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Description: A preliminary hybrid 1A flowsheet in which the extraction section operates substantially acid while the scrub section is acid deficient is presented. The effects of added nitric acid on the performance of the acid deficient 1A flowsheet are considered, and the need for control of the entering stream acidities in such flowsheets is evaluated. Data on batch-countercurrent decontamination and plutonium recovery are included. (J.R.D.)
Date: January 1, 1950
Creator: Coplan, B.V.; Davidson, J.K.; Hass, W.O. & Zebroski, E.L.

Aerodynamic characteristics of damping screens

Description: From Summary: "The experimental investigation of damping screens described herein was undertaken primarily to test theories of the effects of damping screens and to obtain information on the performance of screens in oblique flow. The characteristics investigated include the damping of longitudinal and lateral components of turbulence, the effect of screens on scale, the conditions for the production of turbulence and eddies by screens, and the damping of spatial variations of mean speed."
Date: January 1950
Creator: Schubauer, G B; Spangenberg, W G & Klebanoff, P S

The aerodynamic forces on slender plane- and cruciform-wing and body combinations

Description: From Introduction: "Since these results were not applicable to the present problem, a theoretical analysis of the aerodynamic properties of slender wing-body combinations was undertaken. The results of this investigation were first reported in reference 5 and were later extended in reference 6 to include cruciform-wing and body combinations. The present report summarizes and extends the theory and results previously presented in these references."
Date: 1950?~
Creator: Spreiter, John R

Analysis of spanwise temperature distribution in three types of air-cooled turbine blade

Description: Methods for computing spanwise blade-temperature distributions are derived for air-cooled hollow blades, air-cooled hollow blades with inserts, and air-cooled blades containing internal cooling fins. Individual and combined effects on spanwise blade-temperature distributions of cooling-air and radial heat conduction are determined. In general, the effects of radiation and radial heat conduction were found to be small and the omission of these variations permitted the construction of nondimensional charts for use in determining spanwise temperature distribution through air-cooled turbine blades. An approximate method for determining the allowable stress-limited blade-temperature distribution is included, with brief accounts of a method for determining the maximum allowable effective gas temperatures and the cooling-air requirements. Numerical examples that illustrate the use of the various temperature-distribution equations and of the nondimensional charts are also included.
Date: January 1, 1950
Creator: Livingood, John N B & Brown, W Byron

The application of Green's theorem to the solution of boundary-value problems in linearized supersonic wing theory

Description: Following the introduction of the linearized partial differential equation for nonsteady three-dimensional compressible flow, general methods of solution are given for the two and three-dimensional steady-state and two-dimensional unsteady-state equations. It is also pointed out that, in the absence of thickness effects, linear theory yields solutions consistent with the assumptions made when applied to lifting-surface problems for swept-back plan forms at sonic speeds. The solutions of the particular equations are determined in all cases by means of Green's theorem, and thus depend on the use of Green's equivalent layer of sources, sinks, and doublets. Improper integrals in the supersonic theory are treated by means of Hadamard's "finite part" technique.
Date: January 1, 1950
Creator: Heaslet, Max A & Lomax, Harvard

Application of radial-equilibrium condition to axial-flow compressor and turbine design

Description: Basic general equations governing the three-dimensional compressible flow of gas through a compressor or turbine are given in terms of total enthalpy, entropy, and velocity components of the gas. Two methods of solution are obtained for the simplified, steady axially symmetric flow; one involves the use of a number of successive planes normal to the axis of the machine and short distances apart, and the other involves only three stations for a stage in which an appropriate radial-flow path is used. Methods of calculation for the limiting cases of zero and infinite blade aspect ratios and an approximate method of calculation for finite blade aspect ratio are also given. In these methods, the blade loading and the shape of the annular passage wall may be arbitrarily specified.
Date: January 1, 1950
Creator: Wu, Chung-Hua & Wolfenstein, Lincoln

Bibliography of Pressure Hydrogenation (In Three Parts): [Part] 1. Review and Compilation of the Literature on Pressure Hydrogenation of Liquid and Solid Carbonaceous Materials

Description: From Introduction: This review contains abstracts of the technical literature and patents dealing material application of the Bergius and related processes for the hydrogenation, under greater than atmospheric pressures, of liquid and solid carbonaceous materials such as coal, lignite, their distillation and extraction products, pitches and tars, and petroleum and its distillation residues."
Date: 1950
Creator: Wiley, J. L. & Anderson, H. C.

