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Size Consist, Chemical Analysis, and Physical Properties of 2-1/2-Inch Subbituminous Slack from the Denver, Colorado Region
Report issued by the U.S. Bureau of Mines on sub-bituminous slack from Denver, Colorado. The characteristics and properties of 2-1/2 inch slack samples are listed. This report includes tables, graphs, maps, illustrations, and photographs.
The Slow Neutron Transmission of Be Metal as Measured by a Neutron Beam Spectrometer in the Energy Region 0.004 eV to 50 eV
Abstract. Slow neutron transmission measurements as a function of the time of flight of the incident neutron have been made for three different thicknesses of Beryllium. The energy region from 0.004 eV to 50 eV was investigated using the Columbia neutron beam spectrometer system. Particular emphasis was placed on the very low energy region (from 0.004 eV tp 0/2 eV or from 0.6 to 5 [length]) where pronounced crystal interference effects were observed. The effective slow neutron cross section (in the unity of X 10(-24)ce(2)atom) for several different energy values were: 6.1 at 0.2 [length], 3.5 at 1.5 [length], 2.3 at 2.5 [length] and 0.6 at 4.6 [length]. The positions of the discontinuities in the cross section agree fairly well with the values obtained from the X-ray measurements.
Slowing Down of Neutrons
From introduction: "The Boltzmann equation expressing conversation of particles in phase space is set up."
Slug Jacket Temperatures
Abstract. A method for calculating jacket temperatures in a region of varying heat transfer coefficients is given Some applications are made for temperatures above a supporting rib.
Slug Temperatures in an Off-Center Annulus
Abstract. Temperatures are measured at two points in an internally heated jacketed slug which is cooled by water flowing in an off-center annulus around the slug. The variations of these temperatures with water velocity, water temperature, power, and the amount the annulus is off center are measured. The temperature near the slug surface which approaches and comes in contact with the water jacket does not increase as much as anticipated. The temperature near the slug surface on the side which is moved away from the water jacket increases nearly as much as on the side approaching the slug. An explanation for this unexpected increase of temperature as on side moving away from the jacket is given.
Small-orifice tubes for minimizing dilution in exhaust-gas samples
Report presenting an investigation to find a means of obtaining undiluted exhaust-gas samples from a Wright R-2600-B aircraft engine equipped with short individual stacks. Preliminary tests to aid in determining the best design, location, and orientation of orifices ranging in size. Results regarding the Briggs & Stratton engine tests and Wright aircraft engine tests are provided.
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.
Smooth-Water Landing Stability and Rough-Water Landing and Take-Off Behavior of a 1/13-Scale Model of the Consolidated Vultee Skate 7 Seaplane, TED No. NACA DE 338
A model of the Consolidated Vultee Aircraft Corporation Skate 7 seaplane was tested in Langley tank no. 2. Presented without discussion in this paper are landing stability in smooth water, maximum normal accelerations occurring during rough-water landings, and take-off behavior in waves.
Solubility and Diffusion Constants for Gases
The solubility constants are presented for He , Kr , Xe , O2 , N2 , and air in H20 . Inter-diffusion constants for gases and the diffusion of gases in water are given.
A Solubility Method of the Determination of Non-Volatile Material in Tetrachloride Charges
Abstract: "This report suggests using methyl acetate extraction of charge material as a means of determining the non-volatile residue. It is shown that the volatile constituents of charge material are all extremely soluble in methyl acetate whereas the non-volatile materials are quite insoluble. Percent NVH on several samples of charge material by this method are reported and discussed."
The Solubility of Helium in Tuballoy
This technical report summarizes the work done in attempting to determine the solubility of helium in tuballoy. In general, the method used has been to allow the tuballoy to stand in contact with helium at one atmosphere presume at a fixed temperature for an extended period, then to pump off the excess helium to a low pressure in as short a time as possible (10-6 mm of Hg or less). The system was then closed off and the pressure increase was measured by a suitable gauge as a function of time. The metal was employed in the form of a powder in early measurements, and later as massive metal. The experimental techniques are described in the report.
