In this paper experiments a r e reported on annihilation and scattering of antiprotons in H{sub 2}O , D{sub 2}O, and O{sub 2}. From the data measured i t i s possible to obtain an antiproton-proton and a n antiproton-deuteron c r o s s section a t 457 Mev (lab). Further analysis gives the p-p and p-n c r o s s sections a s 104 mb for the H-p reaction c r o s s section and 113 mb for the p-n reaction c r o s s section. The respective annihilation cross sections a r e 89 and 74 mb. The Glauber correction necessary in order to pass from the p-d to the p-n c r o s s section by subtraction of the p-p c r o s s section i s unfortunately large and somewhat uncertain. The data a r e compared with the p-p and p-n c r o s s sections and with other results on p - p collisions.

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Due to extended low-temperature operation of the KAPL30 carbon steel thimble in the Materials Testing Reactor, a radiation damage evaluation was undertaken. Radiation damage in carbon steel may not be annealed under lowtemperature operating conditions. The data used in the evaluation are presented, and an extension of thimble life to 16 reactor cycles is recommended, subject to review if further low-temperature operation occurs. (D.E.B.)

Calculations are presented of the amount of mass transfer to be expected in liquid alkali metal-Ni alloy systems for two assumed diffusion mechanisms. In one, the boundary layer is assumed saturated and the transfer rate is limited by the rate of diffusion of solute into the liquid. In the other, the mass transfer rate is assumed to be limited by the diffusion rate of a component of the solid alloy to the solid surface. It is concluded tbat a more general hypothesis is needed. (T.R.H.)

Purex and Redox plants operated satisfactorily. Pu production exceeded commitments. The continuous calciners in UO{sub 3} plant experienced difficulty, but the monthly commitment was exceeded. Capital costs for conversion of B plant to recover Cs and Ce have increased. For future processing of E metal, several 3-ton batches were dissolved in Redox. The continuous Task I prototype is being tested for startup of production facilities. Redox product solutions generally have higher waste losses than these from Purex material. The continuous anion exchange prototype will also be tested. Engineering studies were completed of two facets of Purex Phase II expansion, plant conversion to two cycles, and expansion to a rate of 25.8 tons U/day. A proposal requests authority to expand Purex to capacity factor 3.2 along with the two-cycle conversion. The Pu trifluoride process review indicated that conversion to the PuF3 process is not likely. Separations plant dissolver capacity potential for the next 5 yr was studied. (DLC)

Experiments are described that have been designed to measure separately annihilation and reaction cross sections for antiprotons of approximately 450 MeV on oxygen, copper, silver, and lead. A new and more luminous spectrograph has been built for this experiment. The antiproton cross sections a r e compared with total proton cross sections, and are found to be larger by a factor varying from 1.74 for oxygen to 1.39 for silver. Calculations based on the optical model give a reasonable connection between these cross sections and the 6-p and 6-n cross sections. Finally, the information available on antiproton production cross sections is collected. There are indications that a free nucleon is several times as effective as a bound one for producing antiprotons.

Report presenting an investigation of the problem of predicting the experimental wave drag for configurations which have discontinuities in area distribution and thus infinite theoretical wave drag. The agreement between the experimental and computed drags of the ring-body combinations without fillets was very poor. Results regarding the drag coefficients and estimation of wave drag and pressure coefficients and estimation of total drag are provided.

Report presenting an investigation of the certain wing-body combinations as measured by the lift-drag ratio for two arrangements: a half-cone mounted under a triangular wing and a half Newtonian ogive similarly mounted. The configurations were tested for a range of Mach numbers from 1.5 to 5.0. Results regarding the comparison of a half-cone versus a full cone and calculated maximum lift-drag ratio are provided.

Report presenting a control-motion study program with a Republic F-84F using a cross section of tactical maneuvers performed during squadron operational training. Time-history figures, airspeed and Mach number envelopes, and other aerodynamic characteristics are provided.

Report presenting information on the heat transfer, drag, and stability of a large rocket-propelled 10 degree cone in a flight test. The location of turbulent flow was noted and the measured drag coefficients at several locations on the cone are provided.