Blockage corrections for three-dimensional-flow closed-throat wind tunnels, with consideration of the effect of compressibility

Description: Theoretical blockage corrections are presented for a body of revolution and for a three-dimensional unswept wing in a circular or rectangular wind tunnel. The theory takes account of the effects of the wake and of the compressibility of the fluid, and is based on the assumption that the dimensions of the model are small in comparison with those of the tunnel throat. Formulas are given for correcting a number of the quantities, such as dynamic pressure and Mach number, measured in wing-tunnel tests. The report presents a summary and unification of the existing literature on the subject.
Date: January 1, 1950
Creator: Herriot, John G

Buried Valley of the Susquehanna River: Anthracite Region of Pennsylvania

Description: Report issued by the U.S. Bureau of Mines regarding a buried valley area (a deposit of clay, sand, and gravel) around the Susquehanna River in the anthracite region of Pennsylvania, near the city of Wilkes-Barre. According the the introduction, "The purpose of this report is to furnish data on the buried valley of the Susquehanna River that will be useful in solving the anthracite mine-water problem" and "This report (a) discusses the physical characteristics and the influence of the buried valley of the Susquehanna River on anthracite mining in the Wyoming Valley area of the Northern field, (b) correlates pertinent data relating to the buried valley, (c) presents accurate contour maps showing the position of the top of solid rock underlying the water-soaked valley-fill deposits in the buried valley, and (d) presents cross sections at regular intervals across the buried valley showing the irregularities in trend and bottom as well as the thickness, configuration, and nature of the materials composing the water-bearing valley-fill deposits" (p. 3).
Date: 1950
Creator: Ash, S. H. (Simon Harry), b. 1889

The calculation of downwash behind supersonic wings with an application to triangular plan forms

Description: A method is developed consistent with the assumptions of small perturbation theory which provides a means of determining the downwash behind a wing in supersonic flow for a known load distribution. The analysis is based upon the use of supersonic doublets which are distributed over the plan form and wake of the wing in a manner determined from the wing loading. The equivalence in subsonic and supersonic flow of the downwash at infinity corresponding to a given load distribution is proved.
Date: January 1, 1950
Creator: Lomax, Harvard; Sluder, Loma & Heaslet, Max A

Calculation of the aerodynamic loading of swept and unswept flexible wings of arbitrary stiffness

Description: A method is presented for calculating the aerodynamic loading, the divergence speed, and certain stability derivatives of swept and unswept wings and tail surfaces of arbitrary stiffness. Provision is made for using either stiffness curves and root rotation constants or structural influence coefficients in the analysis. Computing forms, tables of numerical constants required in the analysis, and an illustrative example are included to facilitate calculations by means of the method.
Date: January 1, 1950
Creator: Diederich, Franklin W

Calibration of Instruments for Measuring Wind Velocity and Direction

Description: Signal Corps wind equipment AN/GMQ-1 consisting of a 3-cup anemometer and wind vane was calibrated for wind velocities from 1 to 200 miles per hour. Cup-shaft failure prevented calibration at higher wind velocities. The action of the wind vane was checked and found to have very poor directional accuracy below a velocity of 8 miles per hour. After shaft failure was reported to the Signal Corps, the cup rotors were redesigned by strengthening the shafts for better operation at high velocities. The anemometer with the redesigned cup rotors was recalibrated, but cup-shaft failure occurred again at a wind velocity of approximately 220 miles per hour. In the course of this calibration two standard generators were checked for signal output variation, and a wind-speed meter was calibrated for use with each of the redesigned cup rotors. The variation of pressure coefficient with air-flow direction at four orifices on a disk-shaped pitot head was obtained for wind velocities of 37.79 53.6, and 98.9 miles per hour. A pitot-static tube mounted in the nose of a vane was calibrated up to a dynamic pressure of 155 pounds per square foot, or approximately 256 miles per hour,.
Date: January 1, 1950
Creator: Vogler, Raymond D. & Pilny, Miroslav J.

Carbonizing Properties: Pocahontas Number 6, Davy Sewell, and Fire Creek Coals from West Virginia and Upper and Lower Kittanning and Upper and Lower Freeport Coals from Pennsylvania

Description: From Forward: "The value of this survey of the carbonizing properties of American coals by a standard method lies in the comparability of the results on different coals. It must recognized that no standard laboratory method of carbonization, even on a large unit, can yield results that exactly duplicate those obtained in ovens and retorts. The commercial results vary with the type of oven or retort. Allowance must be made for such differences in interpreting the BM-AGA test results in terms of commercial plants."
Date: 1950
Creator: Davis, J. D.; Reynolds, D. A.; Brewer, R. E.; Wolfson, D. E.; Naugle, B. W. & Birge, G. W.