The Solubility of Uranyl Oxalate and the Existence of Undissociated Uranyl Oxalate in Solution
Abstract: "The solubility of the solid, UO2C2O4 x rH2O, was measured at various acid and uranyl nitrate concentrations. The results of the measurements prove the existence of the uranyl oxalate complex - UO2C2O4, in solutions containing excess UO2^2."
A Solution of the Direct and Inverse Potential Problems for Arbitrary Cascades of Airfoils
Methods are given of determining the potential flow plast an arbitrary cascade of airfoils and the inverse problem of determining an airfoil having a prescribed velocity distribution in cascade. Results indicated that Cartesian mapping function method may be satisfactorily extended to include cascades. Numerical calculation for computing cascades by Cartesian mapping function method is considerably greater than for single airfoils but much less than hitherto required for cascades.
Solvent Extraction
Report discussing methods and theories of solvent extraction. Factors that influence solvent extraction, such as the distribution coefficient, relative solubility, and physical properties of the solvent, are discussed as well.
The Solvent-Extraction Performance of Redox IC Columns (ANL June 1948 Flowsheet) Using Raschig Ring Packing, and Unirradiated Uranium: Redox Technical Study No. 14
A report which summarizes the performance data obtained from Redox solvent extraction IC Column studies made prior to January 15, 1949 in accordance with conditions of the A.N.L. June 1, 1948, Flowsheet.
The solvent-extraction performance of small scale redox IA columns using Fenske helix packing, ammonium nitrate salting agent, and unirradiated uranium
A report which deals with the Redox IA Column studies made in small-scale columns packed with 3/16-in. Fenske helices and using NH4NO3 salting agent.
Some Aerodynamic Relations for an Airfoil in Oblique Flow
"Some aerodynamic relations are derived which exist between two infinitely long airfoils if one is in a straight flow and the other in oblique flow, and both present the same profile in the direction of flow" (p. 1).
Some Analyses of Systematic Experiments on the Resistance and Porpoising Characteristics of Flying-Boat Hulls
Report discusses the results of analyses and test results of the porpoising characteristics of flying boats. Equations for calculating stability limits with given hull forms under various combinations of loading and aerodynamic conditions and for modifications of the afterbody are provided.
Some Basic Laws of Isotropic Turbulent Flow
An Investigation is made of the diffusion of artificially produced turbulence behind screens or other turbulence producers. The method is based on the author's concept of disturbance moment as a certain theoretically well-founded measure of turbulent disturbances.
Some Cases of Pile Activity Flattening
Radial flattening of activity in the cores of spherical and cylindrical piles is discussed in connection with pile control and power improvement. Partial flattening as a result of k loss from temperature rise is also considered.
Some comparative tests of plain and alclad 24S-T sheet
Report presenting comparative data on the behavior of plain and alclad 24S-T sheet under several types of structural loading. Results indicated that as far as flexural stiffness and resistance to buckling are concerned, the effect of the soft protective coating on alclad shoot is equivalent to a reduction in thickness of about 7 percent. Results regarding the tensile and compressive properties of materials, bending tests on single thicknesses of sheet, column tests on single thicknesses of sheet, bending tests on box beams, and compression tests on stiffened flat-sheet panels are provided.
Some Considerations of the Lateral Stability of High-Speed Aircraft
Note presenting an investigation to determine the effect of variations in the lateral-stability derivatives, wing loading, altitude, and radii of gyration on the combination of directional stability and effective dihedral required for lateral stability at the landing and cruising condition. The results of the investigation showed that an airplane with a high wing loading designed for high-speed and high-altitude flight would be laterally stable if the moments of inertia, the location of the principal longitudinal axis of the airplane, and the value of the damping-in-roll derivative were properly selected.
Some Considerations on an Airfoil in an Oscillating Stream
Report presenting information regarding the velocity potential, lift force, moment, and propulsive force on a two-dimensional airfoil in a stream of periodically varying angle of attack, as well as an application of the theoretical results.
