A digital-to-analog converter is described which is a part of a system that converts punched-tape digital data to analog data in a series of points drawn by an x-y plotter. The converter is designed to plot accurately tapes that contain information other than coded numerical coordinates. Operation of the converter is also described along with format requirements and power supplies. (J.R.D.)

Figures 1 and 2 summarize total decay energies for the four radioactive series. The alpha-decay energy obtained by measuring the energy of the alpha particle leading to the ground state includes the energy of the recoil nucleus. The curve shown in figure 3 defines in broad outline the conditions and regions of alpha instability. A great deal more is to be learned from a more detailed examination of the region where alpha radioactivity is prominent. Of great value to the experimentalist is that he is able to predict alpha energies, and the agreement between predicted and measured values often serves as a criterion for isotopic assignment. A number of systems for correlating alpha decay energies have been employed, and that perhaps most widely used is illustrated in figure 4. Here the isotopes of each element on a mass number vs. energy plot are joined, resulting in a family of curves which over a wide region comprise a series of nearly parallel lines.

Report issued by the Oak Ridge National Laboratory discussing studies conducted on corrosion by fluorides. Equipment, procedures, results, and analysis is presented. This report includes tables, illustrations, and photographs.

Report issued by the Brookhaven National Laboratory discussing methods of nitrogen fixation, and their economic impacts. As stated in the introduction, "studies are described on circulating dust fuels, as well as fixed plated, porous bed, and other types of fuels as the basis for chemo-nuclear reactor designs, and the various fuel systems are compared on a technical and economic basis" (p. 3). This report includes tables, and illustrations.

THOROBRED is an IBM-704 code for the calculation of nuclear and economic characteristics of two-region homogeneous reactors operating on a U-Th fuel cycle in the steady state. The major input variables are reactor dimensions, power level, thorium concentration, chemical and purification systems cycle times, corrosion rates, fraction of Pa loss, and nuclear and economic data. The output includes equilibrium isotope concentrations, neutron balance, and a breakdown of fuel cost. Running times are normally less than one minute per case.

The method is based on caustic precipitation and centrifugation (which removes the Cs and small amounts of Sr, rare earths, Zr, Nb, and Ru). These are removed in the supernatant and run through a cation exchange column. This separates Zr-NB and Ru. The effluent is precipitated and the Zr-Nb is stored in an asphalt pit. The Ru then may be recovered from the precipitate. The precipitate from the original centrifugation is calcined, pressed and transported to a deep well.

Report presenting an analysis to determine the effect of increasing the fin-chord length while holding the span constant on the lift and longitudinal static stability of fin-body combinations. Rectangular and triangular fins with spans of 2 and 3 body diameters in combination with a fineness-ratio-14 ogive-cylinder body were tested.

Report presenting an investigation to determine the effect of a Küchemann type fuselage modification designed to reduce the interference velocities at the wing-fuselage junctures on the longitudinal characteristics of a wing-fuselage-tail combination and several wing-fuselage combinations. The tests were made through an angle-of-attack range at Mach numbers varying from 0.60 to 0.92 at a Reynolds number of 2 million. Results regarding the 64A wing-fuselage-tail combination, four-digit wing-fuselage combinations, and effects of Mach number are provided.

The compressor case of a 13-stage axial-flow compressor was modified to incorporate air-bleed systems over the fifth and tenth rotor stages. Rotating stall-exited rotor-blade vibrations were measured in the first and second stages at 60 and 68 percent of rated speed, respectively. Either the fifth- or the tenth-stage bleeds satisfactorily eliminated the peak vibratory stresses.

Few data exist for the thermal conductivity and viscosity of gases at very high pressure. The possibility of using gases for heat transfer media at pressures up to 100 atmospheres and above raised the problem of estimating variations in the conductivity and viscosity at high pressure. Generalized plots are presented which are based on the work of Enskog, Eucken, and Hirschfelder et al. Some pertinent data from Hirschfelder et al and from Hilsenrath et al are presented.

