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Here's a war job for you : railroad workers urgently needed.
Five tracks of locomotives run side by side. One of the trains is transporting army tanks.
Keep your Red Cross at his side : give!
Image of a soldier in a helmet. Green foliage is seen in the background. A large Red Cross symbol appears in the lower right area of the poster.
Smoking characteristics of various fuels as determined by open-cup and laboratory-burner smoke tests
Report discussing tests in a combustion chamber to obtain smoking characteristics data on a variety of hydrocarbon fuels. Details about the smoking tendencies and burning rates of the fuels in uncontrolled and controlled tests are provided.
This is the enemy.
Stylized caricature of a scowling German soldier. There is a swastika on his cap. He wears a monocle in one eye; in the monocle is a reflection of a person hanging on a gallows.
With your help China shall teach and lead her own.
Color poster shows a painting of a Chinese woman and young boy in traditional Chinese clothing. The woman has black hair and wears a fitted green dress. The boy wears a black and red cap and a red shirt. He holds an open book.
Electronics progress report, April 1--30, 1949
Prospectus` of Band Pass Amplifiers for Proportional Counters and Instrumentation for the Study of the Electrodeposition Potential of Radioactive Elements have been submitted for review and approval. An error was found in calculations for the band pass amplifier discussed in Group 9 of the Electronics Progress Report,MLM-306, March 1--31, 1949, on the Cathode-Follower Probe. New calculations have been made and a band pass filter constructed to match the new values. Work on the cathode-follower circuit for coupling a Boron-wall tube to its linear amplifier indicated that the limit to the sharpness of a pulse which could be achieved was possibly caused by poor amplitude versus frequency response of the linear amplifier. To check this theory, modifications were made on an existing scaler which resulted in a frequency response flat up to 4.5 megacycles. Plans are being made to improve the amplitude versus frequency of the higher frequencies. The response curve shows a slightly rising characteristic at 4.5 megacycles and an attenuation at 7 megacycles. Construction of the rf generator has been resumed in an effort to deliver the finished product to Group 4 by approximately May 6, 1949. The meter circuit will measure relative rf output voltage instead of absolute voltage. The prospectus for the research on high speed scaling circuits has been completed and the prospectus for research on the high speed trigger pairs is being completed. The prospectus` of Parallel Plate Alpha Chambers and Scintillation Counting has also been completed.
Electronics progress report, March 1--31, 1949
With the completion of tests of the prototype cathode-follower, it was decided to produce three more models. These have been constructed and pass the same pulse as that of the prototype. Drawings are being made of these units. By the time these units had been completed, the amplifier of the scaler was modified so that its frequency response was essentially flat up to 4.5 megacycles. Using this amplifier and the cathode-follower, a study of the pulse shapes was made and four different pulse shapes were found to be obtainable. A band pass network between the B-wall tube and the input of the cathode-follower provided a very substantial improvement over the shunt peaking network with a band pass of 1.8 to 6.5 megacycles and provided clean, uniform pulses. Plans are being made to experiment with a filter of narrower band pass, which, if satisfactory, will produce greater amplitude. When the final band pass has been determined, a combination of shunt peaking and band pass networks should provide a net gain of 30% in amplitude. The result of this research is to provide an immediate improvement in resolution loss and a possibility of realizing a still lower minimum resolving time when the other components in the counting system have been improved. With the amplitude obtained and the use of pass bands of frequencies, it may be possible to develop a B-wall amplifier using one stage of amplification.
Instrumental analysis progress report, June 1--30, 1949
Several bismuth compounds have been submitted by E. Orban for examination by x-ray diffraction. The sample of polonium in contact with platinum mentioned in the May progress report was received and identified tentatively from its x-ray diffraction pattern as PtPo{sub 2}. Calibration of the Perkin-Elmer infrared spectrophotometer has been completed and a preliminary study of the infrared absorption of NiCO{sub 4} made. Data showing the spectral purity obtainable on three ultraviolet-visible spectrophotometers have been completed. The emission spectrum of a sample of volatile impurity from the operations process has been obtained.
