The use of a reactor charged with silver nitrate coated packing for removal of radio-iodine from the waste gases of Hanford chemical processing plants has been successful in removing approximately 99.5 percent of this activity. Studies by the Radiological Sciences Department indicated the desirability of further reducing the amount of radio-iodine released to the atmosphere. Therefore, this study was undertaken with the objectives of better understanding the inherent limitations to iodine removal by reaction with silver nitrate, and improving the efficiency of removal of iodine.

A knowledge of the preferred orientation of the crystal aggregates in pile structural materials is of basic importance in the attempt to understand their behavior under operating conditions. The effect of a preferential alignment of crystallites in enisotropic materials is to create a directional variation in physical and mechanical properties. In most applications directional effects are undesirable and efforts are usually made during fabrication to avoid the conditions which cause the orientation or, if possible, to alleviate the condition by proper heat treatments after the forming process if the orientation persists. Some of the variables that affect the type and degree of preferred orientation is metals during the forming process include working temperature, per cent reduction, the nature of the applied forces used, the crystal structure, and the inherent deformation mechanisms of the metal.

"Test results indicated that graphite is not suitable for seal face material. A program to evaluate various materials and seal face geometries was initiated. A seal run using nucerite-bearium combination was carried on for six hours."

The ANGIE, one of a series of reactor neutronic programs for an IBM 709 or 7090 data processing system, solves the time-dependent, multi-group, neutron diffusion equation for 1 to 26 energy groups applied to a rectangular mesh superimposed on either an x-y or an r-z plane.

As there is no accurate measurements of the energy distribution of neutrons emerging from large uranium blocks, it becomes of importance to see how much information of this kind can be derived from the slowing down distribution of the neutrons in a water tank.

From introduction: "The concluding remarks of the report on the electron diffraction study of UF6 suggest two alternate explanations for the apparent discrepancy between the structure proposed for this compound as deduced from X-ray diffraction work on single crystals and from the electron diffraction investigation of the vapor. The second explanation is based on the premise that the difference may be due to essentially unlike methods of treating the diffraction data. In this report we shall analyze X-ray powder photographs following a scheme parallel to that used in the analysis of the electron diffraction data, to check whether this particular explanation is tenable."

This report discusses the alternating gradient synchrotron at Brookhaven National Laboratory and provides a preliminary discussion on experiences to date and experiments in progress.

Report issued by the Argonne National Laboratory discussing a progress report on the Argonne-Oak Ridge digital computer. This report is an interim report, whose primary value is that it has forced those engaged in the work to give concrete expression to what they have been doing and thinking about up to this point. This report includes tables, illustrations, and photographs.

Report describing an investigation conducted with a single combustor from a J47 turbojet engine using weathered aviation gasoline and several spark-plug modifications to determine altitude ignition, acceleration, and steady-state operating characteristics. Results regarding ignition, acceleration, altitude operational limits, combustion efficiency, and pressure loss are provided.

From Introduction: "Range in more or less steady level flight depends directly on aerodynamic lift-drag ratio at high supersonic speeds, just as it does at lower speeds. This result follows from the classical Breguet range equation in the case of powered flight, and it may be easily deduced from the equations of motion for unpowered or gliding flight (see refs. 1 and 2)."

Preliminary results at high speeds indicate lower bearing temperatures, less internal bearing wear, and greater reliability of the conventional, cage-type cylindrical roller bearings than of either full-complement or special cageless roller bearings of the types investigated, although the latter bearing types have been operated successfully to DN values of 1.0 X 10 superscript 6.

"The over-all performance of a 16-stage axial-flow compressor was determined with various stator-blade resettings and a reduction in solidity of the rotor blades in the last three stages. It was shown that little control over the sudden change in slope of the surge-limit line at intermediate speeds was obtained with the blade modifications attempted, except that some change in speed at which the change in slope occurred could be effected by stator-blade resettings" (p. 1).

