The leak detector system consists of one gas pressurized reservoir containing heavy water, a tubing manifold connecting the pressurizer to six separate lines each connected to one of the flanges, tubing lines leading from the second hole on each of three flange pairs (dome and heat exchanger flanges) back into the instrument room, plus required valves and fittings. A schematic diagram of the system in included.

"The influence of compressive creep on the self-diffusivity of α-iron has been measured in the temperature range of 742-885°C. the diffusivity is enchanced in proportion to the strain rate, but this dependence decreases with increasing temperature. The magnitude of the strain is relatively unimportant in this connection. Strain rates from 0 to -2 x 10¯³ sec¯¹ were investigated with a corresponding increase in diffusivity up to 3 x 10³ times. The results are analyzed in terms of vacancy diffusion and the excess vacancies introduced during deformation. It is concluded that grain boundaries are the main vacancy sinks in polycrystalline iron and that the vacancy lifetime is therefore dependent on the grain size."

"Results of a reconnaissance geochemical survey of the Watertown Quadrangle are reported. Field and laboratory data are presented for 711 groundwater and 603 stream sediment samples. Statistical and areal distributions of uranium and possible uranium-related variables are displayed. a generalized geologic map of the survey is provided and pertinent geologic factors which may be of significance in evaluating the potential for uranium mineralization are briefly discussed."

Abstract: The reactor analysis of the critical experiment and the APPR-1 resulted in a loading of the APPR-1 of 31.096 gm of B-10 with 22.5 kg U-335. This loading will result in adequate reactivity for a core life of 13 MWYR based on uniform burnup of U-335 and B-10. Calculations indicate that five of the seven control rods provided are more than adequate to shut the reactor down at any time. The temperature coefficient of reactivity should be at least -2 x 10-4 [delta] K/0F.

Abstract: The reactor analysis of the critical experiment and the APPR-1 resulted in a loading of the APPR-1 of 31.096 gm of B-10 with 22.5 kg U-335. This loading will result in adequate reactivity for a core life of 13 MWYR based on uniform burnup of U-335 and B-10. Calculations indicate that five of the seven control rods provided are more than adequate to shut the reactor down at any time. The temperature coefficient of reactivity should be at least -2 x 10-4 [delta] K/0F.

"The magnetic properties of color centers were studied to obtain information regarding electron traps in insulators. Experiments designed to determine the equation governing the recovery of resonance after saturation were carried out. Relatively large samples were prepared by the method of additive coloration. KCl and RbCl crystals were used. Resonance saturation as a function of concentration was investigated and no significant dependence found. Measurements of the unsaturated susceptibility were made at liquid nitrogen and liquid helium temperatures. The bleaching of the F-center to form the B-band produced a different resonance. The equipment for observing the saturation and recovery of a portion of the resonance at 4 deg K is described. A theoretical examination was made of the interaction between the vibration of the ions around a negative-ion vacancy in an alkali halide and an electron trapped at that site. (M.C.G.)."

Abstract: "An absolute measurement of the 14.1-Mev (n, 2n) cross sections of Li-6 and Li-7 has been made using the large scintillator technique, resulting in cross sections in barns of 0.070 +/- 0.006 and 0.056 +/- 0.005 for Li-6 and Li-7, respectively."

Report discussing study on recovery of nitric acid in the uranium recovery process. The behavior of chloride ions and tributyl phophate is noted, and the quality of recycled nitric acid was tested. Stainless steel in the nitric acid recovery system was evaluated for corrosion.

Abstract: "Variations in receiver slot design produce changes in quantity and quality of product and recycle, not only instantaneously, but also as a function of time in approaching equilibrium. The case of fixed feed concentration and fixed inventory of Uranium is described here for standard and Dip-Lip wider R slot receivers. The effects of the two types of receivers on recycle and product X and W concentrations, X production rate, plant X utilization efficiency, integrated X production and effective mass output are shown graphically."

Data collected as part of a hydrogeochemical and stream sediment reconnaissance for the Lincoln NTMS quadrangle in Kansas and Nebraska including laboratory data on well water and stream sediments as well as field data.

Data collected as part of the Douglas Quadrangle in Arizona including laboratory and field data on waters and sediments.

From abstract: Results of a reconnaissance geochemical survey of the Lincoln Quadrangle are reported. Field and laboratory data are presented for 577 groundwater and 754 stream sediment samples. Statistical and areal distributions of uranium and possible uranium-related variables are displayed. A generalized geologic map of the survey area is provided, and pertinent geologic factors which may be of significance in evaluating the potential for uranium mineralization are briefly discussed.

