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190-C pump capacity

Description: The purpose of this document is to update 190-C pump capacity information previous released in HW-52449{sup 1} and HW-58580{sup 2}. Improvements in motor cooling has resulted in raising the previous 3500 HP limit to 3660 HP{sup 3} thus increasing total pumping capacity.
Date: June 22, 1959
Creator: Watson, D. F.
Partner: UNT Libraries Government Documents Department
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200 area weekly report

Description: No Description Available.
Date: December 22, 1955
Partner: UNT Libraries Government Documents Department
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Adiabatic Injection

Description: From introduction comments: The present analysis is intended to examine the relations for "adiabatic" injection in general from a different point of view.
Date: September 22, 1955
Creator: Linlor, William I., 1915-
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of Four Bodies of Revolution Showing Some Effects of Afterbody Shape and Fineness Ratio at Free-Stream Mach Numbers From 1.50 to 1.99

Description: The effects of fineness ratio (14.2 and 12.2) and boattailing on aerodynamic characteristics of four bodies of revolution at Mach numbers from 1.50 to 1.99 within a range of angles of attack from 0 degrees 10 degrees at an approximate Reynolds number of 35x10(superscript)6 based on body length were investigated. A comparison of experimental data with available theory is included. At zero angle of attack, fineness ratio has no appreciable effect on model characteristics while boattailing and boattail convergence significantly affect fore drag and base drag.
Date: May 22, 1951
Creator: Cohen, Robert J.
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of two 25-percent-area trailing-edge flaps on an aspect ratio 2 triangular wing at subsonic and supersonic speeds

Description: Report presenting the results of an investigation of flap-type controls on a low-aspect-ratio triangular wing using NACA 0005-63 sections for a constant-chord and a constant-percent-chord control surface. Two flap profiles were investigated: one with a true contour and the other with a blunt trailing edge. Results regarding lift, drag, pitching moment, hinge moment, and rolling moments were obtained for several Mach numbers, a constant Reynolds number, and a range of angles of attack.
Date: July 22, 1952
Creator: Boyd, John W.
Partner: UNT Libraries Government Documents Department
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Aileron and Elevator Hinge Moments of the Bell X-1 Airplane Measured in Transonic Flight

Description: "During the flight investigation of the X-1 airplane the hinge moments of the elevator and aileron control surfaces have been measured over a Mach number range extending to above 1.0. The results of these measurements are presented in this paper" (p. 2).
Date: June 22, 1953
Creator: Drake, Hubert M. & McKay, John B.
Partner: UNT Libraries Government Documents Department
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An Analysis of Pressure Studies and Experimental and Theoretical Downwash and Sidewash Behind Five Pointed-Tip Wings at Supersonic Speeds

Description: "Flow-angle and pressure surveys behind five, thin, pointed-tip wings of varying plan form have been made at Mach numbers 1.62 and 2.41. Schlieren studies at a Mach number 1.93 for the same five plan-form wings were made to illustrate the behavior of the vortex sheet. The surveys were conducted at 1.5, 3, and 4 root chords behind three triangular wings of 50 degree, 63 degree, and 72 degree leading-edge sweep angle, and behind the 50 degree triangular wing reversed" (p. 1067).
Date: January 22, 1954
Creator: Boatright, William B.
Partner: UNT Libraries Government Documents Department
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An analysis of the tracking performances of two straight-wing and two swept-wing fighter airplanes with fixed sights in a standardized test maneuver

Description: From Introduction: "This report presents the initial study, the tracking performance of typical fighter airplanes with fixed gunsights. The types of airplanes tested afford two comparisons of particular interest: that between typical World War II and currently operational fighters of greatly increased speed and altitude, and that between conventional and irreversabile power-boosted controls with artificial feel, both installed on the same airframe."
Date: October 22, 1953
Creator: Rathert, George A., Jr.; Gadeberg, Burnett L. & Ziff, Howard L.
Partner: UNT Libraries Government Documents Department
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Analytical and experimental investigation of a temperature-schedule acceleration control for a turbojet engine

Description: From Introduction: "This report investigates some of the problems involved in scheduling the tailpipe temperature to avoid stall during acceleration. The object of this report is to investigate the dynamics of a closed-loop acceleration control that follows a schedule of tailpipe temperature with rotor speed."
Date: June 22, 1958
Creator: Heppler, Herbert; Stiglic, Paul M. & Novik, David
Partner: UNT Libraries Government Documents Department
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Application of Reactor Safeguard Committee Formula

Description: The Reactor Safeguard Committee formula for the allowable minimum distance between a reactor and the public domain is expressed as: r = 0.01{radical}P, where r = radius from reactor in miles, and P = reactor power level in kilowatts. The six plates in this report illustrates the application of this formula for Hanford Works, both for individual reactors and all reactors in an area.
Date: April 22, 1952
Creator: Smith, J. M.
Partner: UNT Libraries Government Documents Department
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Axially Symmetric Shapes With Minimum Wave Drag

