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Corrosion of Type 347 Stainless Steel in the Uranium-Derby Pickle Bath

Description: Abstract: In one of the final stages of the process at the Mallinckrodt Uranium Refining Center, a 45 per cent nitric acid solution at about 170 F is used to pickle the calcined magnesium fluoride scale off the uranium derbies. The increase in the fluoride-ion content of the bath tends to promote corrosion of the Type 347 stainless tanks. This attack becomes excessive if 0.3 g/liter of fluoride ion or more is present. It was found that if aluminum ion is added to the solution the corrosiveness … more
Date: July 14, 1954
Creator: Peoples, R. S.; Fink, F. W.; Stewart, O. M. & Braun, W. J.
Partner: UNT Libraries Government Documents Department
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A preliminary investigation of the use of circulation control to increase the lift of a 45 degree sweptback wing by suction through trailing-edge slots

Description: Report presenting an investigation to determine the effectiveness of circulation control by applying suction through trailing-edge slots on a 45 degree sweptback wing. Various chordwise extents and depths of slot were investigated with and without deflection of a trailing-edge split flap. Results regarding the correlation of two-dimensional-section results with Ehlers' theory, effectiveness of circulation control on a sweptback wing, effect of slot configuration on circulation control, effect o… more
Date: December 14, 1954
Creator: Cook, Woodrow L.; Griffin, Roy N., Jr. & Hickey, David H.
Partner: UNT Libraries Government Documents Department
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Some effects of aileron span, aileron chord, and wing twist on rolling effectiveness as determined by rocket-powered model tests and theoretical estimates

Description: A determination of the variation of rolling effectiveness with spanwise aileron extent for full-chord ailerons on a sweptback wing over a range of Mach numbers. The test wings had NACA 65A006 airfoil sections, an aspect ratio of 4.0, 45 degrees sweepback at the quarter-chord line, and a taper ratio of 0.6. Results regarding ailerons and twisted wings are provided.
Date: September 14, 1954
Creator: Strass, H. Kurt & Tucker, Warren A.
Partner: UNT Libraries Government Documents Department
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Aspects of internal-flow-system design for helicopter propulsive units

Description: A discussion of pertinent items related to the design of internal-flow systems for reciprocating engine, turbine engine, and pressure-jet installations in helicopters. The following items are emphasized: controllable exit and ram recovery for reciprocating-engine cooling, performance penalties possible in turbine-engine installations, the effects of high subsonic flow velocities on the performance of duct elements, and the effects of centrifugal forces on the flow in a ducted helicopter rotor.
Date: September 14, 1954
Creator: Henry, John R.
Partner: UNT Libraries Government Documents Department
open access

Effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin NACA airfoil sections

Description: Report presenting a wind-tunnel investigation to determine the effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin symmetrical NACA 4-digit-series airfoil sections. The variations with Mach number of the lift, drag, and pitching moment for a 4-percent-chord-thick airfoil section are not significantly affected by a change of leading-edge radius from 0.18 to 0.53 percent of the chord.
Date: April 14, 1954
Creator: Berggren, Robert E. & Graham, Donald J.
Partner: UNT Libraries Government Documents Department
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Flight Investigation of the Rolling Effectiveness of Fingered Semaphore Spoilers on a Tapered 45 Sweptback Wing Between Mach Numbers 0.6 and 1.3

Description: Report discussing an investigation of a fingered semaphore spoiler and an equivalent solid spoiler configuration to determine the effects of spoiler projection, porosity, and chordwise position on the rolling effectiveness and drag of spoiler arrangements at a range of Mach numbers. The fingered semaphore spoilers were found to have less rolling effectiveness and drag than the solid spoilers.
Date: January 14, 1954
Creator: Church, James D.
Partner: UNT Libraries Government Documents Department
open access

Application of Radial-Equilibrium Condition to Axial-Flow Turbomachine Design Including Consideration of Change of Entropy With Radius Downstream of Blade Row

