From Introduction: "The purpose of this paper is to present an analytical method for the design of two-dimensional related selection of a blade for particular rotor conditions may be made quickly and easily and its performance deduced from tests of representative sections in cascade."

"An investigation of a single-annulus turbojet combustor with slot-type air admission was conducted to demonstrate the application of certain design principles to the control of outlet-gas temperature distributions. Comparisons of performance of a one-quarter-annulus combustor (duct-type installation) and a full-annulus combustor (obtained in a full-scale turbojet engine) are presented to indicate the applicability of results obtained from combustion studies conducted in duct-type installations. A reasonable correlation existed between the performance of the one-quarter-annulus and full-annulus combustors except for temperature distribution" (p. 1).

This test project is being carried on for the purpose of testing certain machines which are designed to charge and discharge reactor units with process metal while the unit is in operation. Satisfactory charging of process pieces while the reactor now required for charging operations. These presently required shutdowns are costly in terms of production time, and may cause undesirable thermal stresses in the unit as it changes power level. If charging can be accomplished during operation, reactor shutdowns would only be necessary for maintenance or emergency purposes. During the testing of these metal handling machines, problems have arisen involving the behavior of the process pieces as they are charged. Because these problems directly affect the charging operations, they are being closely investigated also. the machines covered by this report are designated as pressurized machines since they contain the same water pressure as the end of the process tube on ;which they are located. In most of the test work covered by this report, the full scale pressurized charging machine was replaced with a small charging cylinder. The charging operation was simplified by this change.

From Summary: "An investigation was made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.60 to 0.93 to determine the effects on the chordwise pressure distributions of projecting various spoiler-type ailerons on a swept wing. The semispan 35 degree sweptback wing had an NACA 65A006 airfoil section, an aspect ratio of 4, and a taper ratio of 0.6. The results of the investigation are presented as curves of chordwise pressure distributions near the midspan of the spoilers (0.46-wing-semispan station)."

Memorandum presenting testing of semispan wing-fuselage models of the F8F-1 and X-1 airplanes in the 16-foot high-speed wind tunnel utilizing the transonic-bump method. The variations of lift coefficient with angle of attack and Mach number and pitching-moment coefficient with lift coefficient at various Mach numbers are presented for the models. The buffet boundaries were found to be in reasonable agreement with those determined from flight tests of full-scale airplanes.

"An investigation has been conducted in the Langley stability tunnel on a vertical-tail model with a stub fuselage in combination with various horizontal tails to determine the effect of horizontal-tail span and vertical location of the horizontal tail relative to the vertical tail on the aerodynamic characteristics of an unswept tail assembly in sideslip. The results of the investigation indicated that the induced loading carried by the horizontal tail produced a rolling moment about the point of attachment to the vertical tail which was strongly influenced by horizontal-tail span and vertical locations. The greatest effect of horizontal-tail span on the rolling-moment derivative of the complete tail assembly was obtained for horizontal-tail locations near the top of the vertical tail" (p. 351).

Report presenting the results of an investigation to determine the effect of chord discontinuities and chordwise fences on the static longitudinal stability and wake characteristics of an airplane model with a 35-degree sweptback wing. The use of a fence or chord extension was found to cause a slight improvement in the static longitudinal stability of the basic wing alone. The force data and flow characteristics in the form of wake surveys and surface tufts are provided.

Report presenting an investigation to determine the effects of two types of propeller-spinner junctures on the pressure-recovery characteristics of an NACA 1-series D-type cowl with an NACA 1-series spinner, in combination with a four-blade single-rotation propeller.

The lack of control rod capacity in the reactors with nine rods is causing significant production losses. The present control system, which functioned satisfactorily at a 300 MW equilibrium power level, is unable to counteract the larger startup reactivity transient effects at the current high power levels. This lack of strength causes the power level to be restricted during startup. The control system is also not flexible enough to prevent outages for the discharge of temporary poison. (1) A method of obtaining the required supplementary control strength and flexibility has been conceived. (2) and equipment developed for this purpose. The purpose of this test. (3) was to demonstrate the operational feasibility of the special front and rear face equipment which was designed to permit the routine charging and discharging of poison slugs at selected process tubes during periods of reactor operation. This report presents the data, results and conclusions obtained from the trial use of this equipment.

