The HRT leak detector system consists of four headers each of which are connected on one side to a common supply of pressurized water and on the other side by individual tubing to the ring grooves of approximately twenty flanges. There are two methods of detecting the loss of water that are particularly applicable to the HRT: (1) By the loss of pressure in a constant volume system; (2) By the measurement of flow from a constant pressure system. It was determined to investigate the second method which requires a flowmeter capable of measuring flows of .5 cc or less of water per hour. The experiment flowmeter constructed performed almost exactly as the design calculations predicted.

Report issued by the APDA regarting studies conducted on the state of uranium at different temperature and pressure. Calculations are presented for the differing pressures of uranium; it includes tables.

Purpose: A reconnaissance was conducted during parts of August and September, 1956, of an area about two miles square in the southern Carrizo Mountains where the Permian Cutler formation, including its DeChelly member, and the Triassic Shinarump member of the Chinle formation, are exposed. The purpose was to appraise the uranium potential of the area and to determine the cause of bleaching in the DeChelly. Extensive uranium mineralization in the Salt Wash member of the Morrison formation around the Carrizo Mountaind suggested that the Shinarump, a good producer in other areas on the Colorado Plateau, might be mineralized here as well. Bleaching, as shown in the DeChelly; has proven such a useful guide to uranium at other localities as to merit investigation here.

Memorandum presenting several top-inlet configurations tested on a body of revolution in the 8- by 6-foot supersonic wind tunnel at a range of angles of attack and free-stream Mach numbers. The effect on performance of the following variables were studied: throat bleed, ramp perforations, inlet approach surface, side fairings, fuselage fences, canopies, and a simulated 60 degree delta wing.

Memorandum presenting an investigation to determine the influence of the boundaries of a high-speed free water jet on the planing lift of a flat plate operating on the surface of the jet. No appreciable influence of speed on the planing lift coefficient for speeds from 50 to 200 feet per second was observed. Results also indicated that the parameters determining the jet size required for a given test condition have not been defined by these brief tests.

Report presenting a comparison of the experimental wave drags of bodies and wing-body combinations over a wide range of Mach numbers with the computed drags utilizing a 24-term Fourier series application of the supersonic area rule and results of equivalent-body tests. The equivalent-body technique was found to provide a good method for predicting the wave drag of certain wing-body combinations at and below a Mach number of 1, but becomes misleading at Mach numbers greater than 1.

Report presenting an extensive metallographic examination of a group of buckets overtemperatured in service. Most of the buckets showed an overaged microstructure. Results regarding the metallographic survey and stress-rupture tests are provided.

Memorandum presenting a turbojet engine with a two-stage turbine operated with pentaborane fuel continuously for 11.5 minutes at a simulated altitude of 55,000 feet at a flight Mach number of 0.8. The engine incorporated an NACA combustor designed specifically for use with pentaborane fuel. Results regarding oxide formation and deposition, engine operating point, effect of oxide deposits on component performance, effect of oxide deposition on overall performance, and some operational comments are provided.

From Summary: "The primary objectives of the investigation reported herein were to determine the effect of this new combuster design on boric oxide deposition on engine parts and to determine the effect of boric oxide on the performance of multistage turbine. Pentaborance fuel (approx. 130 lb) was used in the engine performance evaluation reported herein. The data presented herein show the engine component and over-all performance deterioration with operation on pentaborane fuel".

Report presenting an investigation of the ejection release characteristics of the MB-1 rocket from the missile bay of a model of the Convair F-106A airplane with its fin tips retracted at a simulated altitude of 18,670 feet. Successful ejections of the rocket were made at supersonic speeds by applying a combination of ejection velocity and nose-down pitching moment at release.

Report presenting an investigation of the ejection release characteristics of the MB-1 rocket from the missile bay of a Convair F-106A airplane. Results regarding pitching moment, ejections, release conditions, and missile trajectory are provided.

Memorandum presenting an investigation in the 27- by 27-inch preflight jet of the ejection release characteristics of the MB-1 rocket from the missile bay of a 0.04956-scaled model of the Convair F-106A. The MB-1 rocket was ejected with its fin tips retracted, for a simulated altitude of 18,670 feet at a Mach number of 1.59.

Report presenting the performance of two translating-double-cone inlets with contrasting rates of turning on the spike shoulder and corresponding cowl projected frontal areas of 40 and 20 percent of maximum compared over a range of Mach numbers. Results regarding internal-flow performance, external-flow performance, inlet airflow patterns, and propulsive-thrust comparison are provided.

Report presenting an investigation to study the origin and development of leading-edge cracking in turbine buckets made of six materials: S-816, M-252, Inconel 550, Inconel 700, Hastelloy R-235, and Jetalloy 1570. Some of the buckets were also given certain stress-relief treatments. Results regarding the development of leading-edge cracks, development of bucket fractures, comparison of performance for the material tested, macro- and microexamination of unfractured and fractured buckets,

Stress corrosion was found in 8 components of the HRT mockup; only of four of these actually shut down the loop. All of the failures have occurred in the high-pressure system of the loop.

Report presenting a procedure for integrating equations involving pressure, temperature, and density in order to analyze an expansion process that occurs when boric oxide from fuels condenses during expansion. An example is provided to illustrate the manner in which the equations can be used to analyze a one-dimensional expansion with phase equilibrium.

The compositions of the compounds and fused salt mixtures referred to in the ANP project by numbers are given.

The results of a machine calculation of a modified Fanning-friction-factor Hedstrom plot for Hedstrom numbers from 0 to 10(10) are presented in graphical and tabular form.

"Thermal-gradient mass transfer" was investigated in the molten sodium hydroxide-nickel system. Possible mechanisms (physical, electrochemical, and chemical) are discussed in terms of experimental and theoretical evidence. Experimental details are included in appendixes.

"A summary is presented of a preliminary study of the application of pole- face windings to the Cambridge Electron Accelerator. Estimates are made of the currents required, the forces on the wibdings and the voltages induced by the magnetic flux. The possibility of automatic control of the pole-face currents in explored, and feasible control systems are suggested."

The following report provides the design and workings of a heavy-ion accelerator designed to accelerate particles of atomic weight 12 through 20.

Report discussing a study to obtain a quantitative measurement of the movement and distribution of hydrogen among components such as magnesium metal chips, uranium tetrafluoride, and magnesium fluoride slag, similar to what would occur during a reaction in a thermite bomb.

"A transonic wind-tunnel investigation was made in the Langley 8-foot transonic pressure tunnel at the request of the Bureau of Aeronautics, Department of the Navy, of the static longitudinal stability and control characteristics and drag of a 0.05-scale model of the Chance Vought XF8U-3 airplane at Mach numbers from 0.80 to 1.20 with an average Reynolds number of 2.6 x 10(exp 6). The investigation included effects of the addition of the ventral fins, extension and removal of the missiles, deflection of the speed brake, addition of a fuselage fairing near the wing leading edge, and longitudinal control effectiveness. The model was statically stable throughout most of the range of positive lift coefficients, but some loss in horizontal-tail effectiveness may be expected near zero lift and a Mach number of 1.0" (p. 1).

"This document includes papers covering technical problems involved in the design, construction and operation of the APPR-1" (p. 4).