"Work has continued on high temperature methods for processing irradiated uranium fuel. Additional results have been obtained with fused halide treatment, solid scavengers and direct Pu distillation. With fussed fluorides about 95 per cent of the Pu was removed from a uranium sample, while treatment of uranium with HC1 gas removed almost all the Pu and many fission products. treatment of molten uranium with uranium oxide removed a substantial fraction of the fission products without removing Pu. Uranium carbide treatment results were similar to the oxide but not as effective. A small scale distillation of Pu from uranium showed that Raoult's law is obeyed."

Performance of experimental annular turbojet combustors at simulated high altitude supersonic flight conditions.

An investigation was conducted on a 35 deg swept-wing fighter airplane to determine the effects of several blunt-trailing-edge modifications to the wing and tail on the high-speed stability and control characteristics and tracking performance. The results indicated significant improvement in the pitch-up characteristics for the blunt-aileron configuration at Mach numbers around 0.90. As a result of increased effectiveness of the blunt-trailing-edge aileron, the roll-off, customarily experienced with the unmodified airplane in wings-level flight between Mach numbers of about 0.9 and 1.0 was eliminated, The results also indicated that the increased effectiveness of the blunt aileron more than offset the large associated aileron hinge moment, resulting in significant improvement in the rolling performance at Mach numbers between 0.85 and 1.0. It appeared from these results that the tracking performance with the blunt-aileron configuration in the pitch-up and buffeting flight region at high Mach numbers was considerably improved over that of the unmodified airplane; however, the tracking errors of 8 to 15 mils were definitely unsatisfactory. A drag increment of about O.OOl5 due to the blunt ailerons was noted at Mach numbers to about 0.85. The drag increment was 0 at Mach numbers above 0.90.

Report discussing an investigation of the McDonnell XF3H-1 with models to determine the aerodynamic effects of operating internally stowed extensible rocket racks during transonic flight. Information about the flutter, static longitudinal stability, dynamic longitudinal stability, static directional stability, trim, drag, and effect of rocket racks on aerodynamic characteristics of the model is provided.

Report presenting a flight investigation using two rocket-boosted scale models of the McDonnell XF3H-1 airplane to determine the aerodynamic effects of operating internally stowed extensible rocket racks during transonic flight. Operation of the racks generally had only a small effect on the aerodynamic characteristics with the exception of drag.

Report presenting a compressor-blade-vibration survey on a production turbojet engine incorporating an axial-flow compressor with a pressure ratio of approximately 7. The investigation was conducted with three different guide-vane assemblies and four jet-nozzle sizes. The correlation of rotating stall and blade vibration were determined using calculations.

Report presenting an investigation of the performance of two experimental annular turbojet combustors at operating conditions typical of high-altitude supersonic flight. Results regarding combustion efficiency, combustor-outlet temperature profile, combustor pressure losses, and carbon and durability are provided.

Report presenting a low-speed wind-tunnel investigation to determine the static longitudinal control characteristics of flap-type and retractable spoiler-type ailerons on a rigid sweptback wing, a flexible sweptback wing, and a flexible M-wing. Results regarding the rigid-wing and flexible-wing characteristics for each plan form are also provided.

Results are presented of wind-tunnel investigations at Mach numbers of 0.60 to 0.94 and angles of attack of -2 degrees to about 24 degrees to determine the lateral control characteristics of spoilers with various wing chord-wise and spanwise locations and spoiler spans and deflections on thin 60 degree delta wing of NACA 65a003 airfoil section parallel to free stream.

"A free-flight investigation into the effect of fuselage gloves, or load increases in volume, designed to improve the overall longitudinal area distribution of a swept-wing-body combination revealed that a reduction of about 20 percent in maximum pressure drag was obtained. The drag reduction effected by the use of gloves decreased with increasing Mach number, becoming zero at a Mach number of about 1.35, the limit of the experiments" (p. 1).

Report presenting a new blade series designed to operate at near choking inlet Mach numbers and to have near maximum critical Mach numbers by employing high aerodynamic loading of the profiles in the leading-edge region and relatively straight trailing edges. Results regarding the aerodynamic characteristics and prediction of high-speed performance are provided.