Production research progress report, March 1--31, 1949
A study has been made of the time and temperature required to anneal Teflon and Fluorothene. It has been found that, by proper annealing, the strains my be removed and cold-flow prevented. The disk stopcocks prepared with annealed plastics have not developed leaks on standing. A description is given of the modified slug-dissolver heating unit which has been installed in the Bismuth-II Process Line. Work has been continued on the absorption spectra of bismuth in hydrochloric acid solutions. Two methods have been described for the interpretation of absorption spectra data. The transmission curve of the Evelyn colorimeter filters have been measured on the Cary recording spectrophotometer. The resulting curves should aid in the selection of the proper filter for a given calorimetric analyses. A brief outline for the proposed method of decontaminating platinum has been presented.
Recovery of uranium and plutonium from Redox off-standard aqueous waste streams
In the operation of countercurrent extraction columns as in the Redox process, it is possible, and probable, that from unexpected behaviour of a column, operator error, colloid formation, etc., there will result from time to time excessive losses of uranium and plutonium in the overall process. These losses will naturally accumulate in the waste streams, particularly in the aqueous waste streams. If the loss is excessively high, and such lost material can be recovered by some additional method, then if economical and within reason, the recovered materials ran be returned to a ISF column for further processing. The objective of this work has been to develop such a method to recover uranium and plutonium from such off-standard waste streams in a form whereby the uranium send plutonium can be returned to the process line and subsequently purified and separated.
Nomograms for Obtaining the Compound Composition of Hydrated Limes from the Oxide Analysis
Report with two nomograms presented for rapidly obtaining the compound composition of hydrated limes from the oxide analysis. The general nomogram can be applied to any commercial hydrated lime and gives values accurate to within 0.3 percent while the special nomogram is applicable only to regularly hydrated and highly hydrated dolomitic limes and is accurate to within 0.1 percent.
Trip Report, December 16--21, 1949
December 16--20, 1949 were spent in inspection of the equipment of the Naval Pilot Channel Test Rig at the Oak Ridge pile, observation of its maintenance and use, and in discussions with the test operating personnel, and members of the H.P. and pile operating divisions. December 21 was spent at the Argonne National Laboratories, Naval Reactor Division, in inspection of the test rig under construction for use at the H pile. Dr. Etherington requested that I express their desire to arrange that an Argonne scientist be at Hanford with the test rig to act in an advisory capacity, for consultation, and to prepare such reports to Argonne as they may need to call for as the test progresses.
No Description Available.
A PreliminaryReport on the Mechanism of the Decomposition ofDiacetyl Peroxide in Acetic Acid
The decomposition of diacetyl peroxide in acetic acid-2-C{sup 14} has been studied, The activity of the products in general confirmed the mechanism of the reaction as proposed by Kharasch and Gladstone, The presence and distribution of activity in the methyl acetate produced in this reaction is not explained by the previously proposed mechanism. There was no appreciable exchange of acetic acid and diacetyl peroxide under the conditions of the reaction. Essentially no exchange of methyl acetate and acetic acid was observed when those reagents mere heated at 100 for five hours.
Homogeneous Reactor Preliminary Process Design Report
"The following report is meant to serve a two fold purpose. First, it is the quarterly report of the homogeneous reactor project for the Technical Division of Oak Ridge National Laboratory. Secondly, it is a description and general feasibility discussion of a 200-1000 K.W. pilot model, homogeneous reactor."
Correlation of pressure drop data isothermal flow through standard process tube assembly
The experimental data presented in HDC-1255 for the pressure drops through the various portions of a standard process tube assembly for isothermal flow are correlated in this report. Data include orifice sizes up to 0.310 inches. The equations have been adapted for the calculation of pressure drops or flow rates for clean tubes in pile operation. A systematic procedure is outlined for determining the pressure drops through each portion of the tube assembly. A method is presented for calculating the flow rate through a process tube from header pressure and panellit age readings.
Trip report: Argonne National Lab., Naval Reactor Division, December 12--13, 1949
This trip was spent in conferences with H. Etherington, A. Amroni, Geo. Anderson, and L.W. Fromm; and in inspection of components now being built for the Navy Test Rig which is to be installed at H Pile. Mr. Anderson believes that the entire assembly will arrive at Hanford between January 16 and 23, 1950. Much has yet to be designed and built, however. Also, certain incompatibilities with the H Pile were pointed out, and will be altered.
