Memorandum presenting a study to determine locations of pressure sensors for controlling the spike position of a blunt-lip, axisymmetric inlet with internal contraction. The inlet performance was determined at Mach numbers of 0.63 and 1.5 to 2.0 for airflow schedules corresponding to those of a given turbojet engine over a wide range of ambient temperatures. The use of the ratio of a throat static pressure to either a local total or the spike-tip total pressure provided a signal that could set nearly maximum pressure recoveries at Mach numbers of 1.7 to 2.0 and within 6 percent of maximum recovery at Mach 1.5.

Static overpressure and dynamic pressure versus time over surfaces processing different physical properties were measured on two tower shots, 6 and 12. On Shot 12, three surfaces were provided: the natural desert, a water surface consisting of a flooded area, and an asphalt surface. On Shot 6, desert and asphalt areas only were available. There were 123 channels of instrumentation installed for Shot 12, and 24 for Shot 6. From the data, a system of wave-form classification was devised for overpressure and dynamic-pressure- versus-time measurements. Incorporation of this system into data analysios indicates that it is possible for an ideal peak pressure to be identified with a nonideal wave form. Introducing both variables, wave form and peak pressure, into analyses reduces ambiguioties associoated with comparing results of different nuclear tests. The data show the effect of the nature of the surface upon airblast phenomena from a nuclear explosion. The effects of surface conditions upon shock phenomena are made more understandable by a review of temperature computatioons, using shock wave parameters in addition to an analysis based upon the arrioval time of the thermal pulse. A phenomenological discussion of precursor formation is presented, and comparisons are made using data from all …

The following report analyzes carry transformation circuits and their value when approaching the general problem of carry transmission in computer addition.

From Summary: "The effect of small downstream pressure distributions on the position of a normal shock in a duct with area variation is analyzed. For the analysis, the gas flow is treated as quasi-one-dimensional, and boundary layer is neglected. The analysis shows that there is a first-order lag relation between shock position and small downstream disturbances in pressure which occur at frequencies below a given limit."

Report presenting a method by which the residual stress distribution in a disk can be determined with the aid of the obliquely mounted strain gage when the directions of the principal stresses are radial and tangential. The strain gages are mounted in such a way as to make them sensitive only to the tangential stresses in the disk. Results regarding cutting procedure, accuracy of the method, and an independent check of the method are required.

Introduction: Atomic Energy Facts is designed to serve as an introduction to nuclear operations in the United States and as a handbook of related information for the use of industrial firms and other active or interested in atomic energy.

Report presenting flat 2024-T3 aluminum panels measuring 11 inches by 13 inches were tested in the near noise fields of a 4-inch air jet and turbojet engine. The stresses which were developed in the panels are compared with those calculated by generalized harmonic analysis. Results regarding noise inputs, panel characteristics, procedure for calculating stress, and comparison of calculated and measured stresses are provided.

Report regarding the chemical processing instrumentation designs and problems at the Idaho Chemical Processing Plant.

Report presenting a compilation of most of the zero-lift drag obtained from free-flight measurements on fin-stabilized bodies of revolution. Results regarding friction drag, base pressure and base drag, pressures on a forward facing step, and fin pressure drag are provided.

Report presenting an investigation to determine whether the low-lift drag of a rocket-model airplane-like configuration could be reduced at transonic and low supersonic Mach numbers by reducing wing thickness while external braces were used to provide the necessary bending strength. The investigation was conducted with two rocket models of aspect ratio 3.04, and unswept braced tapered wings mounted on fuselages with the same fineness ratios and cross-sectional area distributions. Data was compared to a previous study involving a model with a thicker cantilever wing.

Report presenting an investigation to determine the effects of compressibility on the hovering performance and the blade pitching moments of a helicopter rotor with a tip airfoil, a root airfoil, and twist. Results regarding hovering performance, rotor-blade pitching moments, rotor profile-drag torque, and a comparison with two-dimensional drag-divergence data are provided.

