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The Properties and Heat Treatment of Uranium-Titanium Alloys

Description: This report discusses mechanical properties and heat treatment of some uranium-titanium alloys. These alloys were tested for use as fuel-element material.
Date: July 10, 1956
Creator: Douglass, David L.; Marsh, Lyle L. & Manning, George K.
Partner: UNT Libraries Government Documents Department
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Meeting at BMI on electroplating uranium for extrusion cladding, November 8, 1956

Description: This report discusses a meeting held on November 8, 1956 at BMI, Columbus, Ohio, for the following purposes: To determine the best method of electroplating uranium cores for extrusion cladding; to determine if there were any shortcomings in the SRL method of plating which could be the cause of the poor bonding experienced with internally extrusion-clad tubes; and to make what corrections and revisions were necessary in SRL plating procedure to assure the optimum quality of nickel electroplate o… more
Date: November 10, 1956
Creator: O`Leary, W. J.
Partner: UNT Libraries Government Documents Department
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Hindered Diphenoquinones: Diradicals of Oxygen

Description: Attempts were made to prepare a diphenoquinone having substituents in 2,2'-positions in order to prevent the planarity of the molecule and get a diradical of oxygen. The 2,2'-dimethyl-5,5'-di-t-butyldiphenoquinone was prepared and was shown to be in equilibrium with a small amount of diradical. This compound slowly polymerizes.
Date: July 10, 1956
Creator: Bourdon, Jean & Calvin, Melvin
Partner: UNT Libraries Government Documents Department
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EFFECT OF SPACER DENSITY ON HEAT TRANSFER AND PRESSURE DROP IN THE ART FUEL- TO-NaK HEAT EXCHANGER

Description: Heat transfer and isothermal friction characteristics of the experimental ART fuel-to-NaK heat exchanger have been determined for three degrees of spacer density. The data appear to indicate that for a given heat exchanger pressure drop, the heat transfer cocfficient is almost independent of the spacer density; as the spacer density is decreased, the Reynolds modulus increases to such an extent that the Nusselt modulus does not change significantly. For a given available pressure drop, with dec… more
Date: October 10, 1956
Creator: Wantland, J.K.
Partner: UNT Libraries Government Documents Department
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Analysis of a flight investigation at supersonic speeds of a simple homing system

Description: From Introduction: "The purpose of the flight investigation described herein was as a "proof" check of the system and to determine what effect several variables which could not be practicably simulated would have on the operation."
Date: January 10, 1956
Creator: Gardiner, Robert A.; Gillis, Clarence L. & Graves, G. B., Jr.
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of the damping in roll of the Bell X-1A research airplane and its components at supersonic speeds

Description: Report presenting the experimental values of damping in roll of the Bell X-1A airplane and its components at 5 Mach numbers at zero angle of attack. The wing was found to be the predominant contributor to the damping in roll throughout the range of Mach numbers, but the contributions of other airplane components were significant in the range of 2.22 to 2.41.
Date: January 10, 1956
Creator: McDearmon, Russell W. & Clark, Frank L.
Partner: UNT Libraries Government Documents Department
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Force and Pressure-Distribution Investigation to High Angles of Attack on All-Movable Triangular and Rectangular Wings in Combination With a Body at Supersonic Speeds

Description: Force and pressure distribution studies to high angles of attack on all-movable triangular and rectangular wings in combination with body at supersonic speeds. The ranges of aspect ratios were, for the triangular wings, 3/8 to 4, and for the rectangular wings, 1 to 3.
Date: July 10, 1956
Creator: Hill, William A., Jr. & Kaattari, George E.
Partner: UNT Libraries Government Documents Department
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Effect of Throat Bleed on the Supersonic Performance of a Half-Conical Side-Inlet System

Description: Memorandum presenting an experimental investigation conducted at Mach numbers 1.5, 1.8, and 2.0 to determine the effects of several throat boundary-layer bleed configurations on the performance of a 25 degree half-conical side-inlet system. The effects of several flush-slot configurations and a porous-surface bleed were determined over ranges of angle of attack and bleed-duct and main-duct mass flow.
Date: January 10, 1956
Creator: Sitt, Leonard E.; McKevitt, Frank X. & Smith, Albert B.
Partner: UNT Libraries Government Documents Department
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The Appearance of a Boric Oxide Exhaust Cloud From a Turbojet Engine Operating on Trimethylborate Fuel

Description: Memorandum presenting an investigation conducted on the size and density of the boric oxide exhaust cloud from a J47-25 turbojet engine operating on trimethyl-borate fuel at sea-level static conditions. Movies and still photographs were taken from the ground and from a helicopter. Results regarding the visual observation and oxide fallout and concentration are provided.
Date: August 10, 1956
Creator: Lord, Albert M. & Kaufman, Warner B.
Partner: UNT Libraries Government Documents Department
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A Transonic Investigation of Changing Indentation Design Mach Number on the Aerodynamic Characteristics of a 45 Degree Sweptback-Wing-Body Combination Designed for High Performance

Description: Report presenting an investigation of the effects of changing indentation design Mach number on the aerodynamic characteristics of a 45 degree sweptback-wing-body combination designed for high performance at a range of Mach numbers. Theoretical results of zero-lift wave drag for the wing-body combination agreed well with the experimental data. Results regarding the bodies, systematic series of wing-body combinations, -2 degree angle of incidence, M = 1.4 revised body, and transition are present… more
Date: January 10, 1956
Creator: Loving, Donald L.
Partner: UNT Libraries Government Documents Department
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Flight investigation of the effect of vertical-tail size on the rolling behavior of a swept-wing airplane having lateral-longitudinal coupling

Description: Report presenting flight testing over a range of Mach numbers to determine the rolling behavior of a swept-wing airplane with lateral-longitudinal coupling. Results regarding the size of the tail area, speed effects, engine gyroscopic effects, and wing-tip extensions are provided.
Date: April 10, 1956
Creator: Finch, Thomas W.; Peele, James R. & Day, Richard E.
Partner: UNT Libraries Government Documents Department
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