Radioactive contamination in the environs of the Hanford Works for the period January, February, March 1949
This report summarizes in somewhat more detail than the monthly H.I. Environs reports the extent and magnitude of the radioactive contamination detected in the environs of the Hanford Works. Radioactive contamination resulting from the operation of the Hanford Works as well as that found occurring in natural quantities is included. This belated report is being issued merely for the records to serve as a composite summary of measurements already reported in the monthly H.I. Environs reports and covers the quarterly period January, February, and March, 1949.
Ditching Investigation of a 1/18-Scale Model of the North American B-45 Airplane
An investigation of a 1/18-scale dynamically similar model of the North American B-45 airplane was made to observe the ditching behavior and determine the proper landing technique to be used in an emergency water landing. Various conditions of damage were simulated to determine the behavior which probably would occur in a full-scale ditching. The behavior of the model was determined from high-speed motion-picture records, time-history acceleration records, and visual observations. It was concluded that the airplane should be ditched at the maximum nose-high attitude with the landing flaps full down for minimum landing speed. During the ditching, the nose-wheel and bomb-bay doors probably will be torn away and the rear of the fuselage flooded. A violent dive will very likely occur. Longitudinal decelerations of approximately 5g and vertical accelerations of approximately -6g (including gravity) will be experienced near the pilots' compartment. Ditching braces installed in the bomb bay will tend to improve the behavior slightly but will be torn away along with the bomb-bay doors. A hydroflap installed ahead of the nose-wheel doors will eliminate the dive and failure of the nose-wheel doors, and substantially reduce the motions and accelerations.
Theoretical antisymmetric span loading for wings of arbitrary plan form at subsonic speeds
A simplified lifting-surface theory that includes effects of compressibility and spanwise variation of section lift-curve slope is used to provide charts with which antisymmetric loading due to arbitrary antisymmetric angle of attack can be found for wings having symmetric plan forms with a constant spanwise sweep angle of the quarter-chord line. Consideration is given to the flexible wing in roll. Aerodynamic characteristics due to rolling, deflected ailerons, and sideslip of wings with dihedral are considered. Solutions are presented for straight-tapered wings for a range of swept plan forms.
Effects of wing flexibility and variable air lift upon wing bending moment during landing impacts of a small seaplane
From Summary: "A smooth-water-landing investigation was conducted with a small seaplane to obtain experimental wing-bending-moment time histories together with time histories of the various parameters necessary for the prediction of wing bending moments during hydrodynamic forcing functions. The experimental results were compared with calculated results which include inertia-load effects and the effects of air-load variation during impact. The responses of the fundamental mode were calculated with the use of the measured hydrodynamic forcing functions. From these responses, the wing bending moments due to the hydrodynamic load were calculated according to the procedure given in R.M. No. 2221. The comparison of the time histories of the experimental and calculated wing bending moments showed good agreement both in phase relationship of the oscillations and in numerical values."
The Densities of Tributyl Phosphate - Carbon Tetrachloride Solutions Containing Uranium and Nitric Acid
The following report provides the analysis of a large number of unreported data--taken during a study described in report HW-15230--containing density values obtained for solutions of uranium and nitric acid in tributyl phosphate-carbon tetrachloride solutions.
Flight Test of the Aerojet 7KS-6000 T-27 Jato Rocket Motor
"A flight test of the Aero jet Engineering Corporation's 7KS-6000 T-27 Jato rocket motor was conducted at the Langley Pilotless Aircraft Research Station at Wallops Island, Va, to determine the flight performance characteristics of the motor. The flight test imposed an absolute longitudinal acceleration of 9.8 g upon the rocket motor at 2.8 seconds after launching. The total impulse developed by the motor was 43,400 pound-seconds, and the thrusting time was 7.58 seconds" (p. 1).
A free-flight technique for measuring damping in roll by use of rocket-powered models and some initial results for rectangular wings
Report presenting a simplified method for obtaining free-flight measurements of damping in roll through the use of rocket-powered models. Initial configurations have been tested for a range of Mach numbers. Results regarding the rolling velocity with two different airfoil sections and damping-in-roll coefficient are provided.
Level and Leak Indicators
The following report provides results taken from a sodium level indicator developed at Sacandaga using electrical resistance as the principle.
