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DECOMPOSITION OF WATER AND AQUEOUS SOLUTIONS UNDER PILE RADIATION
No Description Available.
Peroxide process -- 234-5 Building
The mechanical line being developed at Los Alamos is designed around the peroxide precipitation process. Development work, at that site, on this process has progressed to the point where actual plant equipment can be designed for future use. The process for converting the peroxide to a reducible fluoride is known. From the reduction step on, no change is necessary in the present process. The possibilities of a satisfactory peroxide process were recognized before design and construction of the R.G. Line, but the development work necessary for this process had not progressed far enough to have been included in that line. The gain to be realized by the adoption of the peroxide method is so great that the amount of work necessary for development of this process can certainly be justified at this time. Advantages of this process are summarized and it is recommended that serious consideration be given to using the peroxide process before design of the R.M. Line goes further.
Carrier-free Radioisotopes from Cyclotron Targets I. Preparation and Isolation of Sn113 and In114 from Cadmium
The cyclotron is the only practical source of many carrier-free radioisotopes. The preparation and radiochemical isolation of a number of these activities, produced in the 60-inch cyclotron of Crocker Laboratory, will be presented in this paper and in subsequent papers of this series. In most cases the carrier-free radioisotopes were prepared for use in biological systems and the final preparations were in the form of isotonic saline solutions at a range of pH from 5 to 8. The present paper reports the radiochemical isolation of carrier-free Sn{sup 113} and In{sup 114} produced by bombarding cadmium with 38 Mev alpha-particles. At this energy, Sn{sup 113} and In{sup 114} are produced in a thick target by the nuclear reactions; Cd{sup 110}({alpha},n)Sn{sup 113}, Cd{sup 111}({alpha},2n)Sn{sup 113}, Cd{sup 112}({alpha},3n)Sn{sup 113}, Cd{sup 111}({alpha},p)In{sup 114}, Cd{sup 112}({alpha},pn) In{sup 114}. The shorter-lived tin and indium activities together with the possible radioisotopes of silver produced by (n,p) reactions, were allowed to decay out prior to the chemical separations.
Design Factors for 4- by 8-Inch Ram-Jet Combustor
Report presenting an investigation of a series of flame holders designed with the objective of providing a high combustion efficiency in a ramjet combustor at an inlet air velocity of 200 feet per second, inlet-air pressure of 60 inches of mercury absolute, inlet air temperature of 200 degrees Fahrenheit, and near stoichiometric fuel-air ratio. Results regarding the preliminary experiments, two parallel rows of gutters, three rows of gutters, staggered gutters, simultaneous use of three rows and staggered gutters, use of molybdenum, and magnitude of pressure fluctuations are provided.
Study of the health aspects of dgreaser operation in the airlock of the 105 Building in the 100 H Area
On June 29th and July 13th, 1949, the Industrial Hygiene Group of the Health Instrument Divisions at HAPO conducted a study of the health aspects of the degreaser operations carried on in the Airlock adjoining the 105 Building in the 100 H Area. This was done at the request of the Medical Division. The results of the study, together with certain pertinent information concerning degreaser operation, are reported in this report.
Performance of J33-A-27 Turbojet-Engine Compressor 1: Over-all performance characteristics at equivalent impeller speeds from 6100 to 11,800 rpm
The J33-A-27 compressor was operated at an inlet pressure of 14 inches of mercury absolute and ambient inlet temperature over a range of equivalent impeller speeds from 6100 to 11,800 rpm. At the design equivalent speed of 11,800 rpm, the J33-A-27 compressor had a peak pressure ratio of 4.40 at an equivalent weight flow of 105.7 pounds per second and a peak adiabatic temperature-rise efficiency of 0.745. The maximum equivalent weight flow at design speed was 113.5 pounds per second.
CHEMISTRY DIVISION, SECTION C-11 SUMMARY REPORT FOR JULY, AUGUST, AND SEPTEMBER 1948
No Description Available.