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Report presenting a free-flight investigation to determine some effects of aileron span and deflection on the rolling effectiveness of plain, sealed, 15-percent- and 30-percent-chord flap-type ailerons through a range of Mach numbers. Wings of different degrees of torsional flexibility were tested and the results were extended to estimate rigid-wing rolling-effectiveness of all aileron configurations tested.

This document presents a summary of work and progress at the Hanford Engineer Works for August 1952. The report is divided into sections by department. A plant wide general summary is included at the beginning of the report, after which the departmental summaries begin. The Manufacturing Department reports plant statistics, and summaries for the Metal Preparation, Reactor and Separation sections. The Engineering Department` section summaries work for the Technical, Design, and Project Sections. Costs for the various departments are presented in the Financial Department`s summary. The Medical,Radiological Sciences, Utilities and General Services, Employee and Public Relations, and Community Real Estate and Services departments have sections presenting their monthly statistics, work, progress, and summaries.

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Memorandum presenting a description of the equipment used in the Ames supersonic free-flight wind tunnel to obtain the data necessary to measure the aerodynamic characteristics of free-flying models. The model is fired from a gun into the supersonic air stream of a blowdown-type wind tunnel. The action resulting from aerodynamic forces is computed from a time-distance-attitude record of the model flight through the test section.

Report presenting an investigation to determine the aerodynamic characteristics of an NACA 4-(5)(05)-041 four-blade propeller in combination with NACA 1-series and extended cylindrical spinners for a range of blade angles. Results regarding variation of propeller thrust coefficient, power coefficient, efficiency, tip Mach number, characteristics of the propeller in combination with different spinners, and maximum efficiency are provided.

Memorandum presenting a simplified analysis to determine the effective thermal conductivity of a powder from the fraction of space occupied by the gas and conductivities of the solid and the gas which make up the powder. Tests were conducted to determine the conductivity of magnesium oxide powder in various gases at a range of temperatures. The effects of some of the factors neglected in the simplified analysis, such as bending of the heat-flow lines and the irregularity of the arrangement of the particles, were investigated and discussed.

Report presenting the use of a simplified method of analysis in order to estimate the turbine blade-tip speed required to design satisfactory two-stage turbines. The investigation allows for certain conditions for optimal two-stage turbine design to be determined.

Report discussing the progress of various research projects by members of the Mathematics Panel at Oak Ridge National Laboratory for the quarter ending April 30, 1952.

Certain types of neutron diffusion calculations were considerably simplified when the Serber.Wilson Method was introduced about eight years ago. This method, semi-empirical In nature and named after its co-discoverers, was first formulated for the one-velocity isotropic theory and applied to spherical geometries. Within these limits it has in general proved to be a fairly accurate method. If restricted source-free case it has, in addition, turned out to be quite manageable both analytically and numerically.

Report presenting an investigation of the overall performance characteristics of a complete canard-type missile configuration with wing-mounted nacelle engines in the 8- by 6-foot supersonic wind tunnel at a range of Mach numbers. The investigation covered a range of angles of attack, control-surface-deflection angles, and engine mass-flow ratios. Results regarding the overall force and moment evaluation, effect of engines on configuration performance, and effect of variation of engine mass-flow ratio on configuration and inlet performance are provided.

"An NACA 65(sub 1)-212 airfoil of 8-foot chord was provided with a gas-heated leading edge for investigations of cyclical de-icing. De-icing was accomplished with intermittent heating of airfoil segments that supplied hot gas to chordwise passages in a double-skin construction. Ice removal was facilitated by a spanwise leading-edge parting strip which was continuously heated from the gas-supply duct. Preliminary results demonstrate that satisfactory cyclical ice removal occurs with ratios of cycle time to heat-on period (cycle ratio) from 10 to 26" (p. 1).

Report discussing waste line methods for separation plants at Hanford Works. A discussion of existing and proposed methods, including methods of protection for lines are included.

Report presenting an investigation of the stress-rupture and creep properties of hot-pressed molybdenum disilicide, which explored the stress-rupture properties, use of molybdenum disilicide at various temperatures, long-time strength, and a satisfactory method for creep and stress-rupture testing.

Temperature variations in a slug create problems in stresses, corrosion, and design. As an acid in solving these problems for present and higher power levels, the temperature distribution and anticipated maximum temperatures have been calculated and are presented here. They are based upon theoretical investigations of heat flow in a four inch standard slug. The results of these investigations are presented in this document.