Thesis describing a research conducted to extend observations on nuclear energy levels and how they effect the nucleus itself, and an investigation on the gamma rays associated for the even-even isotopes and to obtain additional data for the oddmass neclei in the hope that more regularities will become apparent for that class of nuclides.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, John Ben Shepperd, regarding a legal question submitted for clarification: Construction of Armories.

Abstract: During the summer of 1955, two test holes were drilled into the Triassic Chinle Formation in the Lukachukai Mountains near Cove, Arizona, to obtain geologic information. Brief airborne and ground reconnaissance was made of Triassic outcrops near Cove. No anomalous radioactivity was found in the test holes, but chemical tests showed concentrations of heavy metals in conglomerate lenses in the Chinle Formation. Channel sandstones in the middle part of the Petrified Forest Member appear to be the most favorable for mineralization. The Shinarump Member, here underlain by a permeable unit, and occurring at depths greater than 500 feet, appears less promising for uranium exploration.

Progress is reported in the fabrication and inspection of metals.

Performance characteristics of underslung vertical wedge inlet with porous suction at Mach numbers of 0.63 and 1.5 to 2.0.

Memorandum presenting certain considerations and techniques pertinent to the application of the supersonic area rule to the design of airplane fuselages. Some of the factors considered are an extension of the rule to account for the interference effects of the wing and tail on the general flow field for asymmetrical configurations, the determination of fuselage area developments which result in approximately the minimum wave drag, and the influence of wing parameters and design Mach number on the effectiveness of fuselage shaping.

Report presenting tests to determine the flight characteristics of an F-86A airplane equipped with an area-suction boundary-layer-control system on the flaps and to investigate the possible operational problems which may arise on a flight installation of boundary-layer control. Results regarding the airplane with slatted leading edge, suction requirements, airplane with suction flap and various leading-edge configurations, factors affecting flap lift increment, and operational characteristics of boundary-layer control are provided.

Report presenting a flight investigation of a rocket-launched solid-fuel ram-jet engine designed to bypass cooling air around the fuel charge. The internally cooled combustor averted combustor burn-out during the flight test. Results regarding the net thrust coefficient, gross thrust coefficient, time history of the air specific impulse, and total fuel load are provided.

Report presenting an investigation on a model of a 40 degree swept-wing fighter airplane to determine modifications which would eliminate the pitch-up that occurred near maximum lift during flight testing. The effects of high-lift and stall control devices, horizontal-tail locations, external stores, and various inlets on the longitudinal characteristics of the model were investigated.

Memorandum presenting an investigation conducted to determine the effect on the low-speed resistance and spray characteristics and static transverse stability of a modification which extended the bow of a scale model of a nose-inlet transonic seaplane configuration. The investigation was made with and without tip floats. The change was found to result in a 50-percent reduction in the hump resistance, increased engine-inlet clearance, reduced low-speed spray and hull-side flow, and acceptable spray and resistance at 25-percent overload.

Report presenting results of evaluation flights of F-86 series aircraft equipped with two types of boundary-layer control, which differed significantly in regards to the type of lift increment produced. The report presents the comments of 16 Air Force, Navy, contractor, and NACA pilots as to the reasons for their choice of minimum, comfortable approach speed on the several configurations tested.

Report presenting testing of the performance of a ventrally mounted inlet having a variable-angle vertical-wedge compression surface determined at several Mach numbers for angles of attack, angles of yaw, and wedge angle. A solid wedge and wedges with two different porosities were tested. Results regarding the inlet flow-field survey, comparison of inlet configurations, performance of the inlet, effect of free-stream Mach number at angle of attack of 2 degrees, effect of angles of attack and yaw, diffuser total-pressure distortion, fuselage boundary-layer-removal scoop, and effective thrust comparison are provided.

Report presenting an investigation in the high-speed tunnel at Mach numbers from 0.80 to 0.92 to determine the effects of fuselage shape on the aerodynamic characteristics of a model with low and high wing arrangements. Results regarding longitudinal stability characteristics and lateral stability characteristics of the different component combinations are provided.

The purpose of this project proposal revision is to request authorization of total project funds for back-up radioiodine removal and additional nitric acid recovery facilities for the Purex Plant. It is proposed to provide new facilities at the Purex Plant for the further removal of radioiodine from the dissolver off gases and for further recovery of nitric acid. The facility design will be based on meeting iodine emission requirements under 1961 goal conditions. It is expected that the facilities will include equipment such as an acid absorber, a caustic scrubber, heat exchangers, process vessels, process piping, jets, jumpers, remote control instrumentation, a continuous iodine monitor, new utility supply and discharge piping, waste disposal facilities, utilities, and other auxiliaries. The new equipment will be housed in a reinforced concrete building and vault which will provide necessary shielding and contamination control. A new vessel will also be installed in the 202-A aqueous-make-up facility. The equipment will be contact maintained. Some work will also be performed for tie-ins and alternations to existing facilities. The new iodine removal facilities are desired as early as practical since the effect of iodine emission on the environs surrounding HAPO is more serious during the winter months.