An analysis of available data on effects of wing-fuselage-tail and wing-nacelle interference on the distribution of the air load among components of airplanes
From Introduction: "The purpose of the present paper is to summarize the available data on the effects of wing-fuselage-tail and wing-nacelle interference on the distribution of the air load among aircraft components. Some discussion is also given of the effects of center-of-gravity position."
Redox Committee: Conference notes and recommendations, meeting of April 11, 1949
This report discusses recommendations for development work on the Redox Production Plant. It contains an outline for a relationship procedure between the architect engineer and General Electric Design Division; preparation of a material balance and process flow; the preparation of engineering flow diagrams, including lists of standard symbols for these diagrams; a material and equipment list; a project cost estimate; and Procedures covering institution and execution of work involving studies by the Design and Construction Division.
Full-Scale Investigation of a Wing With the Leading Edge Swept Back 47.5 Degrees and Having Circular-Arc and Finite-Trailing-Edge-Thickness Ailerons
Report presenting an investigation to determine the aerodynamic characteristics of a wing with a leading sweptback edge at 47.5 degrees and a 20-percent-chord, 50-percent-span outboard aileron. The wing had symmetrical circular-arc airfoil sections and was tested with a circular-arc contour aileron and a flat-sided contour aileron with finite trailing-edge thickness. The longitudinal aerodynamic characteristics and aileron effectiveness are provided for both types of ailerons.
Oxides of nitrogen exposures accompanying pickling operations 313 Building - 300 Area
No Description Available.
Aerodynamic characteristics of a flying-boat hull having a length-beam ratio of 15 and a warped forebody
From Introduction: "The results of two phases of this investigation, presented in references 1 and 2, have indicated possible ways of reducing hull drag without causing large changes in aerodynamic stability and hydrodynamic performance."
COMPARISON OF VARIOUS METHODS FOR THE REMOVAL OF URANIUM FROM CARBON SALVAGE
No Description Available.
[Office of Hanford Directed Operations events of importance for week ending February 9, 1949]
This report details events of importance reported by the Hanford Operations Office for the week ending February 9, 1949.
Free-Flight Investigation at Transonic and Supersonic Speeds of the Rolling Effectiveness of Several Aileron Configurations on a Tapered Wing Having 42.7 Degrees Sweepback
Report presenting an investigation of several aileron modifications in conjunction with a tapered, sweptback wing with circular-arc airfoil sections of relatively large thickness ratio. This testing permits the evaluation of the wing-aileron rolling effectiveness over a range of Mach numbers. Results regarding true-contour ailerons, extended-chord ailerons, and blunt trailing-edge ailerons are provided.
Langley Free-Flight-Tunnel Investigation of the Automatic Lateral Stability Characteristics of a Model Equipped with a Gyro Stabilizing Unit that Provided either Flicker-Type or Hunting Control
Memorandum presenting an investigation to determine the automatic lateral stability characteristics of a model equipped with a gyro stabilizing unit that gave response to bank and yaw. Stable flights were obtained with the flicker-type automatic control, and the amplitude of the oscillations was decreased by adding the attachment which provided hunting control.
Activity of fission products
This report compares the activity and disintegration energy of fission products from metal under two conditions of exposure: 200 Megawatt-days integrated exposure over a period of 180 days, and 400 Megawatt-days integrated exposure over a period of 360 days. (JL)
200 Area stack contamination. Interim report, August 2, 1948--October 11, 1948
In connection with the problem of eliminating contamination of the atmosphere by the exhaust from the 221 Building ventilation air stacks, sand filters were previously recommended. Construction of a sand filter in West Area is about completed and construction of a filter in East Area is well underway. This report summarizes the status, technical findings, and comments and suggestions since the writer`s last Interim Report, dated August 6, 1948, was issued.
