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Electroplated Metals on Uranium for Aluminum Cladding

Description: Abstract: "Aluminum-clad nickel-plated uranium is corrosion resistant in boiling water. Samples with intentional defects in the aluminum-nickel clodding layers, after testing for more than 300 hr. showed no sign of rapid failure. The study of electroplated metals on uranium for aluminum cladding has defined the effects of several processing variables on the corrosion resistance. The quality of the uranium and the quality of the aluminum-nickel bond were important. Heat treatment and vacuum outg… more
Date: May 4, 1955
Creator: Beach, John G.; Schickner, William C.; Hopkinson, Dolores. & Faust, Charles L.
Partner: UNT Libraries Government Documents Department
open access

The Design of a Pulsed Magnetic Field Coil for Table Top 1

Description: Abstract: "A cylindrical coil has been designed for pulsed field operation suitable for use in a model thermonuclear reactor. The coil has an eight-inch inside diameter and a length of fifty-one inches. Magnetic mirrors at the ends consist of double-layer solenoids six and one-half inches long designed to slip over the main coil. Subsequent models of this coil have been fabricated which improved the electrical insulation provided by the bonding materials and the mechanical rigidity of the coil.… more
Date: May 4, 1955
Creator: Ford, Franklin C.
Partner: UNT Libraries Government Documents Department
open access

High Radiation Levels at the Discharge Faces of the Reactors

Description: Undesirably high radiation dosage rates are being encountered in the discharge areas during reactor outages. This is costly to operations in terms of burn-out time, extra work crews, and extended outages require to complete scheduled work. Significant savings in operating costs would be realized if the rear face radiation levels could be reduced during shutdowns. As a first step towards this some measurements have been made to identify and locate the major sources of this radiation. These resul… more
Date: January 4, 1955
Creator: Greene, M. C.
Partner: UNT Libraries Government Documents Department
open access

The New Element Mendelevium, Atomic Number 101

Description: We have produced and chemically identified for the first time a few atoms of the element with atomic number 101. Very intense helium ion bombardments of tiny targets of 99{sup 253} have produced a few spontaneously fissionable atoms which elute in the eka-thulium position on a cation resin column.
Date: April 4, 1955
Creator: Ghiorso, A.; Harvey, B. G.; Choppin, G. R.; Thompson, S. G. & Seaborg, G. T.
Partner: UNT Libraries Government Documents Department
open access

Calculated Heats of Formation and Combustion of Boron Compounds (Boron, Hydrogen, Carbon, Silicon)

Description: Memorandum presenting the calculation of the heats of formation and combustion for liquid and gaseous alkyl- and silyl-substituted boron compounds by a semitheoretical method. The results indicated that alkylation and more especially silylation reduce the heat of combustion. Results regarding alkyl- and silyldecaboranes, diborylmethane, diborylethane, and their alkyl derivatives, bipentaboranyl and bideocaboranyl, dipentaboranyl- and didecaboranylalkanes, and heats of combustion of isomers are … more
Date: October 4, 1955
Creator: Altshuller, Aubrey P.
Partner: UNT Libraries Government Documents Department
open access

Nonlifting Wing-Body Combinations With Certain Geometric Restraints Having Minimum Wave Drag at Low Supersonic Speeds

Description: "Several variational problems involving optimum wing and body combinations having minimum wave drag for different kinds of geometrical restraints are analyzed. Particular attention is paid to the effect on the wave drag of shortening the fuselage and, for slender axially symmetric bodies, the effect of fixing the fuselage diameter at several points or even of fixing whole portions of its shape" (p. 113).
Date: August 4, 1955
Creator: Lomax, Harvard
Partner: UNT Libraries Government Documents Department
open access

Theoretical analysis of incompressible flow through a radial-inlet centrifugal impeller at various weight flows

Description: A method for the solution of the incompressible nonviscous flow through a centrifugal impeller, including the inlet region, is presented. Several numerical solutions are obtained for four weight flows through an impeller at one operating speed. These solutions are refined in the leading-edge region. The results are presented in a series of figures showing streamlines and relative velocity contours. A comparison is made with the results obtained by using a rapid approximate method of analysis.
Date: March 4, 1955
Creator: Kramer, James J.; Prian, Vasily D. & Wu, Chung-Hua
Partner: UNT Libraries Government Documents Department
open access