Refrigeration System Used in Mercury Isotope Collections
From introduction: During 1948, the Isotope Research and Production Division undertook to obtain small quantities of nearly pure mercury isotopes by electromagnetic isotope separation. The possible use of a mercury isotope of even-numbered mass to establish an international standard of length required an isotopic purity greater than 99 per cent. It, became apparent that this degree of separation could only be achieved by preventing random diffusion of un-ionized mercury which otherwise would contaminate the isotope collectors.
Spontaneous Fission of 48
Report discussing an experiment to reinvestigate the spontaneous fission of 48 (Pu-238) in an effort to determine a more accurate value for the spontaneous fission constant that was found in a previous experiment.
Comparison of Effectiveness of Coordinated Turns and Level Sideslips for Correcting Lateral Displacement During Landing Approaches
Memorandum presenting a calculation of the amount of possible correction for coordinated turns with limited bank angle and level sideslips for a large transport airplane, the C-54D. The results indicate that for all instances from the end of the runway, coordinated turns are the more effective maneuver.
No Description Available.
Low-speed investigation of deflectable wing-tip ailerons on an untapered 45 degrees sweptback semispan wing with and without an end plate
Report presenting a low-speed wind-tunnel investigation to determine the characteristics of deflectable wing-tip ailerons on an untapered 45 degree sweptback semispan wing. Ailerons with triangular and parallelogram plan forms with a maximum chord of 0.625 wing chord and a flat-plat profile were investigated. The aerodynamic characteristics in pitch and lateral control characteristics are included.
Preliminary Investigation of a Variable Mass-Flow Supersonic Nose Inlet
Memorandum presenting a method for varying the mass flow of supersonic inlets with a circular cross section and a central body. The method consists of changing the size of the entering stream tube by means of an inflatable boot on the surface of the central body.
Comparative tests of the rolling effectiveness of constant-chord, full-delta, and half-delta ailerons on delta wings at transonic and supersonic speeds
Report presenting comparative tests of the rolling power of plain constant-chord, full-delta, and half-delta ailerons on delta wings with varying degrees of sweepback were tested on rocket-propelled test vehicles. Results regarding the effect of leading-edge sweepback, a comparison of rolling effectiveness, and comparison with theory are provided.
Experimental investigation at supersonic speeds of side scoops employing boundary-layer suction
Report presenting the pressure-recovery characteristics of a model with two scoops situated on the aft position of a long forebody and connected through diffusors to a common settling chamber at a range of Mach numbers. The effects of interaction between the flow in the two air-induction systems and of varying the mass flow through the boundary-layer scoops were studied. Results at several different angles of attack are provided.
Preparation of Ductile Zirconium: Progress Report for November 1949
Report discussing the progress made on a research project for the preparation of ductile zirconium during November 1949.
The effects of scale and test technique on the validity of small-scale measurements of the aerodynamic characteristics of a wing with the leading edge swept back 63 degrees
Report presenting the lift and pitching-moment characteristics of two wings of the same plan form measured over a range of Mach and Reynolds numbers using the wing-flow method. One wing had a symmetrical airfoil section and no twist, while the other was cambered and twisted to support a uniform load distribution at a lift coefficient of 0.25 at Mach number 1.5. A comparison with previous testing is also provided.
An empirical criterion for fin stabilizing jettisonable nose sections of airplanes
"Investigations in the Langley 20-foot free-spinning tunnel of models of five jettisonable nose sections have shown that the airplane nose sections are inherently unstable but can be stabilized by the addition of suitable fins. An empirical criterion has been developed which indicates the fin area required for stabilizing an airplane jettisonable nose section" (p. 1).
Hemoglobin labeled by radioactive lysine. Erythrocyte life cycle
No Description Available.
Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel 5: Static Longitudinal Stability and Control Throughout the Subsonic Speed Range of a Semispan Model of a Supersonic Airplane
Memorandum presenting wind-tunnel tests of a semispan model of a hypothetical supersonic airplane to determine the static longitudinal stability and control characteristics of the airplane throughout the range of subsonic Mach numbers up to 0.95. The model had a long slender fuselage and a wing and horizontal tail of aspect ratio 4 and taper ratio 0.5. Results regarding the force and moment characteristics, wing wake and effective downwash at the horizontal tail, effects of compressibility, and longitudinal characterisitcs with the flaps deflected are provided.