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Subsonic Mach and Reynolds number effects on the characteristics of the wing and on the effectiveness of an elevon
Report presenting a wind-tunnel investigation of a semispan model of a wing swept back 63 degrees with an aspect ratio of 3.5 and a taper ratio of 0.25. The tests were conducted to evaluate the effects of Reynolds and Mach number on the aerodynamic characteristics of the wing. Results regarding the characteristics of the wing with the elevon undeflected, effectiveness of the elevon, effects of roughness strips, and effect of model deflection under varying loads are provided.
The Ion-Exchange Separation of Zirconium and Hafnium
In the course of a rather cursory examination of the elution of tetra-positive ions from the cation exchange resin Dowex 50 with hydrochloric acid solutions, the authors have discovered a very effective method of separating zirconium from hafnimu. In view of the great labor involved in preparing even reasonably pure hafnium compounds by existing methods, they feel that this procedure will prove very valuable to those interested in obtaining hafnium compounds free of zirconium. Although the conditions which give satisfactory separation were first worked out using microgram amounts of material and the radioactive tracer technique, the run described here, involving milligrams of material, illustrates the applicability of the method to the production of significant amounts of pure hafnium and zirconium.
Safety Tests on Hand Stacking of U-235 Cubes
From abstract: "Critical assembly tests have been made on the Pajarito Universal Machine to determine the safety limits of handstacking cubes of 95% U-235 in spherical geometries preparatory to making critical assemblies of U-235 in an "infinite" tuballoy tamper. The U-235 cubes were stacked as pseudospheres in a cavity at the top of a tuballoy block 12" high and 8" on a side, and the assembly tamped by locating it inside a doughnut shaped water tank whose tamping effect is equivalent to the tamping caused by personnel necessary for hand stacking."
Flight Tests of a Two-Dimensional Wedge Diffuser at Transonic and Supersonic Speeds
"A two-dimensional wedge diffuser, designed to be used with a ducted-airfoil ram jet, was tested on a rocket-powered test vehicle up to a Mach number of 1.45. Orifice plates and a choking section behind the diffuser exit simulated burning in a combustion chamber by providing the proper pressure drop. Results obtained from these tests showed there was no abrupt changes in mass flow and pressure recovery as the model velocity increased through the transonic region" (p. 1).
Comparison of Hovering Performance of Helicopters Powered by Jet-Propulsion and Reciprocating Engines
Report presenting an investigation of the maximum hovering time, or the time that a helicopter can sustain itself without motion, for helicopters using a reciprocating engine, by ramjet engines at the tips of rotor blades, and by pulse-jet engines at the tips of rotor blades. Testing showed that the reciprocating engine permitted much longer hovering time than the jet-propulsion engines, but the jet-propulsion engines were much lighter and could lift greater disposable loads.
Lexington Project Report Number 24: Aircraft
This report talks about aircraft design demand
An Investigation of the Downwash Behind a High-Aspect-Ratio Wing With Various Amounts of Sweep in the Langley 8-Foot High-Speed Tunnel
Report presenting measurements of downwash angles at points at two vertical positions at the probable tail location behind a high-aspect-ratio wing with an NACA 65-210 section with no sweep and 30 degrees and 45 degrees of sweepback and sweepforward in conjunction with a fuselage.