Wind Tunnel Investigation at Low Speed of the Aerodynamic Characteristics of the Army Chemical Corps Model E112 Bomblets

Description: Report discussing an experimental investigation to determine the aerodynamic characteristics of the Army Chemical Corps model E112 bomblets. From Summary: "A detailed analysis has not been made; however, the results showed that a gap between model tips and the end plates or increasing the end-plate size for a solid model could result in a spirally stable configuration." A large amount of data collected from testing and photographs of the model are provided.
Date: November 4, 1955
Creator: Letko, William & Williams, James L.
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation at low speed of the aerodynamic characteristics of the Army Chemical Corps model E112 bomblets

Description: "An experimental investigation has been made n the Langley stability tunnel to determine the aerodynamic characteristics of the Army Chemical Corps model E112 bomblets. A detailed analysis has not been made; however, the results showed that a gap between model tips and the end plates or increasing the end-plate size for a solid model could result in a spirally stable configuration" (p. 1).
Date: November 4, 1955
Creator: Letko, William & Williams, James L.
Partner: UNT Libraries Government Documents Department
open access

Transonic wind-tunnel investigation of the effects of taper ratio and body indentation on the aerodynamic loading characteristics of a 45 degree sweptback wing in the presence of a body

Description: Report presenting an investigation to determine the effects of taper ratio and body indentation on the aerodynamic loading characteristics of a 45 degree sweptback wing in the presence of a body in the transonic pressure tunnel for a range of Mach numbers and angles of attack. Results regarding the effect of wing-body-juncture seals, general effects of the variables, effect of taper ratio, effects of body indentation, and comparisons with other data are provided.
Date: April 4, 1955
Creator: Delano, James B. & Mugler, John P., Jr.
Partner: UNT Libraries Government Documents Department
open access

Vibratory-Stress Investigation of Six- and Eight-Blade-Dual-Rotating Propellers Operating at Zero Advance

Description: Report presenting the results of an investigation of the vibratory stresses of a dual-rotating propeller with both six-blade and eight-blade configurations using the NACA 6,000-horsepower propeller dynamometer. Attention was focused on the measurement of vibratory stresses caused by mutual blade interference of the front- and rear-propeller components. A range of blade angles and rotational speeds were used in testing.
Date: February 4, 1955
Creator: Heath, Atwood R., Jr. & O'Neal, Robert L.
Partner: UNT Libraries Government Documents Department
open access

Effect of an All-Movable Wing-Tip Control on the Longitudinal Stability of 60 Degree Sweptback-Wing-Indented-Body Configuration Equipped With Fences at Transonic Speeds

Description: Report presenting an investigation to obtain the effects of a 20-percent-semispan all-movable wing-tip control on the longitudinal stability characteristics of a twisted and cambered 60 degree sweptback-wing-indented-body configuration. Testing occurred over a range of angles of attack and Mach numbers. Results regarding the effects on drag coefficient and lift-drag ratio are also provided.
Date: April 4, 1955
Creator: Fischetti, Thomas L. & Loving, Donald L.
Partner: UNT Libraries Government Documents Department
open access

Some Results of Flight Testing of Ski-Equipped Aircraft at the Naval Air Test Center

Description: Memorandum presenting the results of flight testing of four different ski-equipped airplanes. Two types of skis were tested: hydro-skis designed to operate under or on the water surface and general-purpose skis designed to operate on a variety of surfaces but not underwater. A breakdown of the ski performance for each plane and ski combination is provided.
Date: February 4, 1955
Creator: Beck, Preston E.
Partner: UNT Libraries Government Documents Department
open access

Inlet-air distortion effects on stall, surge, and acceleration margin of a turbojet engine equipped with variable compressor inlet guide vanes

Description: Report presenting an investigation of a turbojet engine in an altitude test chamber to determine the effects of a wide range of uneven inlet-air pressure distributions on transient characteristics and stall phenomenon. Circumferential, radial, and mixed pressure variations were run at three simulated altitudes and a simulated Mach number of 0.80. Results regarding the compressor characteristics, compressor stage performance, and acceleration margin are provided.
Date: October 4, 1955
Creator: Harry, David P., III & Lubick, Robert J.
Partner: UNT Libraries Government Documents Department
open access

