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100 Areas technical activities report -- Engineering, May, 1950

Description: This report discusses progress made by the Physical Chemistry Group and Pile Engineering Groups. Topics covered are as follows: x-ray studies--tube bore mining; physical expansion of capsule exposures; special capsule exposures; pile annealing; thermal conductivity and pile annealing; total stored energy; Sykes stored energy method; slug corrosion rate; effect of pressure drop on slug corrosion; exposure of P-10 fuel slugs; slug corrosion weight loss variables; vertical safety rod thimble corro… more
Date: June 28, 1950
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100-B Area flow analysis

Description: Results of experimental programs indicate that it might be desirable in the future to modify the existing reactors by replacing the aluminum process tubes with tubes made of a zirconium alloy. The zirconium tubes would be more corrosion resistant than the aluminum ones and would also be stronger at higher temperatures. These new tubes would have the same outer diameter as the present tubes (for ease of handling and in order to provide adequate graphite cooling) but would have a thinner wall (si… more
Date: June 1, 1957
Creator: Bainard, W. D.
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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.
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450-Mev/C K$sup -$ and /Anti p/ Beams at the Northwest Target Area of the Bevatron Separated by the Coaxial Velocity Spectrometer

Description: Enriched beams of 450 Mev/c K/sup -/ mesons and antiprotons have been produced by separation with the coaxial static electromagnetic velocity spectrometer. Characteristics of the final separated beams as observed in the 15- inch hydrogen bubble chamber are given together with a detailed description of the beam optics and apparatas. (auth)
Date: June 1, 1958
Creator: Horwitz, N.; Murray, J. J.; Ross, R. R. & Tripp, R. D.
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1951 at Hanford Works

Description: This document provides a discussion of activities at the Hanford Works during 1951.
Date: June 30, 1952
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The Absorption and Translocation of Several Fission Elements by Russian Thistle

Description: Abstract: An investigation was conducted to determine the absorption and translocation of fission products by Russian thistle from a localized spot of contaminated soil. The amount and identity of the radioactive elements absorbed and translocated by the Russian thistle is given along with the location of these elements in the plants. Beta radioactivity to the amounts of 10 microcuries per gram caused no visible effects on the growth habits of sectioned material are included.
Date: June 8, 1950
Creator: Selders, A. A.
open access

The Absorption Spectra of Suspensions of Living Micro-Organism

Description: The following document describes how to determine the measurements of the optical density or absorption spectra of suspensions of micro-organisms.
Date: June 1954
Creator: Shibata, Kazuo, 1918-; Benson, Andrew A. & Calvin, Melvin, 1911-1997
open access

Acenaphthene solvents for use in Building 313 Frost Test operation

Description: Acenaphtheno is a low-melting organic compound, C{sub 10}H{sub 6}(CH{sub 2}){sub 2}, used as a temperature indicating coating for slugs tested in the Frost Test induction coil. In preparation for this test, slugs are coated by spraying a 12 to 24 per cent by weight solution of acenaphthene in a high vapor pressure solvent on the rotating slug. The solvent evaporate leaving a thin, adherent coating of acenaphthene. This process is completely described in reference 1. To be entirely satisfactory … more
Date: June 26, 1951
Creator: Kratzer, W. K.
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Acoustical Treatment for the NACA 8- by 6-Foot Supersonic Propulsion Wind Tunnel

Description: "This report presents results of a research and engineering program performed during the first half of 1950 that resulted in an acoustical treatment for the 8- by 6-foot supersonic wind tunnel at the Lewis Flight Propulsion Laboratory" (p. 1).
Date: June 1955
Creator: Beranek, Leo L.; Labate, Samuel & Ingard, Uno
open access

The Action of Oxygen on Activated Charcoal

Description: The following report provides information conducted with the purpose of ascertaining the effect of oxygen on activated charcoal at approximately one atmosphere by measuring the amount of CO2 formed over a known length of time.
Date: June 29, 1951
Creator: Bigelow, J. E.; Belaga, M. W. & Mulvihill, R. J.
open access

Aerodynamic characteristics at high and low subsonic Mach numbers of four NACA 6-series airfoil sections at angles of attack from -2 to 31 degrees

Description: From Introduction: "The airfoil sections tested, which differ only in thickness ratio, were the NACA 64-006, 64-008, 64-010, and 641-012. Lift, drag, and pitching-moment data were obtained for Mach numbers of 0.3 to that for tunnel choke at angles of attack of -2^o to 31^o. The results of this investigation are reported herein."
Date: June 5, 1953
Creator: Wilson, Homer B., Jr. & Horton, Elmer A.
open access

Aerodynamic Characteristics of a 6-Percent-Thick Symmetrical Circular-Arc Airfoil Having a 30-Percent-Chord Trailing-Edge Flap at a Mach Number of 6.9

Description: Memorandum presenting an investigation of the flow characteristics over a 6-percent-thick symmetrical circular-arc airfoil section with a 30-percent-chord trailing-edge flap at a Mach number of 6.90 and a Reynolds number of 1.65 x 10(sub 6). The model was tested over an angle-of-attack range of 0 to 16 degrees and a flap-deflection range of -16 degrees to 16 degrees. Results regarding pressure results and aerodynamic characteristics are provided.
Date: June 5, 1956
Creator: Ridyard, Herbert W. & Fetterman, David E., Jr.
open access

Aerodynamic Characteristics of a 45 Degree Swept Wing Fighter Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53

Description: Report discussing tests to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane and to determine the loads on attached stores and detached missiles. An investigation into aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications of aerodynamic characteristics was also carried out at various Mach numbers. Results are presented, but caution is provided in regards to extrapolating results from the model onto a full-scale … more
Date: June 24, 1958
Creator: Oehman, Waldo I. & Turner, Kenneth L.
open access

Aerodynamic Characteristics of a 45 Degree Swept-Wing Fighter-Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53

Description: Memorandum presenting an investigation in the Unitary Plan wind tunnel to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane, and to determine the loads on attached stores and detached missiles in the presence of the model. Results also included a determination of aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications on model aerodynamic characteristics. The results are presented with minimum analysis.
Date: June 24, 1958
Creator: Oehman, Waldo I. & Turner, Kenneth L.
open access

Aerodynamic Characteristics of a Refined Deep-Step Planing-Tail Flying-Boat Hull with Various Forebody and Afterbody Shapes

Description: From Introduction: "The results of one phase of this investigation, presented in reference 1, have indicated that hull drag can be reduced without causing large changes in aerodynamic stability and hydrodynamic performance by the use of high length-beam ratios. Another phase of the investigation, reference 2, indicated that hulls of the deep-step planning-tail type have much lower air drag than the conventional type of hull and about the same aerodynamic stability; tank tests, reference 3, have… more
Date: June 1952
Creator: Riebe, John M. & Naeseth, Rodger L.
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Aerodynamic Characteristics of Four Wings of Sweepback Angles 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees, NACA 65A006 Airfoil Section, Aspect Ratio 4, and Taper Ratio 0.6 in Combination With a Fuselage at High Subsonic Mach Numbers and at a Mach Number of 1.2

Description: Report discussing an investigation of the effect of sweepback angle on wing-fuselage characteristics at a subsonic and a supersonic Mach number. Lift, drag, and pitching-moment coefficients, downwash-angle, and total-pressure measurements are all provided.
Date: June 6, 1951
Creator: Luoma, Arvo A.
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