Some Data on the Static Longitudinal Stability and Control of Airplanes: Design of Control Surfaces
In the solution of a number of problems on the stability and controllability of airplanes, there arises the necessity for knowing the characteristics of the tail surfaces of the types in common use today. Of those characteristics, the most important are the effectiveness and hinge moments of the tail surfaces. As has been shown in the present paper, there exists the possibility of determining these characteristics by the formulas obtained with a degree of accuracy sufficient for the purposes of preliminary computation.
Some Effects of Compressibility on the Flow Through Fans and Turbines
"The laws of conservation of mass, momentum, and energy are applied to the compressible flow through a two-dimensional cascade of airfoils. A fundamental relation between the ultimate upstream and downstream flow angles, the inlet Mach number, and the pressure ratio across the cascade is derived. Comparison with the corresponding relation for incompressible flow shows large differences. The fundamental relation reveals two ranges of flow angles and inlet Mach numbers, for which no ideal pressure ratio exists" (p. 123).
Some effects of gutter flame-holder dimensions on combustion-chamber performance of 20-inch ram jet
Report presenting the operational characteristics of a 20-inch ramjet with four different gutter-grid flame holders and a three-gutter flame holder with an adjustable gutter angle. The flame holders were compared on the basis of operating ranges of fuel-air ratio, combustion-chamber-inlet velocity, and the combustion efficiencies obtainable.
Some Effects of Internal Coolants on Knock-Limited and Temperature-Limited Power as Determined in a Single-Cylinder Aircraft Test Engine
Report presenting an investigation to determine the permissible increase in engine power by using various internal coolants from the consideration of fuel knock and cylinder cooling. The internal coolants tested were water, 30-70 methyl alcohol-water volume percent mixture, 70-30 methyl alcohol-water volume percent mixture, methyl alcohol, and 80-20 ethyl alcohol-water volume percent mixture.
Some Effects of Propeller Operation on the Distribution of the Load on the Vertical Tail Surface of a Typical Pursuit Airplane
Report discusses the results of testing on the pressure distribution at several longitudinal sections of the vertical tail surface of the Curtiss P-40K airplane at various angles of attack and angles of yaw and with the propeller removed and propeller operating. Results regarding the chordwise pressure distributions, effects of propeller operation on the spanwise distribution of normal-force coefficient, total normal-force coefficients, and effect of propeller operation on the variation of vertical-tail normal-force coefficients are presented.
Some effects of rainfall on flight of airplanes and on instrument indications
"Several possible effects of heavy rain on the aerodynamic performance of an airplane and of heavy rain and associated atmospheric phenomena on the indications of flight instruments are briefly considered. It is concluded that the effects of heavy rain on the performance of an airplane are not so great as to force the airplane down from moderate altitudes. Serious malfunctioning of the air-speed indicator may occur, however, as a result of flooding of the pitot-static head and subsequent accumulation of water in the air-speed pressure line" (p. 1).
Some Effects of Reynolds and Mach Numbers on the Lift of an NACA 0012 Rectangular Wing in the NACA 19-Foot Pressure Tunnel
Bulletin presenting a short investigation in the 19-foot pressure tunnel to determine the aerodynamic characteristics of a rectangular wing model constructed to NACA 0012 airfoil sections. Tests were run with the air in the tunnel at 2 different pressures: atmospheric and 35 pounds per square inch absolute.
Some Effects of Stator Cone Angle and Blade-Tip Leakage on 40 Percent Reaction Turbine Having Rotor-Blade Caps
Memorandum presenting an investigation of the effects of stator cone angle and tip leakage on turbine performance. A single-stage turbine with 40-percent reaction was operated with two stators and two stationary shrouds. The turbine was operated at an entrance temperature of 660 degrees R with total-pressure ratios from 1.25 to 3.70 and equivalent mean blade speeds from 166 to 655 feet per second.