Experimental flutter investigation of a thin unswept wing at transonic speeds

Description: Report presenting zero-lift experimental flutter data in a range of Mach numbers on a 1.5-percent-thick, untapered, unswept, solid steel wing with hexagonal airfoil sections and wing length-to-chord ratios of 1.61 and 1.73. The wing was tested as a cantilever with and without a half-body-of-revolution fuselage. Results regarding the calculated flutter speeds and frequencies, effect of fuselage, variation of wing flutter characteristics with Mach number, results of analytic solutions, and variat… more
Date: April 4, 1955
Creator: Pratt, George L.
Partner: UNT Libraries Government Documents Department
open access

Flutter Experiences With Thin Pointed-Tip Wings During Flight Tests of Rocket-Propelled Models at Mach Numbers From 0.8 to 1.95

Description: Report presenting flutter data over a range of Mach numbers in free-flight testing of several wing-body combinations as part of a general zero-lift drag investigation. The wings all had the same streamwise airfoil sections and the plan-form variations consisted of delta wings, diamond wings, and an arrow wing. Time histories of model speed, Mach number, and air density are provided for each model as well as flutter frequency, amplitude, and reduced-frequency parameter plotted as functions of mo… more
Date: April 4, 1955
Creator: Wallskog, Harvey A.
Partner: UNT Libraries Government Documents Department
open access

Effects of increasing Reynolds number from 2 x 10(exp 6) to 6 x 10(exp 6) on the aerodynamic characteristics at transonic speeds of a 45 degree swept wing with 6 degree leading-edge droop

Description: Report presenting an investigation in the 16-foot and 8-foot transonic tunnel to determine the effects of Reynolds number and on a swept wing with camber. The wing had 45 degrees sweepback of the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding the effect of Reynolds number on the aerodynamic characteristics and effects of roughness strips are provided.
Date: February 4, 1955
Creator: Schmeer, James W. & Cooper, J. Lawrence
Partner: UNT Libraries Government Documents Department
open access

Results of Measurements Made During the Approach and Landing of Seven High-Speed Research Airplanes

Description: Memorandum presenting an investigation of the landing characteristics of the X-1, X-3, and D-558-I straight-wing, the X-4, X-5, and D-558-II swept-wing, and the XF-92A delta-wing high-speed research airplanes. Results regarding normal landings, vertical velocities at ground contact, ground effect, and effects of lift-drag ratio are provided.
Date: February 4, 1955
Creator: Stillwell, Wendell H.
Partner: UNT Libraries Government Documents Department
open access

Wing-load measurements of the Bell X-5 research airplane at a sweep angle of 58.7 degrees

Description: Report presenting a flight investigation over a range of altitudes and lift to determine the wing loads of the Bell X-5 research airplane at a sweep angle of 58.7 degrees at subsonic and transonic Mach numbers. Testing indicated that wing loads exhibit nonlinear trends over the angle-of-attack range from zero to maximum wing lift.
Date: April 4, 1955
Creator: Banner, Richard D.; Reed, Robert D. & Marcy, William L.
Partner: UNT Libraries Government Documents Department
open access

Flight Experience With Two High-Speed Airplanes Having Violent Lateral-Longitudinal Coupling in Aileron Rolls

Description: "During flight tests of two high-speed airplane configurations, violent cross-coupled lateral and longitudinal motions were encountered following abrupt rudder-fixed aileron rolls. The speeds involved ranged from a Mach number of 0.7 to 1.05. The motions were characterized by extreme variations in angles of attack and sideslip which resulted in load factors as large as 6.7g (negative) and 7g (positive) normal acceleration and 2g transverse acceleration" (p. 1).
Date: February 4, 1955
Partner: UNT Libraries Government Documents Department
open access

Thunderstorms-Part One

Description: This report is about thunderstorms and studying its characteristics. It also studies the various cycles of thunderstorms.
Date: May 4, 1955
Creator: U.S Government printing office
Partner: UNT Libraries Government Documents Department
open access

200 Area weekly report

Description: No Description Available.
Date: August 4, 1955
Creator: Christl, R. J.
Partner: UNT Libraries Government Documents Department
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