Carbonizing Properties: West Virginia Coals from the Eagle, Number 2 Gas, Pocahontas Number 3, and Pocahontas Number 4 Beds

Description: From Introduction and Summary: "This paper gives results of an investigation of the composition and carbonizing properties of coals from Pocahontas No.3 bed, Lake superior No.4 mine, McDowell County, W.Va.; Eagle bed, Cannelton No.3 mine, Fayette County, W.Va; and No.2 Gas bed, Cannelton No.100 mine, Kanawha County, W. Va."
Date: 1950
Creator: Davis, J. D.; Reynolds, D. A.; Brewer, R. E.; Ode, W. H.; Naugle, B. W.; Wolfson, D. E. et al.

Characterization of Tar Acids from Coal-Hydrogenation Oils

Description: From Introduction: "The purpose of this investigation was to separate and identify as many of the principal phenolic compounds produced by the mild hydrogenation of Pittsburgh-bed (Bruceton) coal as possible and to determine with the greatest possible accuracy the proportions in which they are present."
Date: 1950
Creator: Woolfolk, E. O.; Golumbic, C.; Friedel, R. A.; Orchin, Milton & Storch, H. H.

Comparative drag measurements at transonic speeds of rectangular sweptback NACA 65-009 airfoils mounted on a freely falling body

Description: Directly comparable drag measurements have been made of an airfoil with a conventional rectangular plan form and an airfoil with a sweptback plan form mounted on freely falling bodies. Both airfoils had NACA 65-009 sections and were identical in span, frontal area, and chord perpendicular to the leading edge. The sweptback plan form incorporated a sweepback angle of 45 degrees. The data obtained have been used to establish the relation between the airfoil drag coefficients and the free-stream Mach number over a range of Mach numbers from 0.90 to 1.27. The results of the measurements indicate that the drag of the sweptback plan form is less than 0.3 that of the rectangular plan form at a Mach number of 1.00 and is less than 0.4 that at a Mach number of 1.20.
Date: January 1, 1950
Creator: Mathews, Charles W & Thompson, Jim Rogers

Comparison of BM-AGA and Slot-Oven Experimental Methods of Carbonization, with Results for Eleven Coals

Description: From Introduction and Summary: "However, with the completion and satisfactory performance of an experimental vertical slot oven of 500-pound capacity at the University of Illinois Geological Survey Laboratory, the opportunity to directly compare BM-AGA coke with coke made by two-sided heating became available and the necessary test apparatus was installed. This report compares the results obtained by the two methods."
Date: 1950
Creator: Davis, J. D.; Reynolds, D. A.; Wolfson, D. E. & Birge, G. W.

Contributions to the Data on Theoretical Metallurgy: [Part] 11. Entropies of Inorganic Substances: Revision (1948) of Data and Methods of Calculation

Description: From Introduction: "The present bulletin also contains all the pertinent explanatory matter that appeared in its predecessors. Thus, it retains the same dual purpose of assembling the available values of the entropies at 298.16 degrees K of the elements and inorganic compounds and giving enough explanation of methods of calculating entropies to make the results comprehensible."
Date: 1950
Creator: Kelley, K. K.

Critical stress of ring-stiffened cylinders in torsion

Description: A chart in terms of nondimensional parameters is presented for the theoretical critical stress in torsion of simply supported cylinders stiffened by identical equally spaced rings of zero torsional stiffness. The results are obtained by solving the equation of equilibrium by means of the Galerkin method. Comparison of the theoretical results with experimental results indicates that ring-stiffened cylinders buckle, on the average, at a buckling stress about 15 percent below the theoretical buckling stress. (author).
Date: January 1, 1950
Creator: Stein, Manuel; Snaders, J Lyell, Jr & Crate, Harold

Determination of plate compressive strengths at elevated temperatures

Description: The results of local-instability tests of h-section plate assemblies and compressive stress-strain tests of extruded 75s-t6 aluminum alloy, obtained to determine flat-plate compressive strength under stabilized elevated temperature conditions, are given for temperatures up to 600 degrees F. The results show that methods available for calculating the critical compressive stress at room temperature can also be used at elevated temperatures if the applicable compressive stress-strain curve for the material is given.
Date: January 1, 1950
Creator: Heimerl, George J & Roberts, William M