Research Progress Meeting for March 11,1948
The linear accelerator is again in operation after a shutdown fore repairs and minor changes. Radiofrequency checks of the instrument were made while the Van de Graaff was open. The vacuum of the system is now very good, the base pressure being 1.7 x 10{sup -6} mm Hg with a rate of rise of 800 s/{micro}s. Some preliminary results have been obtained on the activation of carbon with protons. The experiments were done using 10 mil, 50 mg/cm{sup 2} polystyrene discs. The activation curve obtained is shown. The break shown in the curve was found on two separate runs and it yet unexplained. In another experiment a proton induced activity in nickel was found. This had a 3.3 second half-life. Positive mesons have been detected on plates exposed in the 184-inch cyclotron with an arrangement shown schematically. The beam ws allowed to strike a 1/16 inch carbon target, and the mesons, which are bent around by the magnetic field, were detected with photographic plaes placed beneath the circulating beam. A series of experiments were done in which the plates were placed at distances varying from 1-1/2 to 3/4 inch from the beam between 1/4 inch plates of copper. The plates obtained at 1 inch and 3/4 inch were so blackened as to be unusable. From the plates secuired at 1-1/4 inch Lattes has found a total of 30 positive meson tracks, of which 20 end in the emulsion. Eight of these were found to give rise to seconaries, none of which stopped in the emulsion. This work was done with 50 micron plates and will be extended using 100 micron plates. The data will be further analyzed to see if all of the positive mesons and in secondaries. The number of positive mesons produced seems to be comparable to the …
Calculation of Wing Bending Moments and Tail Loads Resulting from the Jettison of Wing Tips During a Symmetrical Pull-Up
"A preliminary analytical investigation was made to determine the feasibility of the basic idea of controlled failure points as safety valves for the primary airplane structure. The present analysis considers the possibilities of the breakable wing tip which, in failing as a weak link, would relieve the bending moments on the wing structure. The analysis was carried out by computing the time histories of the wing and stabilizer angle of attack in a 10g pull-up for an XF8F airplane with tips fixed and comparing the results with those for the same maneuver, that is, elevator motion but with tips jettisoned at 8g" (p. 1).
A comparison with flight data of vertical-tail loads in various maneuvers estimated from sideslip angles and rudder deflections
Report presenting a comparison of the vertical-tail loads determined from pressure-distribution measurements in flight in various maneuvers with the corresponding vertical-tail loads. Some of the maneuvers investigated included slow rolls, steady sideslips, fishtails, and rolling pull-outs.
Physics Division. Quarterly Report, Period Covered September, October and November 1947
No Description Available.
Preliminary Tests to Determine the Maximum Lift of Wings at Supersonic Speeds
Report presenting the results of a test program in a supersonic tunnel to determine the maximum lift of wings operating at supersonic speeds. A variety of wing plan forms of several thickness distributions were tested at a range of Mach numbers, Reynolds numbers, and angles of attack. The lift results, drag results, and Schileren photographs are described.
Tests of Submerged Duct Installation on a Modified Airplane in the Ames 40- by 80-foot Wind Tunnel
Memorandum presenting an investigation of an NACA submerged intake installation on a modified fighter airplane conducted to determine the full-scale aerodynamic characteristics of this installation. Additionally, tests were conducted on the submerged inlet with revised entrance lips and deflectors to determine the configuration which would result in the best dynamic pressure recovery measured at the inlet for this installation without a major rework of the entrance.
Fraunhofer Diffraction Pattern Produced by a Slit of Varying Width and its Application to High Speed Cameras
Abstract: "A theoretical and experimental investigation is made of the diffraction pattern produced by a slit, whose aperture varies uniformly from a constant value A to zero. The results of this investigation are applied to a proposed high speed camera. It is shown that diffraction effects are very serious and cannot be neglected. It seems, unless the suggested design of this high speed camera is changed, the camera will be of little use for accurate measurements, and photographs will show too much blue to give details."
Report on Zirconium Nitride
Report presenting the properties and method of preparation of zirconium nitride, a compound that was being considered for use in high temperatures due to its high melting point and hardness.
Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine 3: performance with tail-pipe burning in standard-size tail pipe
From Introduction: "Evaluation of tail-pipe burning in this engine with a larger tail-pipe combustion chamber is discussed in reference 1. Results of investigations on tail-pipe burning in this engine at static sea-level conditions are presented in reference 2. An investigation of thrust augmentation by means of injecting water at the inlet of an axial-flow compressor engine is discussed in reference 3."
THE EXTRACTION OF IONIUM BY ORGANIC SOLVENTS
No Description Available.