Description: Report presenting an investigation of the validity of application of the simplified-radial-equilibrium equation to axial-flow turbomachines. Two different types of equations were used. Results regarding the interpretation of the data, single stages, middle and end stages of the multistage compressor, application of the radial-equilibrium equation, and the solution for the velocity distributions are provided.
Date: April 14, 1954
Creator: Hatch, James E.; Giamati, Charles C. & Jackson, Robert J.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics of several flap-type trailing-edge controls on a trapezoidal wing at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation at Mach numbers of 1.61 and 2.01 to determine the control effectiveness and hinge-moment characteristics for a series of 25.4-percent-chord trailing-edge controls on a trapezoidal wing with a 23 degree sweptback leading edge, aspect ratio of 3.1, and taper ratio of 0.4. Pressure distribution and hinge-moment measurements were made at a range of angles of attack and control deflections. Results regarding effect of control deflection, effect of wing angle of att… more
Date: June 14, 1954
Creator: Lord, Douglas R. & Czarnecki, K. R.
Partner: UNT Libraries Government Documents Department
open access

Effect at Transonic Speeds of Inboard Spoilers on the Static Longitudinal Stability Characteristics of a 45 Degree Sweptback Wing-Body Combination Having a Leading-Edge Chord-Extension

Description: Memorandum presenting an exploratory investigation in the 9- by 12-inch blowdown tunnel to determine the effect of inboard spoilers located along the 20- and 30-percent-chord lines on the static longitudinal stability characteristics of a semispan 45 degree sweptback wing-body combination with a leading-edge chord-extension. The model pitching-moment characteristics were improved by spoilers extending from 15 percent semispan to 45 percent semispan. Results regarding pitching moment, lift, drag… more
Date: June 14, 1954
Creator: Henderson, James H.
Partner: UNT Libraries Government Documents Department
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Effects of diffuser and center-body length on performance of annular diffusers with constant-diameter outer walls and with vortex-generator flow controls

Description: Report presenting data for five diffusers tested with and without vortex-generator controls in order to determine the performance improvements attainable through the use of boundary-layer controls. Results regarding inlet conditions, axial inlet flow, and whirling inlet flow are provided.
Date: September 14, 1954
Creator: Wood, Charles C. & Higginbotham, James T.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation at High Subsonic Speeds of the Stability Characteristics of a Complete Model Having Sweptback-, M-, W-, and Cranked-Wing Plan Forms and Several Horizontal-Tail Locations

Description: Report presenting an investigation at high subsonic speeds of a complete model with one of four types of wings: a basic sweptback wing, an M-shaped wing, a W-shaped wing, and a cranked wing. All of the wings had the same aspect and taper ratio and were tested at the same range of Mach numbers. Results regarding longitudinal characteristics and lateral characteristics of the different wings are provided.
Date: May 14, 1954
Creator: Goodson, Kenneth W. & Becht, Robert E.
Partner: UNT Libraries Government Documents Department
open access

Effect of yaw and angle of attack on pressure recovery and mass-flow characteristics of a rectangular supersonic scoop inlet at a Mach number of 2.71

Description: Report presenting an investigation of the effect of yaw and angle of attack on the total-pressure recovery and mass-flow characteristics of a rectangular supersonic scoop inlet designed to have low external drag at a Mach number of 2.7 and an angle of attack of 0 degrees. Total-pressure recovery and mass-flow data are presented for a Mach number of 2.71 at angles of yaw 0, 2.5, and 5 degrees and angles of attack of 0 and 5 degrees are provided.
Date: September 14, 1954
Creator: Comenzo, Raymond J. & Mackley, Ernest A.
Partner: UNT Libraries Government Documents Department
open access

Minimum drag of 0.11-scale rocket-powered models of the Chance Vought XF8U-1 airplane, with and without nose modifications, at Mach numbers between 0.85 and 1.30 : TED No. NACA DE 392