Abstract: Field and laboratory data are presented for 161 water samples and 235 sediment samples from the Douglas Quadrangle, Arizona; New Mexico. Uranium values have been reported by Los Alamos National Laboratory in Report GJBX-69(78). The samples were collected by Los Alamos National Laboratory; laboratory analysis and data reporting were performed by Uranium Resource Evaluation Project at Oak Ridge, Tennessee.

Abstract: "Two transistor plug-in decade counters are described, one of which operates over the SCS-7 temperature range. A transistor digital scanner with storage and parallel readout is described. It utilizes one of the plug-in decades. A simple design procedure for flip-flops is presented."

Report presenting data obtained three single annular-type combustors with different combustor inlet-air pressure profiles over a range of engine speeds. Results regarding effect of changing combustor inlet-air pressure profile and hole geometry on combustor performance, performance of the prototype J40-WE-8 turbojet engine combustor, correlation of combustion efficiency with engine fuel-air ratio and combustion parameter, and comparison of several combustors from different turbojet engines are provided.

Report discussing the division of load among the wing, fuselage, and tail for several aircraft configurations at subsonic and supersonic speeds. The load that each component carries at various Mach numbers and angles of attack is described.

Report presenting an investigation in the high-speed tunnel for a range of Mach numbers to determine the lateral control characteristics of a wing-fuselage combination with the wing quarter-chord line swept back 32.6 degrees, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 section. Results regarding yawing-moment characteristics, spoiler-slot-deflector testing, and rolling-moment coefficient are provided.

Report presenting an investigation to determine the effects of plan-form taper on the aerodynamic characteristics of a series of symmetrical, unswept wings with thicknesses of 8-percent chord. The wings were tested with four different bodies of revolution over a range of Mach numbers. Results regarding the lift, drag, pitching-moment, lift-curve slope, lift-drag ratio, and pitching-moment curve are provided.

Memorandum presenting an investigation of the effects of higher degrees of forming in biaxial stretch-forming of polymethyl methacrylate to about 50-percent strain. Sheets of commercial cast polymethyl methacrylate were hot-stretched approximately 100 and 150 percent, respectively, and tests were conducted on this material and on unstretched cotton material. Results regarding the standard tensile tests, stress-solvent crazing, surface abrasion tests, and x-ray diffraction patterns are provided.

Report presenting an investigation at Mach number 1.61 of the effects of chordwise fences and attached tabs on the hinge-moment characteristics of a half-delta tip control mounted on a 60 degree delta wing. Testing occurred over a range of angles of attack and control deflection. Results indicated that, in general, the effect of fences was to improve the linearity of hinge-moment curves and increase the negative values of slope parameters of hinge moment against control deflection and angle of attack.

From Introduction: "As a part of the comprehensive investigation of the XJ34-WE-32 engine conducted in the NACA Lewis altitude wind tunnel, the over-all-performance was determined over a range of altitudes and flight Mach numbers. Other phases of the investigation are reported in reference 1. The results are given in tables and also in graphical form to show the trends of engine performance associated with changes of altitude, flight Mach number, and exhaust-nozzle area."

From Introduction: "The present report gives results at a Mach number of 4.04 of the part of the program concerned with flap controls at Mach numbers from 1.62 to 6.9."

Memorandum presenting an investigation of the J71-A-11 (600-B36) turbojet engine conducted in an altitude wind tunnel, and more specifically the component and overall engine performance up to the altitude limit imposed by the use of MIL-F-5624A, grade JP-4, fuel. The data were then extended to higher altitudes by the use of gaseous-hydrogen fuel. Results regarding altitude operating limits, component performance, overall engine performance, contribution of individual component losses to overall engine performance losses, exhaust-nozzle-area requirements, and altitude performance at rated engine conditions are provided.

A connected account is given of the Possio theory of non-stationary flow for small disturbances in a two-dimensional supersonic flow and of its application to the determination of the aerodynamic forces on an oscillating airfoil. Further application is made to the problem of wing flutter in the degrees of freedom - torsion, bending, and aileron rotations. Numerical tables for flutter calculations are provided for various values of the Mach number greater than unity. Results for bending-torsion wing flutter are shown in figures and are discussed. The static instabilities of divergence and aileron reversal are examined as is a one-degree-of-freedom case of torsional oscillatory instability.