An analysis is made of the factors affecting the weight-flow rate per unit frontal area of centrifugal compressors with axial-flow vaned diffusers preceded by mixed-flow vaneless sections. It is shown that, for specified inlet conditions to the impeller and vaned diffuser, the weight-flow rate is increased at the expense of pressure ratio and vice versa. Charts are presented to help the designer make a satisfactory compromise between weight-flow rate and pressure ratio. Some conclusions of the investigation are : (1) Prewhirl is of negligible value in centrifugal compressors designed for high weight-flow rates.

Report presenting a comparison of three hypervelocity vehicles: a ballistic rocket, a skip rocket, and a rocket glider. Range efficiency, automatic heating, and problems of glide rockets are explored.

Report presenting an investigation to evaluate the external-store drag reductions obtainable by application of Baldwin's moment-of-area rule. Several wing-body combinations were investigated with and without four typical air-to-air missiles. Results regarding the total-drag measurements, wave-drag components, and effectiveness of moment-of-area rule for reducing the drag of the external-store installations are provided.

Memorandum presenting an investigation to define the relationships between the extent of laminar flow and such variables as surface smoothness, wall temperature, pressure gradient, and Mach number. The purpose of this particular paper is to review briefly the results that have been obtained from research.

"The information on the propeller-cowling-nacelle combinations, presented in Technical Reports nos. 592, 593, and 596 and in Technical Note 620, is applied to the practical design of NACA cowlings. The main emphasis is placed on the method of obtaining the dimensions of the cowling; consequently, the physical functioning of each part of the cowling is treated very briefly. A practical method of designing cowlings and some examples are presented" (p. 383).

Memorandum presenting an investigation of the performance of a five-stage transonic research compressor with distorted inlet flow. Both overall performance and individual blade-row performance results over a range of compressor speeds and equivalent weight flows were obtained with three circumferential inlet flow-distortion patterns covering annular extents of 60, 120, and 180 degrees. Results regarding compressor-inlet conditions and overall performance and individual blade-row performance are provided.

Memorandum presenting an investigation of a double-ramp cascade inlet at Mach number 3.05 in order to determine the penalties associated with decreasing the length of inlets by means of cascades. Total-pressure recovery and profile distortion of the cascade inlet were compared with a similar single-passage inlet that captured the same mass flow.

From Summary: "The available information on the spectrum of atmospheric turbulence is first briefly reviewed. On the basis of these results, methods are developed for the conversion of available gust statistics normally given in terms of counts of gusts or acceleration peaks into a form appropriate for use in spectral calculations. The fundamental quantity for this purpose appears to be the probability distribution of the root-mean-square gust velocity. Estimates of this distribution are derived from data for a number of load histories of transport operations; also, estimates of the variation of this distribution with altitude and weather condition are derived from available data and the method of applying these results to the calculation of airplane gust-response histories in operations is also outlined."

A finite-difference method previously presented for computing elastic stresses in rotating disks is extended to include the computation of the disk stresses when plastic flow and creep are considered. A finite-difference method is employed to eliminate numerical integration and to permit nontechnical personnel to make the calculations with a minimum of engineering supervision. Illustrative examples are included to facilitate explanation of the procedure by carrying out the computations on a typical gas-turbine disk through a complete running cycle. The results of the numerical examples presented indicate that plastic flow markedly alters the elastic-stress distribution.

A variational theorem is presented for a body undergoing creep. Solutions to problems of the creep behavior of plates, columns, beams, and shells can be obtained by means of the direct methods of the calculus of variations in conjunction with the stated theorem. The application of the theorem is illustrated for plates and columns by the solution of two sample problems.

The gust and draft velocities from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from August 16, 1947 to August 20, 1947 are presented.

"Tests of a 1/20-scale model of the Fleetwings XBTK-1 airplane have been performed in the Langley 15-foot free-spinning tunnel to determine the trim tendencies of the airplane at attitudes above the stall. The results of the tests indicated that the model would trim longitudinally only in the normal range of angles of attack and that the yaw trim tendencies for such longitudinal trim conditions were normal. Although wide oscillations in yaw were noted for some conditions, they occurred at angles of attack larger than those indicated as possible for longitudinal trim and spin equilibrium" (p. 1).