Investigation of the I-40 Jet-Propulsion Engine in the Cleveland Altitude Wind Tunnel. V - Operational Characteristics, 5, Operational Characteristics
An investigation has been conducted in the Cleveland altitude wind tunnel to determine the operational characteristics of the I-40 jet-propulsion engine over a range of pressure altitudes from 10,000 to 50,000 feet and ram-pressure ratios from 1.00 to 1.76. Engine operational data were obtained with the engine in the standard configuration and with various modifications of the fuel system, the electrical system, and the combustion chambers. The effects of altitude and airspeed on operating speed range, starting, windmilling, acceleration, speed regulation, cooling, and vibration of the standard and modified engines were determined, and damage to parts was noted.
Application of Ascorbic Acid Method to Uranium in Salvage Solutions
Abstract: The erroneously high values for uranium content of salvage solutions as determined by the ether extraction-ascorbic acid procedure have been demonstrated to be due to the presence of colored organic materials in these solutions. Evaporation of such solutions to fumes of HC104 before extraction has been shown to be completely successful in preventing such interference while pretreatment with activated carbon is sufficiently successful for application in Control laboratories. Complete procedures for application of either protreatment and results of such application to composite salvage solutions received over a six-month period are included.
Results of Flight Test of an Automatically Stabilized Model C (Swept Back) Four-Wing Tiamat
"The results of the first flight test of a swept-back four-wing version of Tiamat (MX-570 model C) which was launched at the NACA Pilotless Aircraft Research Station at W4110PB Island, Va. are presented. In general, the flight behavior was close to that predicted by calculations based an stability theory and oscillating table tests of the autopilot. The flight test thus indicates that the techniques employed to predict automatic stability are valid and practical from an operational viewpoint" (p. 1).
Supersonic Wave Drag of Sweptback Tapered Wings at Zero Lift
An analysis has been made of airfoil data taken on several NACA 16-series propeller airfoils from tests of 5-inch-chord models in the Langley 24 inch high-speed tunnel and l2-inch-chord models in the Langley 8 foot high-speed tunnel, This analysis has shown that the combined effects of Reynolds number changes and variations in airfoil characteristics resulting from differences in models and tunnels are such that when 5 inch-chord and l2-inch-chord data are applied to full-scale propeller design at or near the design condition, differences of less than 1 percent in efficiency will be involved.
Observations on an aileron-flutter instability encountered on a 45 degree swept-back wing in transonic and supersonic flight
Report presenting a flight test of a supersonic research pilotless aircraft in which large-amplitude aileron oscillations, most likely aileron compressibility flutter, were encountered in the transonic and supersonic speed ranges. Results regarding power-on flight and coasting flight are provided.
Tests of a Horizontal-Tail Model through the Transonic Speed Range by the NACA Wing-Flow Method
"A 1/12-scale model of a horizontal tail of a fighter airplane was tested through the transonic speeds in the high-speed flow over an airplane wing, the surface of which served as a reflection plane for the model. Measurements of lift, elevator-hinge moment, angle of attack, and elevator angle were made in the Mach number range from 0.75 to 1.04 for elevator deflections ranging from 10 degrees to minus 10 degrees, and for angles of attack of minus 1.2 degrees, 0.4 degrees, and 3.4 degrees. The equipment used to measure the hinge moments of the model proved to be unsatisfactory, and for this reason the hinge-moment data are considered to be only qualitative" (p. 1).
Aerodynamic Measurements Made During Navy Investigation of Human Tolerance to Wind Blasts
From Summary: "This report presents the aerodynamic measurements made during a Navy investigation conducted in the Langley 8-foot high speed tunnel to determine the actual human tolerance to wind blasts."
Extraction of Uranium from Iron Box Sludge
It was desired to establish the adaptability of iron box sludge, a residue recovered in the initial concentration of domestic ores, as a raw material from the production of high purity U{sub 3}O{sub 8}. This report summarizes the experimental work on the extraction of uranium from iron box sludge and that on the removal of V{sub 2}O{sub 5} and P{sub 2}O{sub 5} from the solutions.