Report presenting an analysis of horizontal-tail loads on a flexible multi-engined jet-propelled swept-wing medium bomber to determine the tail lift-curve slope due to tail angle of attack, tail-lift curve slope due to elevator deflection, tail pitching-moment coefficient due to elevator deflection, downwash factor, and elevator effectiveness factor. The effect of the stabilizer, effects of elevator flexibility, and effects of wing stability are presented.

The following temperature measurement tabulation consists of two parts. Part I lists all HRT thermocouples, their location, the junction box thru which the leads pass, and their termination, if on an instrument. Part II lists all temperature read out instruments and their location. A total of 577 thermocouples are listed in this tabulation. The roughly 77,000 ft of wire used in connecting them up cost $6,799. Temperatures are read on 24 instruments. Cost of these was approximately $15,688. Accessories such as patch panels, conduit, disconnects, etc., used in installing the thermocouples cost about $8,069. Total cost for material and instruments for temperature measure comes to approximately $30,556.

Performance of supersonic ramp-type side inlet with ram-scoop throat bleed and varying fuselage boundary layer removal at low supersonic speeds.

The horizontal and vertical power distribution for a 5 x 7 fuel element loading of the TSR is presented. (auth)

Plutonium sheet of uniform thickness and good surface can be made by the extrusion of a tube which is then split and flattened. This report describes the equipment and the operating conditions for making sheet 0.005 to 0.055 in. thick with areas up to 24 in. square.

Safety measures of the Livermore Pool Type Reactor in reaction to certain meteorological conditions and following the improbable rupture of the reactor building.

Report presenting a method for analyzing the effects of inertia and aerodynamic cross-coupling on the response of airplanes in rolling maneuvers. The method is based on the concept that variations in the calculated steady-state angle of attack and sideslip with roll rate give a measure of the onset and degree of roll coupling. An evaluation of this concept from several different perspectives is also provided.

For constant-mechanical-speed operation, the two-spool thrust values are as great as or greater than the one-spool thrust values over the entire flight range considered, while the specific fuel consumption for the two engines agrees within 1 percent. The maximum difference in thrust occurs at Mach 2.8 in the stratosphere, where the two-spool thrust advantage is about 9 percent for operation with the after burning.

Report presenting a rotating total-pressure survey rake to obtain wake measurements of a compressor rotor. Results indicated that there was a considerable radial flow of the inboard-blade boundary layer and little radial flow of the inner casing boundary layer. Results regarding the variation in total-pressure-loss distribution with Mach number, variation in total-pressure-loss distribution with angle of attack, contour plots, spanwise variation in total-pressure-loss coefficient, variation of low-speed momentum loss coefficient withe angle of attack, and variation of momentum-loss coefficient with Mach number are provided.

A report regarding a drilling project at Tenderfoot Mesa, Mesa County, Colorado.

Report presenting the longitudinal and lateral stability characteristics of a 40 degree swept-wing fighter model with and without horizontal tails of 0 degrees and 22.5 degrees negative dihedral for a range of Mach numbers, angles of attack, and sideslip.

Report presenting testing on two three-blade supersonic propellers in order to determine the effects of trailing-edge bluntness on the performance of a supersonic propeller. Results regarding propeller thrust, power, effects of Mach number and advance ratio on maximum efficiency, and a comparison to a previous test are provided.

Report presenting the stall characteristics of the J71-A2(X-29) turbojet engine as determined in an altitude test chamber. When the normal high-speed configuration of bleeds closed, inlet guide vanes open was operated in the low-speed range, the stall-limit line intersected the operating line at 4067 and 4630 rpm. Results regarding compressor performance at steady state and stall and fuel flow at steady state and stall are provided.

"The effect of inclination of the airstream on the measured pressures of 54 total-pressure tubes has been determined for angles of attack up to 60 degrees and over a Mach number range from 0.26 to 1.62. The investigation was conducted in five wind tunnels at the Langley Aeronautical Laboratory" (p. 495).