Some Essential Safety Factors in Tunneling
From Purpose of Report: "This paper is based partly upon the authors' observations and partly upon studies of tunnel driving; these cover essentially all types of tunnels in various parts of the United States during the past 25 years."
Some Flight Measurements of Pressure-Distribution and Boundary-Layer Characteristics in the Presence of Shock
Memorandum presenting some pressure-distribution and boundary-layer measurements made in flight in the presence of shock on two modifications of the local contour of the wings of a high-speed airplane. Results regarding the pressure distribution, boundary-layer surveys, and effects on test airplane are provided.
Some Flight Measurements on Pressure Distribution During Tail Buffeting
Report presenting pressure-distribution measurements obtained from the horizontal tail surfaces of the Curtiss P-40K airplane during low-speed pull-ups to abrupt stall in which tail buffeting was experienced. The chordwise load distributions during buffeting are similar to those experienced during angle-of-attack changes. The location of the stall and frequency of stall disturbances are also described.
Some fundamental similarities between boundary-layer flow at transonic and low speeds
Report presenting an analysis of low-speed boundary-layer flow over airfoils at moderate angles of attack and Reynolds numbers of several million. Methods are developed for estimating the growth of the boundary layer in the regions of laminar separation and transition.
Some Haulage and Hoisting Hazards in Western Mines
Report issued by the U.S. Bureau of Mines discussing safety hazards in western mines. Mine hoisting and haulage accidents are presented. Accident prevention is also discussed. This report includes tables.
Some Investigations of the General Instability of Stiffened Metal Cylinders 1: Review of Theory and Bibliography
This is the first of a series of reports covering an investigation of the general instability problem. This report consists of earlier reports along with the results of the current studies in the form of a series of reports covering the entire investigation.
Some Investigations of the General Instability of Stiffened Metal Cylinders 2: Preliminary Tests of Wire-Braced Specimens and Theoretical Studies
"This is the second of a series of reports covering an investigation of the general instability problem by the California Institute of Technology. The first five reports of this series cover investigations of the general instability problem under the loading conditions of pure bending and were prepared under the sponsorship of the Civil Aeronautics Administration. The succeeding reports of this series cover the work done on other loading conditions under the sponsorship of the National Advisory Committee for Aeronautics" (p. 1).
Some Investigations of the General Instability of Stiffened Metal Cylinders 3: Continuation of Tests of Wire-Braced Specimens and Preliminary Tests of Sheet-Covered Specimens
"This is the third of a series of reports covering an investigation of the general instability problem by the California Institute of Technology. The first five reports of this series cover investigations of the general instability problem under the loading conditions of pure bending and were prepared under the sponsorship of the Civil Aeronautics Administration. The succeeding reports of this series cover the work done on other loading conditions under the sponsorship of the National Advisory Committee for Aeronautics" (p. 1).
Some Investigations of the General Instability of Stiffened Metal Cylinders 4: Continuation of Tests of Sheet-Covered Specimens and Studies of the Buckling Phenomena of Unstiffened Circular Cylinders
"This is the fourth of a series of reports covering an investigation of the general instability problem by the California Institute of Technology. The succeeding reports of this series cover the work done on other loading conditions under the sponsorship of the National Advisory Committee for Aeronautics. This report is to deal primarily with the continuation of tests of sheet-covered specimens and studies of the buckling phenomena of unstiffened circular cylinders" (p. 1).
Some Investigations of the General Instability of Stiffened Metal Cylinders 5: Stiffened Metal Cylinders Subjected to Pure Bending
This report summarizes the work that has been carried on in the experimental investigation of the problem of general instability of stiffened metal cylinders subjected to pure bending at the C.I.T. This part of the investigation included tests of 46 sheet-covered specimens. The most significant result was the determination of a new design parameter for the case of a stiffened metal cylinder subjected to pure bending.