Report presenting a free-flight investigation to determine normal-force and hinge-moment characteristics of a half-diamond tip control on a diamond wing with 60 degree sweptback leading edges and 30 sweptforward tailing edges for a range of Mach numbers. Results regarding control hinge moments, control normal force, and total normal force are provided.

Memorandum presenting low-lift drag and longitudinal trim data for two versions of an interceptor-type airplane, the second of which had a slimmer nose and a thinner tail than the first. Data are presented for three models (complete, wingless, and horizontal tailless) of the first version, and from one model (complete configuration) of the second version. Results regarding longitudinal trim, drag, longitudinal stability, and flutter and buffet are provided.

The following report follows the study on economics of nuclear power generation using a light water reactor.

The rapid development of the field of atomic energy during the past few years now permits the exploration of applications to medicine involving new concepts in the treatment of cancer. One such has been the study of neutron capture therapy which is being developed at the Brookhaven National Laboratory.

At present there are three Laboratories actively engaged in analyzing samples for the "SUNSHINE PROGRAM"; Lamont Geological Observatory, University of Chicago and the New York Health and Safety Laboratory. The U.S. Department of Agriculture Laboratories at Beltsville ae preparing samples for the University of Chicago, and are running normal strontium analyses. In order that the results reported from each of the three laboratories may be used to evaluate Sr90 distribution, a cooperative program has been in operation since August of 1953. This preliminary report lists the results on samples received and distributed by HASL. It is hoped that complete results from all laboratories will be available soon.

Memorandum presenting tests of four annular nose inlets covering a wide range of supersonic compression to determine the effect of Reynolds number on their pressure recovery and mass-flow performance. The studies were conducted over a range of angles of attack with various geometric modifications to the basic inlet. Results regarding inlet performance over range of spike-tip positions, inlet performance at angle of attack with and without spike-tip roughness, effect of stream Reynolds numbers on inlet performance, spike surface static-pressure distributions, and inlet schileren photographs are provided.

Report presenting an investigation of the aerodynamic characteristics of a model of the NACA RM-10 in the hypersonic tunnel at a Mach number of 6.9. Longitudinal pressure surveys were made on the body without fins at zero lift and at angles of attack. Results regarding the pressure distributions, forebody pressure forces, body forces, fin-body combination forces, pitching moment and center of pressure, variation of the zero-lift drag components with Reynolds number and Mach number, variation of the lift-curve slope and center of pressure with Mach number, and Schileren observations are provided.

The static lateral- and directional-stability characteristics of a high-speed fighter-type airplane, obtained from wind-tunnel tests of a model, are presented. The model consisted of a thin, unswept wing of aspect ratio 2.3 and taper ratio 0.385, a body, and a horizontal tail mounted in a high position on a vertical tail. Rolling-moment, yawing moment, and cross-wind-force coefficients are presented for a range of sideslip angles of -5 deg. to +5 deg, for Mach numbers of 0.90, 1.45, and 1.90. Data are presented which show the effects on the lateral and directional stability of: (1) component parts of the complete model, (2) modification of the empennage so as to provide different heights of the horizontal tail above the wing plane, (3) angle of attack, and (4) dihedral of the wing.

Shows coastal areas of greater-than-average radioactivity.

An extension of the concepts advanced by Langmuir regarding the nature of the platinum catalyzed oxidation of hydrogen and the application of the resulting theory to the experimental data observed by Ranschoff and Spiewak for an HRE type recombiner indicates that their data are corrected by the dimensionless equation (see report) equally well, with a mean deviation of 3.8 percent. This expression is recommended as a basis for the design of catalytic recombiners. The catalytic combinations is pictured as consisting of two surface chemical mechanisms, one of which is oxygen diffusion controlled, the other hydrogen diffusion regulated, the mechanism "change-over" occurring at that point in the recombiner where the components are arriving at the catalyst surface by diffusion in stoichiometric proportions. The catalyst volume requirements for three two portions of the bed are shown to be (see report). The hydrogen mole fraction at the mechanism "change-over" point is (see report). And the relationship between the two mass transfer coefficients is (see report). Methods for evaluating the necessary transport properties of the ternary system steam-hydrogen-oxygen for carrying out design calculations are summarized, and the new significant parameters are tabulated and plotted to facilitate these calculations. The question of non-uniform velocity profiles …