Knock-Limited Performance of Triptane and 28-R Fuel Blends as Affected by Changes in Compression Ratio and in Engine Operating Variables
From Summary: "A knock-limited performance investigation was conducted on blends of triptane and 28-P fuel with a 12-cylinder, V-type, liquid-cooled aircraft engine of 1710-cubic-inch displacement at three compression ratios: 6.65, 7.93, and 9.68. At each compression ratio, the effect of changes in temperature of the inlet air to the auxiliary-stage supercharger and in fuel-air ratio were investigated at engine speeds of 2280 and. 3000 rpm. The results show that knock-limited engine performance, as improved by the use of triptane, allowed operation at both take-off and cruising power at a compression ratio of 9.68."
Wind-Tunnel Investigation of Wing Inlets for a Four-Engine Airplane
Report presenting an investigation in the propeller-research tunnel to develop wing-leading-edge inlets for locations between the inboard and outboard nacelles on each wing of a four-engine airplane. Testing was performed on the basic wing and original inlet as well as NACA-developed inlets for two versions of the airplane.
Computed Temperature Distribution and Cooling of Solid Gas-Turbine Blades
"Computations were made to determine the temperature distribution and cooling of solid gas-turbine blades.A range of temperatures was used from 1500 degrees to 2500 degrees F, blade-root temperatures from 100 degrees to 1000 degrees F, blade thermal conductivity from 8 to 220 BTU/(hr)(sq ft)(degrees F/ft), and net gas to metal heat transfer coefficients from 75 to 250 BTU/(hr)(sq ft)(degrees F)" (p. 1).
Cooling of Gas Turbines 1 - Effects of Addition of Fins to Blade Tips and Rotor, Admission of Cooling Air Through Part of Nozzles, and Change in Thermal Conductivity of Turbine Components
"An analysis was developed for calculating the radial temperature distribution in a gas turbine with only the temperatures of the gas and the cooling air and the surface heat-transfer coefficient known. This analysis was applied to determine the temperatures of a complete wheel of a conventional single-stage impulse exhaust-gas turbine. The temperatures were first calculated for the case of the turbine operating at design conditions of speed, gas flow, etc. and with only the customary cooling arising from exposure of the outer blade flange and one face of the rotor to the air" (p. 1).
Cooling of Gas Turbines, 3, Analysis of Rotor and Blade Temperatures in Liquid-Cooled Gas Turbines
A theoretical analysis of the radial temperature distribution through the rotor and constant cross sectional area blades near the coolant passages of liquid cooled gas turbines was made. The analysis was applied to obtain the rotor and blade temperatures of a specific turbine using a gas flow of 55 pounds per second, a coolant flow of 6.42 pounds per second, and an average coolant temperature of 200 degrees F. The effect of using kerosene, water, and ethylene glycol was determined. The effect of varying blade length and coolant passage lengths with water as the coolant was also determined. The effective gas temperature was varied from 2000 degrees to 5000 degrees F in each investigation.
Development of Inboard Nacelle for the XB-36 Airplane
From Summary: "A series of investigations of several 1/14-scale models of an inboard nacelle for the XB-36 airplane was made in the Langley two-dimensional low-turbulence tunnels. The purpose of these investigations was to develop a low-drag wing-nacelle pusher combination which incorporated an internal air-flow system. As a result of these investigations, a nacelle was developed which had external drag coefficients considerably lower than the original basic form with the external nacelle drag approximately one-half to two-thirds of those of conventional tractor designs. The largest reductions in drag resulted from sealing the gaps between the wing flaps and nacelle, reducing the thickness of the nacelle training-edge lip, and bringing the under-wing air inlet to the wing leading edge."
Investigation of Pressure Losses in Several Turbosupercharger Nozzle Hoses
Memorandum presenting surveys of the impact pressure of the flow to obtain information for determining pressure losses in four different turbosupercharger nozzle boxes. The data indicated substantial differences in total head loss among the boxes and the existence of sharply defined high-loss regions in portions of the nozzle annulus.
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