Abstract: "Thorium tubes were cold drawn from extruded tube stock and also from drilled hot-rolled rod. Total reductions up to approximately 85 per cent were accomplished by conventional tube-drawing methods, without an intermediate anneal. The hard-drawn tubes had high tensile strength, but the ductility, as indicated by flaring and flattening tests, was low."

From introduction: The purpose of this report is to make a comparison of cargo carrying capacity and approximate gross revenue of nuclear powered ships.

Introduction: "In connection with conducting neutron experiments in a pit with earth and concrete walls, it was proposed that the background flux of neutrons might be reduced by lining the walls of the pit with a neutron absorber such as boron. To determine how much liner material would be desirable and what diminution in the neutron background could be expected, the following measurements were undertaken."

Report discussing tests conducted in an attempt to adapt a micromanometer for use in measuring variations of about 0.003 mm Hg in atmospheric pressure. Additionally, a method for making full use of the micromanometer sensitivity and extending its range is described.

Technical report presenting the results of a study of the AEC thorium production facilities at Iowa State College, Ames, Iowa. Operating procedures, descriptions of equipment and a production cost analysis have been included in this study.

Abstract. the Laplacian of a beryllium metal lattice with 3.3 kg of uranium metal per cell and a volume ratio of 17.2 was measured in the removable region of the CP-2 machine. the sandwich effect with different moderators made interpretation of the observations very uncertain. The best result found was Be = 407 x 10(-6) cm(-2).

Report discussing testing to evaluate some of the major aspects of mounting and launching missiles from the leading edge of a wing, including experimentation with six missile models at several Mach numbers. Information from flight tests and launching tests is provided.

Report presenting an investigation to determine the effectiveness of experimental control signals applied to a theoretical inlet throat Mach number control system and normal-shock-position control system for varying the inlet geometry of a twin-duct prototype aircraft. Results regarding inlet instability, control requirements, individual throat Mach number control signals, average throat Mach number control signals, theoretical thraot Mach number control analysis, effect of angle of attack, and theoretical normal-shock-position control are provided.

Memorandum presenting an experimental turbine designed for a high weight flow per unit frontal area, a high specific work output, a relative critical velocity ratio of 0.82 at the rotor hub inlet, and zero rotor blade suction-surface diffusion. Results regarding a comparison of overall performance of subject turbine with that of configurations I and II and comparison of rotor blade momentum thickness of subject turbine with that of configurations I and II are provided.

Memorandum presenting the overall performance results obtained for a 7-inch transonic turbine and a comparison with the results of a 14-inch turbine of geometrically similar design that had been previously investigated. The peak efficiency obtained with the turbine was 0.85, which was 2 points lower than that obtained previously with the 14-inch turbine.

"A device has been developed which measures the velocity of sound in fluids at stagnation and is especially adaptable to turbine and compressor testing for which the constituency of the working fluid may be in doubt. By utilizing the shaft frequency of a rotary compressor, the instrument can also be used to provide a direct measurement of the compressor Mach number (ratio of blade-tip velocity to inlet velocity of sound at stagnation). A Helmholtz resonator is employed in the measurement of the sound velocity" (p. 1).

Memorandum presenting an investigation of the drag and pressure distribution on a body of revolution of fineness ratio 12 as measured by the free-fall method. Analysis of the results has provided knowledge of the mechanism of the abrupt drag rise which occurs near the speed of sound, and demonstrates that the theoretical method described in a previous report satisfactorily predicts the shape of the measured pressure distributions at low supersonic speeds.

Report presenting an investigation of the pressure distribution on the full-span droop-nose flap of a wing with the leading edge swept back 47.5 degrees and symmetrical circular-arc airfoil sections. Flap pressure distributions were obtained for the base configuration and various deflections of the full-span droop-nose flap and other flap deflection combinations. Information regarding the flow and section characteristics, spanwise loading parameters, center-of-pressure variation, and flap normal-force and hinge-moment coefficients is provided.