This report addresses the constant-pressure leak rate gage.

The results of the corrosion study are illustrated in a plot of the weight loss of the aluminum--nickel samples with respect to the time at test temperatures of 470 to 485 deg F. The corrosion rate determined by this test indicates that the weight loss per unit time is the same for both the in-pile irradiated specimens and the out-of-pile control specimens which did not have any neutron exposure, except that the out-of-pile specimens had a higher initial rate of corrosion which elevated the curve above that of the in-pile specimens. (auth)

This document is a HAPO report dated September 20, 1957. At the time of this report, there had been many different methods suggested for improving the Purex organic recovery system. Some of these suggestions been tried in the plant and others had not. Information concerning this system and, particularly, methods for improving it were wide spread. At the time of this report was no immediate source of information available on the proposed and investigated methods for improving the Purex solvent recovery system.

Monthly newsletter of the High Plains Underground Water Conservation District No. 1, discussing the field of underground water. Topics include profiles of water conservation research, annual pre-plant soil moisture survey data, annual Winter Water Level measurement data, and information about the latest water conservation tips.

This report summarizes the design and construction of the Bevatron (6-Bev proton synchrotron) with emphasis on the engineering problems. It includes specifications, outline drawings, and a bibliography of other reports concerning the subject. Operating results and changes made after the initial start-up in February 1954 are mentioned only briefly.

The gamma -radiation field from a battery of 10 MTR spent fuel elements was calculated and a special shipping cask designed to contain the 10 elements. An internal watercooled tank in the cask holds the 10 elements in the vertical position. Two external air-cooled, finned-tube heat exchangers control the water temperature. The sides of the cask open to convert the cask to a radiation source without changing the position of the elements. A unique feature of the design is a device for closing the sides of the cask by gravity in the event of accident or power failure. This provides a ''fail-safe'' safety feature. (auth)

Report presenting an investigation of an axial-flow turbojet engine in the altitude wind tunnel, including limitations on transient operation of the engine in relation to two altitudes and exhaust-nozzle-areas. Results regarding hysteresis, frequency of surge and stall, altitude effect, exhaust-nozzle-area effect, and a comparison of steady-state and transient surge lines are provided.

Report presenting zero-lift drag data for a flare-stabilized bluff body of fineness ratio 4.4 alone and with conical and flat windshields at a range of Mach and Reynolds numbers. The model with the flat windshield was found to have the lowest drag at Mach numbers up to 1.05, but there was little difference in drag among the models above 1.05.

Note presenting an analysis made to determine the effect of configuration parameters and valve area-time operating relations on the speed of response of the liquid flow and the suppressed suction head of the pump in a rocket motor. The configuration consisted of tank, pump, combustion chamber, valves, and lines, including a bypass line with a valve around the pump. Results regarding the effect of valve resistance-time history on pump suppression head and flow response time and effect of configuration parameters are provided.

Report presenting an investigation to determine the effect of frequency of sideslipping motion on the lateral stability derivatives of a 60-degree delta-wing airplane configuration. Results regarding the steady-state tests, oscillation-in-sidestep tests, comparison of oscillation data for delta wings with a round edge versus a sharp edge, and effect of sideslip oscillatory derivatives are provided.

Report presenting the results of an investigation to determine the effects of full-span trailing-edge flaps on the static longitudinal characteristics of a triangular wing-body combination. Data was obtained for the basic configuration and for a wing with the control surfaces deflected for longitudinal control.

Memorandum presenting an investigation to study the effect of ground proximity on the aerodynamic characteristics of two jet vertical-take-off-and-landing airplane models in which the fuselage remains in a horizontal attitude for the take-off and landing. Results regarding the flow surveys and force tests are provided.

Report issued by the Bureau of Mines over studies conducted on bleeder application in bituminous coal mines. The methods and results of the studies are presented. This report includes illustrations.