Description: "The external wave drag of bodies of revolution moving at supersonic speeds can be expressed either in terms of the geometry of the body, or in terms of the body-simulating axial source distribution. For purposes of deriving optimum bodies under various given conditions, it is found that the second of the methods mentioned is the more tractable. By use of a quasi-cylindrical theory, that is, the boundary conditions are applied on the surface of a cylinder rather than on the body itself, the variational problems of the optimum bodies having prescribed volume or caliber are solved" (p. 131).
Date: November 22, 1954
Creator: Heaslet, Max A. & Fuller, Franklyn B.
Partner: UNT Libraries Government Documents Department
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Beryllium-oxide : [bibliography]

Description: "This is a bibliography of journal articles relating to beryllium oxide. Sources consulted include; Chemical Abstracts, 1951-1955; Physics Abstracts, 1951-1955; Industrial Arts Index, 1955-Jan, 1957; and the library card catalog. Starred articles are available in the library.
Date: March 22, 1957
Creator: Cason, Maggie
Partner: UNT Libraries Government Documents Department
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Boiling limits

Description: Uncontrolled boiling of the water in a process tube might result in serious damage to a pile. Consequently, it is desirable to maintain header pressure generally sufficient to sweep out any steam which might be formed. Since the header pressure required to remove the steam depends upon the power output of the tube, the power level of a tube or pile is limited by the pressure available. In the past, tube power limitations have been specified and interpretations thereof. Recently a through study, both theoratical and experimental, has been made to determine the validity of these limitations. The purpose of this report is to present the results of the study must make recommendations for future operations. The limits presented herein are based on tube power levels.
Date: January 22, 1952
Creator: Vanderwater, R. G.
Partner: UNT Libraries Government Documents Department
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Bremsstrahlung Theories Since 1945 : [Bibliography]

Description: Report detailing various Bremsstrahlung theories since 1945. Citations for different theories are included.
Date: December 22, 1958
Creator: Maynard, Glenn R. & Lane, Zanier
Partner: UNT Libraries Government Documents Department
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Calculated Effect of Uranium Distribution on Reflector Control Effectiveness for a Water-Moderated Power Reactor

Description: Report presenting two-group theory calculations to determine the effect of nonuniform uranium loading as compared to uniform loading on the reflector control effectiveness attainable in a large thermal reactor usable for aircraft power application. Results regarding reactivities and investments, uranium distributions, and power distributions are provided.
Date: January 22, 1954
Creator: Fox, Thomas A. & Valerino, Michael F.
Partner: UNT Libraries Government Documents Department
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Calculation of Stagewise Contacting Systems

Description: From abstract: General expressions relating product stream compositions to the operating conditions of countercurrent stagewise extraction columns are derived by an inductive method, and the conversion of the general equations to ones involving the particular case of constant extraction factor is demonstrated. For comparison, the derivation of simple column equations by the use of finite difference equations is included.
Date: May 22, 1953
Creator: Bloom, J. L. & Auer, P. L.
Partner: UNT Libraries Government Documents Department
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Calculations of Laminar Heat Transfer Around Cylinders of Arbitrary Cross Section and Transpiration-Cooled Walls With Application to Turbine Blade Cooling

Description: "An approximate method for the development of flow and thermal boundary layers in the laminar region on cylinders with arbitrary cross section and transpiration-cooled walls is obtained by the use of Karman's integrated momentum equation and an analogous heat-flow equation. Incompressible flow with constant property values throughout the boundary layer is assumed. The velocity and temperature profiles within the boundary layer are approximated by expressions composed of trigonometric functions" (p. 339).
Date: June 22, 1951
Creator: Eckert, E. R. G. & Livingood, J. N. B.
Partner: UNT Libraries Government Documents Department
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The change with mass-flow ratio of the cowl pressure drag of normal-shock inlets at supersonic speeds

Description: Report presenting pressure-drag coefficients and the changes in these coefficients with mass-flow ratio, which have been measured in tests of six open-nose conical cowls at an angle of attack of 0 degrees. Testing occurred in the Ames 8 by 8-inch supersonic wind tunnel at a range of Mach numbers. Results regarding pressure distributions, change in cowl pressure drag with mass-flow ratio, cowl pressure drag at a given mass-flow ratio, and changes in cowl pressure drag with mass-flow ratio as a function of Mach number are provided.
Date: June 22, 1956
Creator: Davis, Wallace F. & Gowen, Forrest E.
Partner: UNT Libraries Government Documents Department
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Chemical Processing Department Monthly Report: July 1957

Description: This report, for July 1957 from the Chemical Processing Department at HAPO, discusses the following; Production operation; Purex and Redox operation; Finished products operation; maintenance; Financial operations; facilities engineering; research; and employee relations.
Date: August 22, 1957
Creator: Hanford Atomic Products Operation. Chemical Processing Department.
Partner: UNT Libraries Government Documents Department
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