Report of an investigation to determine the effect of surface roughness on the performance of a 23 degree conical diffusers with 2:1 ratio of exit to inlet area and a constant-area tail pipe. Information about the pressure survey results, including total-pressure-loss coefficient, diffuser effectiveness, and boundary-layer profiles is provided.

Memorandum presenting steady-state and transient characteristics of the J34-WE-32 turbojet engine with electronic power regulator as obtained in the altitude wind tunnel to determine the effects of engine and control limits on the performance. Limits on the fuel valve and exhaust nozzle area influence any schedule of speed and temperature. Results regarding the effect of limits on operating schedule, effect of altitude on safe operating range, effect of minimum fuel flow settings on transient performance, and some potential problems are provided.

Report presenting testing of two rocket-propelled research models to determine the effect of the intersection of thin aerodynamic surfaces and the effect of moderate sweepback of thick aerodynamic surfaces on low-lift buffeting. Results regarding trim changes and drag are also provided. It was discovered that low-lift buffeting may be induced at high subsonic speeds by interference due to the intersection of thin aerodynamic surfaces.

From Summary: "A rudder bulb was installed on the trailing edge of the rudder of the Bell X-1 airplane having the 8-percent-thick wing and 6-percent-thick tail. Several flights were made to investigate the effects of the bulb on the snaking oscillation at Mach numbers between 0.75 and 1.0. It was found that the rudder bulb had no noticeable effect on the snaking oscillation over the Mach number range tested."

Report presenting an investigation at a Mach number of 1.24 to determine the distribution of lift, drag, and pitching moment between the wing and fuselage of a scale semispan model of the Bell X-5 airplane. Lift, drag, pitching moments, and wing bending moments were obtained for various angles of attack for 40 through 60 degrees sweptback duralumin wings in the presence of, but detached from, the fuselage.

"The net heat of combustion of a sample of tetraethyldiborane was found to be 20,400 plus or minus 130 Btu per pound for the reaction of liquid fuel to gaseous carbon dioxide, gaseous water ,and solid boric oxide. The measurements were made in a Parr oxygen bomb calorimeter and the combustion is believed to have been 99 percent complete. A more reasonable value for the net heat of combustion would therefore be 20,600 plus or minus 130 Btu per pound" (p. 1).

Paper using the Bernoulli equation for nonsteady flow to derive formulas for propeller lift and thrust distribution in terms of wake-survey measurements of stagnation pressure rise through the propeller. Lift distributions and overall values of thrust from wake survey were compared with direct measurements of those values.

"A lift-cancellation technique is presented for determining load distributions on thin wings at supersonic speeds. The loading on a wing having a prescribed plan form is expressed as the loading of a known related wing (such as a two-dimensional or triangular wing) minus the loading of an appropriate cancellation wing. The lift-cancellation technique can be used to find the loading on a large variety of wings. Applications to swept wings having curvilinear plan forms and to wings having reentrant side edges are indicated" (p. 65).

Inroduction: "A study of the literature, particularly the work done by R. Strubl, I.W. Kolthoff and S.B. Smith, indicated that a polargraphic method for the estimation of T could be devised which would not sacrifice reasonable accuracy for rapidity. Work was begun with the intention of developing such a method."

Summary: "An analysis is made of the heat transferred by natural convection flow inside a small vertical tube with internal heat generation. The reduction in temperature is found to be small."

This paper presents the results of a series of buckling measurements involving the use of enriched uranium rods (1.007% by weight U²³⁵) in light water. The effect of replacing a water reflector with one of uranyl nitrate solution of two different concentrations, 536 and 188 grams of U per liter of solution was investigated for the 0.925" rods with the 1.74 H₂O/U-volume ratio in the core. Some information was also obtained on the extrapolation length to be used in unreflected cases. The application of theory to these lattices, and others, is given in an appendix under separate title, "Buckling Calculations for One Per Cent Enriched Uranium-Water Rod Lattices."