Neutron spectra were obtained for a series of subcritical fuel assemblies with light water as moderator. It is concluded from the experimental results that the observed spectra are in reasonable agreement with the Wigner-Wilkins thermal neutron spectra calculations. (L.T.W.)

Several potential hazards that have been recognized and anticipated in the design and fabrication of the pressure vessel in the Homogeneous Reactor Test are discussed. These hazards results from the high operating pressure and temperature of the reactor, the exposure of the reactor vessel material to potential embrittlement and other affects of fast-neutron irradiation, and the need for containment of corrosive flowing liquids. The steps taken in recognition of these hazards are also discussed. The applicability of present codes to the reactor vessel fabrication is considered. Additional fields are suggested where recommended practices developed by code writing bodies could assist in development-type reactor design and fabrication.

In order that fairly accurate thermal stress calculations can be made on the ART, it is necessary to have a reasonable picture of the temperature distribution in the reactor. To get the temperature distributions, and to determine cooling requirements in various parts of the reactor, one must know the heat deposition rates due to alpha particles, beta rays, gamma rays, and neutrons in all parts of the reactor. The present report contains only the basic physical data necessary to determine the heat deposition rates due to gamma rays. Neutron fluxes in the core and reflector regions of the ART are to be obtained from two-dimensional multigroup calculations (performed by the Curtiss-Wright Corporation). These fluxes, in conjunction with the neutron absorption cross sections, determine the neutron capture and inelastic scattering rates in the core and in the reflector. The data in this report permit the calculation of the number of gamma rays originating at various energies at every point in the core and reflector.

Report presenting a flight investigation of a rocket-launched solid-fuel ram-jet engine designed to bypass cooling air around the fuel charge. Having an internally cooled combustor averted combustor burn-out during the flight test. Results regarding acceleration, altitude, air specific impulse, and fuel specific impulse are provided.

"Recent results of the effects of Mach number, stream turbulence, leading-edge geometry, leading-edge sweep, surface temperature, surface finish, pressure gradient, and angle of attack on boundary-layer transition are summarized. Factors that delay transition are nose blunting, surface cooling, and favorable pressure gradient. Leading-edge sweep and excessive surface roughness tend to promote early transition. The effects of leading-edge blunting on two-dimensional surfaces and surface cooling can be predicted adequately by existing theories, at least in the moderate Mach number range" (p. 1).

The sizes and weights of the cores of heat exchangers were determined analytically for possible application for reducing turbine cooling-air temperatures of an engine designed for a Mach number of 2.5 and an altitude The sizes and weights of the cores of heat exchangers were determined analytically for possible application for reducing turbine cooling-air temperatures of an engine designed for a Mach number of 2.5 and an altitude of 70,000 feet. A compressor-bleed-air weight flow of 2.7 pounds per second was assumed for the coolant; ram air was considered as the other fluid. Pressure drops and inlet states of both fluids were prescribed, and ranges of compressor-bleed-air temperature reductions and of the ratio of compressor-bleed to ram-air weight flows were considered.

Report presenting aerodynamic-heating data obtained from Mach numbers 1.2 to 4.2 from a free-flight test of a model finless NACA RM-10. Skin temperatures were measured at six stations along the body. Results regarding experimental recovery factors and Stanton number are provided.

Report presenting an investigation to determine the effect of conical camber on the drag due to lift and on the static longitudinal, lateral, and directional stability characteristics of an aspect-ratio-3, 45 degree sweptback wing in combination with a streamline body. The addition of conical camber to the basic wing reduced the drag due to lift at moderate and large lift coefficients and increased the maximum lift-drag ratios.

Report presenting some considerations and techniques pertinent to the application of the supersonic area rule to the design of airplane fuselages. Some of the factors to consider are an extension of the rule to account for the interference effects of the wing and tail on general flow field, the determination of fuselage area developments which result in minimum wave drag, and the influence of wing parameters and Mach number on the effectiveness of fuselage shaping.

The statistical theory of pressure broadening is developed for any interaction law in which the potential energy is inversely proportional to some power of the distance between the molecules, including cases in which the forces change sign. This note is intended to prove two propositions: A. When a spectral line is broadened by single impacts of perturbing molecules and the half-width of the line is delta infinity, the statistical theory of broadening is applicable provided delta infinity . R >> 1. In this criterion T is a time comparable to the interval in which the perturbed traverses a distance equal to the impact parameter. B. Far in the wings of a line the statistical theory is always applicable.