"Temperature surveys were made at the combustion-chamber outlets of a British Rolls-Royce Nene II engine. The highest mean nozzle-vane and mean gas temperatures were found to occur at a radius approximately 75% of the nozzle-vane length from the inner ring of the nozzle-vane assembly. Variations in engine speed, jet-nozzle area, simulated altitude, and simulated flight speed altered the temperature level but did not materially affect the pattern of radial temperature distribution" (p. 1).

This paper presents a critical comparison made between experimental and theoretical results for the aerodynamic characteristics of wings at supersonic flight speeds. As a preliminary, a brief, nonmathematical review is given of the basic assumptions and general findings of supersonic wing theory in two and three dimensions. Published data from two-dimensional pressure-distribution tests are then used to illustrate the effects of fluid viscosity and to assess the accuracy of linear theory as compared with the more exact theories which are available in the two-dimensional case. Finally, an account is presented of an NACA study of the over-all force characteristics of three-dimensional wings at supersonic speed.

Summary: "Six different types of solutions of various concentrations were used to deoxidize uranium chips on a laboratory scale. None of the solutions tested appears to be more desirable than 50% nitric acid for deoxidizing uranium chip on a production scale."

The method for calculating relative heat generation as a function of radius of an equivalent ``G`` type cylindrical pile for specified inhours of ideal flattening is given in INDC-3833. The report has been extended to include flattening curves for the range of zero to 800 inhours. Equations have been integrated to determine average relative power per tube for a fixed amount of flattening. Average relative power per tube, number of effective tubes, kw per effective tube, and maximum temperature rise per tube for 34.6 gpm water flow rate per effective tube are tabulated in Table 1 for several values of flattening of an 800 MW--2,220 tube pile.

The following report contains two parts on the analysis of astatine, neptunium and plutonium. Part A discusses a bent crystal focusing X-ray spectrometer that has been designed and built for the observation of the X-and gamma-rays emitted in association with radioactive decay. The instrument uses proportional counter detection and is described, as well as associated electronic circuits. The plutonium L X-rays from Cm-242 and the neptunium L X-rays from Am-241 have been measures. Values of the energies and abundances are reported. Then in Part B, it discusses some isotopes of astatine hitherto unreported that have been observed in bombardments of bismuth on the University of California 184" cyclotron.

The following report is meant to record the premises upon which the site plan for the NTR is already established.

Equations are derived for the rates of heating of objects in induction furnaces and for the maximum temperatures attainable. The equations are primarily useful in designing conducting crucibles, shells, and cylinders so as to increase the power input and decrease heat losses. A very brief treatment is given of the factors which influence the current in the induction coil. The performances of various induction furnaces are compared.

Fission-production of krypton-85 in natural uranium piles is substantial and in direct proportion to plutonium production. The known chemical and nuclear properties of krypton are such as to permit its determination in air samples taken at considerable distance from its force and to allow correlation of such measurements with plutonium production.