Memorandum presenting the flammability limits of 18 high-boiling hydrocarbons at reduced pressures in a closed flame tube with hot-wire ignition. Characteristic two-lobe flammability-limit curves were demonstrated by all of the hydrocarbons. The rich limit, lean limit, and flammability range were found to decrease as the number of carbon atoms increased.

Abstract: "The mechanical properties of a large number of zirconium alloys have been investigated. These alloys include zirconium-tin and zirconium-tin-uranium. Tensile tests have been run on these alloys at room temperature, 500 F, and 600 F. Hot-hardness data have been obtained from room temperature to 1600 F, with particular emphasis on the hot-rolling range. Creep tests and fatigue tests have been run on a number of zirconium-tin alloys at 500 F."

Abstract: "The mechanical properties of a large number of zirconium alloys have been investigated. These alloys include zirconium-tin and zirconium-tin-uranium. Tensile tests have been run on these alloys at room temperature, 500 F, and 600 F. Hot-hardness data have been obtained from room temperature to 1600 F, with particular emphasis on the hot-rolling range. Creep tests and fatigue tests have been run on a number of zirconium-tin alloys at 500 F."

Report of an investigation of the overall performance characteristics of a complete missile configuration in the 8- by 6-foot supersonic wind tunnel at several Mach numbers, angles of attack, canard-control-surface deflections, and a designated Reynolds number based on wing mean aerodynamic chord. The investigation showed that at a Mach number of 2.0, the addition of engines to a no-engine configuration increased drag and moved the aerodynamic center rearward but produced little additional lift. Results regarding force and moment evaluation and engine-internal-flow evaluation are provided.

Report presenting the performance characteristics of one convergent and three convergent-divergent nozzles obtained over a range of nozzle pressure ratios. Results regarding one-dimensional flow theory and the performance characteristics themselves are provided.

Report presenting an investigation for stationary turbine blades with 10 tubes and 13 fins forming the internal heat-transfer surfaces in order to accurately predict local turbine blade temperatures. Results regarding the comparison of calculated and measured midchord blade temperatures, comparison of calculated and measured temperatures near blade trailing edge, comparison of calculated and measured temperatures near the blade leading edge, the influence of errors in calculated temperatures on design considerations, and an application of the analysis to other blade configurations are provided.

"The applicability of some results from the theory of generalized harmonic analysis (or power-spectral analysis) to the analysis of gust loads on airplanes in continuous rough air is examined. The general relations for linear systems between power spectrums of a random input disturbance and an output response are used to relate the spectrum of airplane load in rough air to the spectrum of atmospheric gust velocity. The power spectrum of loads is shown to provide a measure of the load intensity in terms of the standard deviation (root mean square) of the load distribution for an airplane in flight through continuous rough air" (p. 371).

Abstract: An airborne radiometric survey of parts of the east flank of the Big Horn Mountains was begun on June 23, and completed on August 27, 1952. An area of approximately 250 square miles was covered, and only two anomalies were found in the entire area. Flight lines were arranged in accordance with the geology of the area, particular attention being given to formations the stratigraphic equivalents of which are known to be uranium bearing in other areas. Two additional zones of radioactivity were found by ground investigation, but assays from both the ground and the airborne discoveries showed no economic uranium deposits.

An arbitrary weak spatial distribution of vorticity can be represented in terms of plane sinusoidal shear waves of all orientations and wave lengths (Fourier integral). The analysis treats the passage of a single representative weak shear wave through a plane shock and shows refraction and modification of the shear wave with simultaneous generation of an acoustically intense sound wave. Applications to turbulence and to noise in supersonic wind tunnels are indicated.

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This memorandum discusses the engineered safety system which combines the Ball 3-X System with the VSR System. The operation of the system is detailed and settings are recommended for 105-C trips.

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.

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 a method for predicting wing-tail interference as applied to the calculation of tail efficiency parameters, lift characteristics, and center-of-pressure locations for a series of generalized missile configurations. The calculations are also compared to experimental data. The rolled-up vortex concept appears to give good results in the prediction of tail efficiency with angle of attack for inline configurations.

Report presenting an investigation of the aerodynamic loads on a leading-edge slat on a 40 degree sweptback wing with NACA 64(sub 1)-112 airfoil sections in the low-turbulence pressure tunnel. Results regarding wing force data, slat force data, and slat pressure distributions are provided.

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Memorandum presenting the results of an investigation of the stability, control, and induced rolling moments of a canard missile with cruciform wings of rectangular plan form at Mach number 1.7. All data including the measured hinge moments of the canard control surfaces, the axial forces on the complete missile, and the forces and moments on the various combinations of the missile components are presented in tabular form.

Memorandum presenting the results of an investigation of the stability, control, and induced rolling moments of a canard missile with cruciform wings of rectangular plan form at Mach number 1.7. All of the data obtained, including the measured hinge moments of the canard control surfaces, axial forces on the complete missile, and forces and moments on the various combinations of missile components are presented in tabular form.

Report presenting the results of a flight investigation of the lateral stability and control characteristics of a high-speed fighter airplane. Results regarding the control-free lateral oscillations, sideslip characteristics, rudder control characteristics, rudder hinge-moment characteristics, and rolling characteristics are provided.

Report presenting an investigation in the free-flight tunnel to determine the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with a sweptback-wing fighter model attached to each wing tip with freedom in roll. The results indicated that the longitudinal position of the fighters with respect to the bomber had an important effect on the flight behavior of the coupled configuration.

Memorandum presenting an investigation in the 9-inch supersonic tunnel of several missiles with low-aspect-ratio, cruciform, tandem lifting surfaces with a view toward developing a missile with small variations of center-of-pressure location at various angles of attack and roll. The investigation centered about a basic configuration with equal-span wings and tails.

The present RMA Line has now progressed through the run-in period and is engaged in actual production. Considerable new data and experiences are available for use in an evaluation of the basis used for design of the equipment in regard to contamination control and the safety of operating and maintenance personnel. Research and development funds have been allocated to the improvement of the 234-5 process equipment. Thus it is desirable that an up-to-date basis be established for use as criteria for the design development of these improvements. It is concluded that remote control operation of all plutonium purification and fabrication equipment is ultimately desirable. However, until reliable, tested, remote-control equipment is available, the remote control requirement may have to be compromised on some steps of the process to allow non-remote or rubber glove operation in order to obtain equipment with sufficient operating reliability.

From Summary: "Ogive-cylindrical fuselages of fineness ratio 11 have been flight-tested with and without stabilizing fins. Base-pressure measurements over a range of free-stream Mach numbers from 0.7 to 1.3 indicated that the fins reduced the base drag. A rear-support sting similar to those used in wind tunnels was tested with one of the fuselages and found to reduce base suction by 40 percent at subsonic speeds, but to have little effect at Mach numbers above 1.15."

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