Some Investigations of the General Instability of Stiffened Metal Cylinders 6: Stiffened Metal Cylinders Subjected to Combined Bending and Transverse Shear
"This is the sixth of a series of reports covering an investigation of the general instability problem by the California Institute of Technology. This report and the succeeding reports of this series cover the work done on other loading conditions under the sponsorship of the National Advisory Committee for Aeronautics. This report summarizes the work that has been carried on in the experimental investigation of the problem of general instability of stiffened metal cylinders subjected to combined bending and transverse shear at the C.I.T." (p. 1).
Some Investigations of the General Instability of Stiffened Metal Cylinders 7: Stiffened Metal Cylinders Subjected to Combined Bending and Torsion
"This report summarizes the work that has been carried on in the experimental investigation of the problem of the general instability of stiffened metal cylinders subjected to combined bending and torsion at the C.I.T. This part of the investigation included tests on 26 sheet-covered specimens. An interaction curve for the case of combined bending and torsion is presented. The results of tests of 17 specimens subjected to pure torsion are also given" (p. 1).
Some Investigations of the General Instability of Stiffened Metal Cylinders 8: Stiffened Metal Cylinders Subjected to Pure Torsion
"An experimental investigation of the general instability of reinforced thin-walled metal cylinders was carried out at the California Institute of Technology. The basic parameters involved were the spacing and sectional properties of the stiffening elements, the wall thickness, and the diameter of the cylinder. An analysis of the experimental data led to a suitable parameter for estimating the general instability stress of reinforced metal cylinders when subjected to pure torsion loading" (p. 1).
Some Lift and Drag Measurements of a Representative Bomber Nacelle on a Low-Drag Wing
Report presenting testing of a representative bomber nacelle on a low-drag wing in the NACA two-dimensional tunnel. The adverse or interference effects of the nacelle on the low-drag wing were small.
Some Lift and Drag Measurements of a Representative Bomber Nacelle on a Low-Drag Wing 2
"Tests of a second representative bomber nacelle on a low-drag wing at a large value of the Reynolds number were made in the NACA two-dimensional low-turbulence pressure tunnel. Results show the drag and interference of the nacelle on the low-drag wing to be small" (p. 1).
Some Lift and Drag Measurements of Two Configurations of a Nacelle and Oil-Cooler Scoop for the Hughes-Kaiser Cargo Airplane
Report presenting tests in the two-dimensional low-turbulence tunnel to determine the drag characteristics of two configurations of a 0.0476-scale nacelle and oil-cooler scoop for the Hughes-Kaiser cargo airplane. The nacelles were found to have a slightly favorable effect on the maximum lift coefficient.
Some New Problems on Shells and Thin Structures
"Cylindrical shells of arbitrary section, reinforced by longitudinal and transverse members (stringers and ribs) are considered by us, for a sufficiently close spacing of the ribs, as in our previously published papers (references 1 end 2), as thin-walled orthotropic spatial systems at the cross-sections of which only axial (normal and shearing) forces can arise. The longitudinal bending and twisting moments, due to their weak effect on the stress state of the shell, are taken equal to zero. Along the longitudinal sections of the shell there may arise transverse forces in addition to the normal ~d shearing forces" (p. 1).
Some Notes on the Determination of the Stick-Fixed Neutral Point From Wind-Tunnel Data
"Two methods are presented for determining the horizontal location of the stick-fixed neutral point from wind-tunnel data. One method involves the solution of a mathematical equation; whereas the other method is a graphical solution for the same mathematical equation. The combined horizontal and vertical variation of the neutral point completely describes the stick-fixed longitudinal stability of airplanes that have large allowable center-of-gravity shifts" (p. 1).
Some Notes on the Determination of the Stick-Free Neutral Point from Wind-Tunnel Data
"Two graphical methods are presented for determining the stick-free neutral point, and they are extensions of the methods commonly used to determine the stick-free neutral point. A mathematical formula for computing the stick-free neutral point is also given. These methods may be applied to determine approximately the increase in tail size necessary to shift the neutral point (stick fixed or free) to any desired location on an airplane having inadequate longitudinal stability" (p. 1).
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