Full-Scale Hydrodynamic Evaluation of a Modified Navy J4F-2 Amphibian with a 0.425-Scale XP5M-1 Hull Bottom: TED No. NACA DE325
An investigation was made to evaluate the hydrodynamic qualities of a 0.425-scale model of the Navy XP5M-1 hull, which was installed on a modified Navy J4F-2 amphibian. Longitudinal and directional stability during take-off and landing, low-speed maneuverability, spray characteristics, and take-off performance were investigated. The behavior of the airplane in moderately rough water was also observed. The opinions of three pilots have been correlated with the data.
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effects at subsonic speeds of a constant-chord elevon on a wing cambered and twisted for a uniform load at a lift coefficient of 0.25
Report presenting testing of a cambered and twisted wing with constant-chord elevons with a slender fuselage to determine the longitudinal and lateral control from the elevons for a range of Mach numbers. Results regarding lift, drag, pitching-moment, and rolling-moment characteristics for various elevon deflections are provided.
Investigation of altitude performance of AN-F-58 fuels in annular combustor of J34-WE-22 engine
From Summary: "An investigation was conducted in the combustor of a 3000-pound-thrust turbojet engine to determine the altitude performance characteristics of AN-F-58 fuels. Three fuels conforming to AN-F-58 specification were prepared in order to determine the influence of boiling-temperature range and aromatic content on altitude performance. The performance of the three AN-F-58 fuels was compared with the performance of AN-F-48 (grade 100/130) fuel in the range of simulated altitudes from 20,000 to 55,000 feet, corrected engine speeds from 6000 to 12,500 rpm, and flight Mach numbers of 0.2 and 0.6."
Materials Testing Reactor Project: Coffins and Coffin Handling, Design Report No. 21
The following report discusses special shielded containers, called coffins, that are used for removing beam hole plugs from the reactor, transporting them to plug storage and inserting them therein. This report focuses on the handling of dummy and experimental beam hole plugs.
Reduction of oxides of nitrogen exposures at pickling operation, 313 Building, 300 area
Short communication.
Decontamination of Redox Feed Solutions by Super Filtrol Scavenging
From introduction: "This report examines the hazard which would result in the extremely unlikely event that all of the safety devices failed to operate either by accident or sabotage."
Events of importance for week ending November 30, 1949
Waste disposal, pile operations and P-10 operations are reported. Construction in the 100 (Pile) areas, 200 (Separations) areas, and 400 (Technical Center) area is described. General work included Richland paving, the Southern Railroad connection, and the Richland levee. Personnel data and visitor information is also included.
Survey of two-dimensional data on pitching-moment changes near maximum lift caused by deflection of high-lift devices
Report presenting a survey of two-dimensional data on trim changes near maximum lift resulting from deflection of various types of leading-edge and trialing-edge high lift devices. Results regarding pitching-moment coefficients, pitching-moment increments, and maximum lift coefficients are provided.
Aerodynamic characteristics of the NACA 8-H-12 airfoil section at six Reynolds numbers from 1.8 x 10(exp 6) to 11.0 x 10(exp 6)
Report presenting an investigation in the two-dimensional low-turbulence pressure tunnel to determine the aerodynamic characteristics of the NACA 8-H-12 airfoil section at four Reynolds numbers. The section lift, drag, and pitching-moment characteristics are presented for smooth and rough surface conditions. Generally, no unusual scale effects are present for either condition.
Analysis of means of improving the uncontrolled lateral motions of personal airplanes
From Summary: "The purpose of this investigation was to determine whether such airplanes could be made to fly uncontrolled for an indefinite period of time without getting into dangerous attitudes and for a reasonable period of time (one to three minutes) without deviating excessively from their original course. The results of this analysis indicated that the uncontrolled motions of a personal airplane could be made safe as regards spiral tendencies and could be greatly improved as regards maintenance of course without resort to an autopilot."
Effect of airfoil section and tip tanks on the aerodynamic characteristics at high subsonic speeds of an unswept wing of aspect ratio 5.16 and taper ratio 0.61
Report presenting an investigation of the effect of two wing sections and a tip tank on the aerodynamic characteristics of a rigid unswept wing in the high-speed tunnel over a Mach number range of 0.60 to 0.90. Results regarding the effect of original airfoil sections, effect of modifications to Section B, effect of tip tank, and characteristics of the tip tank in the presence of the wing are provided.
No Description Available.