The following report provides the results of laboratory corrosion tests held to investigate the behavior of austenitic stainless steel, Type 347, in selected O.R.N.L. #1 Redox streams.

This report studies tritium oxides and tritium in water vapor, a product of P-10.

A first approximation of the gas required to cool control rods for Pile Area G is presented in the following report. Since the results are based on a number of assumptions and approximations, they should be considered only as a first approximation and subject to revision. A gadolinium-stainless steel control rod can probably be readily cooled by gas. A boron-stainless steel control rod would be difficult to cool with gas and would probably require about 1,000 lbs./hr. of helium per rod. Carbon dioxide has a slight advantage over helium as a cooling agent for control rods. This advantage is so small that the problems of gas cooling control rods should not influence the decision whether to use helium or carbon dioxide in the pile.

Though the product of P-10 is T{sub 2}, the chief hazard is the tritium oxides, and tritium in water vapor might exchange with the hdyrogen in the water. If a catalyst is present, essentially all of the tritium would be exchanged. Because we do not know what catalyzers may exist at P-10 or in the lungs of a person breathing tritium, a ready answer cannot be given to the question of the importance of the exchange reactions. The HT + H{sub 2}O {r_reversible} HTO + H{sub 2} is also considered. The same conclusion holds, most of the tritium will be exchanged; however the equilibrium constant is needed. 1 fig.

Early this year recommendations for biological research with tritium were outlined by M. E. Getzendaner in document EW-17059. Since then work on many of the preliminary experiments suggested in that document has been and further thought has been given to design a research program to secure the information needed for evaluation of the tritium hazards. It seems desirable at this time to reformulate the projected research more extensively. This document will indicate only the scope of desirable investigations, without attempting to spell out in detail the experimental procedures to be followed. Proposed investigations are studies of water metabolism; studies of hydrogen metabolism; studies with tritium labelled compounds of biological interest; and studies of the biological effect of tritium radiations. The problems outlined under these headings were chosen on the basis of general scientific interest. In most if not all cases, however, the application to radiation hazard evaluation and control is obvious.

This HAPO report discusses the toxic effects of methyl isobutyl ketone, known commercially as hexone. Explosive limits are discussed, in addition to animal experimentation results.

An altitude-test-chamber investigation of a 28-inch-diameter ram-jet engine at a simulated flight Mach number of approximately 2.0 for altitudes of 40,000 to 50,000 feet was conducted at the NACA Lewis laboratory. Three different flame holders, varying in the number and size of the annular gutters, in conjunction with several fuel-injection systems were investigated. The combustion efficiency for the flame-holder fuel-injection system that provided the best over-all operational fuel-air-ratio range (0.03 to 0.075) was over 0.9 at a fuel-air ratio of about 0.065 for the altitude range investigated.

A heat-transfer investigation was conducted with air flowing through an electrically heated Inconel tube having either a long-approach or a right-angle-edge entrance, an inside diameter of 0.402 inch, and a length of 24 inches over a range of Reynolds numbers up to 375,000 and average inside-tube-wall temperatures up to 2000 degrees R. Good correlation of heat-transfer data was obtained for both entrances, which substantiates work previously reported. A fair correlation of friction data was obtained for both entrances. The entrance configuration had little effect on the average heat-transfer and friction coefficients.

Report presenting the results of an experimental investigation of the downwash and wake characteristics behind two highly swept wings in a supersonic stream. Results regarding the rate of change of downwash with angle of attack at zero lift, variation of downwash angle with angle of attack, and wake are provided.

From Introduction: "This paper, which should be of interest to those concerned with transonic wind tunnels, covers the design and operating characteristics of the nozzle."

Report presenting an investigation to determine the lateral control characteristics of a 20-percent-chord flap-type aileron of various spans on a semispan wing-fuselage model in the transonic speed range. The wing of the model had 45 degrees of sweepback, an aspect ratio of 3.7, a taper ratio of 1.0, and an NACA 65A009 airfoil section parallel to the free stream.

Memorandum presenting a pressure-distribution investigation of a wing of a complete supersonic aircraft configuration as conducted in the 4- by 4-foot supersonic tunnel at Mach number 1.59 based on the mean aerodynamic chord. The experimental life and drag coefficients were less than those predicted by linear theory. Results regarding section pressure characteristics, section characteristics, spanwise characteristics, and overall wing characteristics are provided.

Report presenting the first sample of time-history data of airspeed, altitude, and normal accelerations obtained by the NACA VGH recorder in transport operations. This data defines the distribution of normal accelerations and airspeeds in greater detail than what was obtainable with the V-G recorder. Results regarding effective gust velocities, proportion of time spent in rough air, values of airspeed in descent, and variations in load experience are provided.

Report presenting the pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 measured in the Mach number range of 0.60 to 1.08 by the wing-flow method. Variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60. Results regarding the pressure-recovery characteristics and application of the data to fuselage installations are provided.

"The rolling effectiveness of a thin, tapered, and essentially unswept wing having outboard partial-span plain ailerons has been determined by means of rocket-powered test vehicles. The rolling power decreased abruptly in the Mach number range from 0.85 to 0.95 and more gradually at higher speeds. At the maximum Mach number of the tests (1.95), the rolling effectiveness was only 20 percent of that at a Mach number of 0.85" (p. 1).

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This report constitutes a summary and discussion of radiation damage to graphite and its effects on pile distortion. The data covered in this report consist of that obtained from some pile motion measurements and tube bowing measurements, but particularly of that information obtained from direct sampling of pile graphite.

Report discussing the progress made on research concerning sluge-supernate acidification. This report focuses mainly on "'reverse strike' acidification and the observations of the physical characteristics of the test material," which was a synthetic incubated metal waste.

Report reviewing a study regarding the chemical properties, appearance, texture, homogeneity and slurrying ability of waste metal sludge. The settling rates of sludge-supernatant slurries is also discussed.

Procedures are outlined for the separation of Ac/sup 228/ from Ra/sup 226/ in aged Th(NO/sub 3/)/sub 4/ solutions and for the preparation of Ac/sup 228/ samples. (C.W.H.)

None

The following report describes results from a study of three types of cement (Barytes, Brookhaven, and Portland) exposed in the ORNL Reactor for periods of seven and twenty-eight days.

The design of the present time of light mass spectrograph is similar to that of the isotron devised some time ago for isotope separation. The spectrograph will employ the time of flight principle only for the isotopic analysis of small samples.

The reaction of alanine-1-C14 and phenylalanine-1-C14 with acetic anhydride in the presence of pyridine has been studied and the carboxyl group of the amino acid has been shown to be the exclusive source of carbon dioxide involved.