range from 0.40 to 0.97. The results are compared with those obtained with an 0.08-scale sting-mounted complete model tested in the same tunnel and with an 0.026-scale semispan model tested by the wing-flow method. The lift-curve slopes obtained for the 0.08-scale semispan model and the 0.026-scale wing-flow model were in good agreement but both were generally lower than the values obtained for the sting model.

"An investigation was conducted to determine the performance characteristics of the axial-flow supersonic compressor of the XJ55-FF-1 turbojet engine. An analysis of the performance of the rotor was made based on detailed flow measurements behind the rotor. The compressor apparently did not obtain the design normal-shock configuration in this investigation. A large redistribution of mass occurred toward the root of the rotor over the entire speed range; this condition was so acute at design speed that the tip sections were completely inoperative" (p. 1).

None

Report presenting an investigation of pressure distributions and flow characteristics at low speed through a range of yaw and angle of attack through the stall for three small-scale low-aspect-ratio pointed wings with varying degrees of trailing-edge sweep. An effort was made to correlate pressure distributions with the strong conical vortex flow observed. Results regarding chordwise pressure distributions and flow characteristics, section lift characteristics at zero yaw, spanwise-load distributions, centers of pressure at zero yaw, and wing force and moment characteristics are provided.

This report discusses enhanced Hg202 as a source of monochromatic light in relation to the effects of the isotopic impurities.

Three graphs representing the four series of isotopes.

Report presenting an investigation in the two-dimensional low-turbulence tunnel of a symmetrical airfoil section equipped with a 0.30-airfoil-chord sealed internally balanced flap with a 0.70-flap-chord overhang and a 0.33-flap-chord leading tab. Results regarding airfoil lift, surface pressure, flap hinge-moment, and flap-balance-chamber pressure characteristics at various flap deflections.

This document details activities of the Hanford Works during the month of February 1949. (JL)

This report details events of importance reported by the Hanford Operations Office for the week ending March 16, 1949.

Report presenting the effect of flutter characteristics of variation on the aerodynamic shape of concentrated weights rigidly mounted on a simplified wing structure. Two general types of weights with similar mass and moment-of-inertia properties were employed. Results regarding effects of aerodynamic shape of concentrated weights, effects of spanwise variation of light concentrated weights, and effects of moment of inertia of light concentrated weights.

"This paper presents some data on the dynamic lateral stability characteristics of the Douglas D-558-II (BuAero No. 37974) airplane. For the airplane in the clean condition, the lateral oscillations are lightly damped. In the landing condition, the airplane performs a constant-amplitude lateral oscillation" (p. 1).

This report details events of importance reported by the Hanford Operations Office for the week ending February 16, 1949.

Report describing the blood cultures of fifty-four dogs that were exposed mid-lethal whole body x-radiation.

In a manner somewhat analogue to that employed by R. Margulies in his memo (BNL Log No. C-2985) on fast source corrections in sigma piles, corrections to be applied to the data obtained on the laid-up graphite in the BNL reactor have been calculated. The correction was computed for a Ra-Be source using the data of Seren and using a standard graphite density for the BNL pile of 1.69. Values of the correction for different experimental sets of data were computed for each of three different diffusion lengths measured parallel to the channels. A correction for diffusion lengths perpendicular to the channels was also determined.

Report presenting testing in the X-4 airplane to obtain stability and control data. The flight was made with the center of gravity at 19.7 percent of the mean aerodynamic chord and with the rudder-boost system removed. The results showed that the longitudinal stability was positive in the clean condition and in the gear-down flaps-up condition.

This document details activities at the Hanford Works during the month of April 1949.