Description: Report presenting drag data obtained from flight tests of two scale rocket-powered models of the Chance Vought XF8U-1 airplane. Results regarding the minimum drag coefficient and effect of nose modifications are provided.
Date: June 14, 1954
Creator: Blanchard, Willard S., Jr.
Partner: UNT Libraries Government Documents Department
open access

Summary of rocket-model tests at zero lift of an arrow-wing missile configuration from Mach numbers of 0.9 to 1.8

Description: Report presenting flight tests conducted between Mach numbers of 0.9 to 1.8 over a range of Reynolds numbers to determine the zero-lift drag and some rolling-effectiveness characteristics of a proposed long-range, supersonic, ground-to-ground missile. Results regarding the longitudinal trim, drag, rolling effectiveness, and instability due to roll are provided.
Date: January 14, 1954
Creator: Arbic, Richard G. & Gillespie, Warren, Jr.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of a Method for Obtaining Hydrodynamic Data at Very High Speeds With a Free Water Jet

Description: Report presenting information regarding the feasibility of using a rectangular free water jet to obtain hydrodynamic data at very high speeds. Total-head pressure distributions in the jet and experimental hydrodynamic lift data is provided and compared to data obtained in water tank testing. The data obtained indicates that it is feasible to use a free water jet for this purpose.
Date: June 14, 1954
Creator: Weinflash, Bernard & McGehee, John R.
Partner: UNT Libraries Government Documents Department
open access

DEVELOPMENT OF A METHOD FOR PREDICTING CONTINUOUS TRICKLE-TYPE COLUMN DISSOLVER BEHAVIOR FROM BATCH DATA

Description: A method for determining dissolver solution concentration as a function of length of column traversed for trickletype continuous dissolvers has been developed. An illustrative example is worked out for the mercury-catalyzed nitric acid dissolution of U-Al cast alloy slugs. The method employs a graphical integration of simple functions of dissolution rates and acid concentrations. These rates and concentrations are easily obtained from batch experiments made over the important ranges of concentr… more
Date: May 14, 1954
Creator: Wymer, R.G.
Partner: UNT Libraries Government Documents Department
open access

Evaluation of a Modified Zircaloy-2 Ingot F-1071 Melted at WAPD

Description: "The following is an evaluation of a modified Zircaloy-2 ingot melted at WAPD using the non-consumable electrode melting technique. The nominal composition of the alloy is 0.5% tin, 0.1% iron, 0.1% chromium, and 0.5% nickel."
Date: April 14, 1954
Creator: Goodwin, J. G.
Partner: UNT Libraries Government Documents Department
open access

Metallurgy Division Semiannual Progress Report for Period Ending October 10, 1955

Description: Progress report of the Oak Ridge National Laboratory Metallurgy Division providing updates on various projects, experiments, and other work. This report includes a summary of nondestructive testing, physical chemistry of corrosion, fundamental physico-metallurgical research, HRP metallurgy, process metallurgy, metallurgical materials and processing, metallography, and ceramics research.
Date: June 14, 1954
Creator: Manly, W. D.
Partner: UNT Libraries Government Documents Department
open access

Infinite Conductivity Theory of the Pinch

Description: With the assumption of infinite conductivity a simple model may be constructed for the dynamic construction of a current carrying plasma, i.e., the pinch effect. The magneto-hydrodynamic equations of this model are discussed and solved. It is also shown that the infinite conductivity model can be derived from a picture of particles orbiting without collisions in the fields set up by their motions.
Date: September 14, 1954
Creator: Rosenbluth, M.; Garwin, R. & Rosenbluth, A.
Partner: UNT Libraries Government Documents Department
open access

The Recovery of Uranium from Chattanooga Shales

Description: Recovery of uranium from Chattanooga shales.
Date: January 14, 1954
Creator: Wilson, R. Q.; Ewing, R. A.; Hanway, J. E., Jr.; Meeley, W. A.; Bearse, A. E.; Filbert, R. B., Jr. et al.
Partner: UNT Libraries Government Documents Department
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