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Zirconium Metal Fines Recovery: Interim Technical Report for May 15, 1950 to December 15, 1950

Description: This report covers the laboratory and pilot plant investigation of the reclamation of the low hafnium zirconium fines resulting from the manufacture of zirconium sponge and zirconium crystal bar. The process investigated involved recovery of the zirconium as zirconium tetrachloride, by drying the fines in an atmosphere of nitrogen and subsequent chlorination of the fines with anhydrous hydrogen chloride at temperatures above the sublimation point of the product.
Date: January 24, 1951
Creator: Ogburn, S. C., Jr. & Reader, L. J.
Partner: UNT Libraries Government Documents Department
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Insulating webbing between thermal shield and graphite reflector

Description: The purpose of this document is to present the bases and calculations which resulted in the conclusion given in the letter of October 17. Also, the original calculations were made on the basis that the webbing face thickness is equal to 1/2 inch, which is no longer the case. The new thickness is 3/4 inch. This alters the condition of heat generation. Consideration is given to the heat generation in the legs.
Date: October 24, 1951
Partner: UNT Libraries Government Documents Department
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Hanford Works monthly report, August 1951

Description: This is a progress report of the production reactors on the Hanford Reservation for the month of August 1951. This report takes each division (e.g., manufacturing, medical, accounting, occupational safety, security, reactor operations, etc.) of the site and summarizes its accomplishments and employee relations for that month.
Date: September 24, 1951
Partner: UNT Libraries Government Documents Department
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Hanford Works monthly report, July 1951

Description: This is a progress report of the production reactors on the Hanford Reservation for the month of July 1951. This report takes each division (e.g., manufacturing, medical, accounting, occupational safety, security, reactor operations, etc.) of the site and summarizes its accomplishments and employee relations for that month.
Date: August 24, 1951
Creator: Prout, G. R.
Partner: UNT Libraries Government Documents Department
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Uranium Deposits on Mesas I 1/2 and II 1/2, Lukachukai Mountains, Northeast Arizona

Description: Abstract: Mesas 1 1/2 and II 1/2 were investigated in October 1951, to determine the extent and degree of uranium mineralization in the Salt Wash sandstone. Carnotite-vanoxite-type minerals are sufficiently concentrated to recommend 14,600 feet of drilling.
Date: October 24, 1951
Creator: Masters, John A. & Blum, Richard D.
Partner: UNT Libraries Government Documents Department
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Carbon Dioxide Fixation by Microorganisms

Description: Resting cells of eleven microorganisms were exposed to radioactive carbon dioxide for 40 minutes. The radioactive compounds formed during this time were separated and identified by paper chromatography. Resting cells of Lactobacillus casei fixed no carbon dioxide and growing cells fixed carbon dioxide primarily in malic and aspartic acids. All of the radioactive compounds formed could have become radioactive by reversal of known decarboxylation reactions.
Date: July 24, 1951
Creator: Lynch, Victoria H. & Calvin, Melvin
Partner: UNT Libraries Government Documents Department
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Investigation at low speed of the effectiveness and hinge moments of a constant-chord elevator on a large-scale triangular wing with section modification

Description: Report presenting an investigation in the full-scale tunnel to determine the low-speed longitudinal, lateral, and hinge-moment control characteristics of a basic 60 degree delta wing of aspect ratio 2.31 with 10-percent-thick biconvex symmetrical airfoil sections. The wing was tested with a nose glove using NACA 65-010 section ordinates and a constant-chord plain semispan ailavator with two segments.
Date: April 24, 1951
Creator: Hawes, John G. & May, Ralph W., Jr.
Partner: UNT Libraries Government Documents Department
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A transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2 : wing-fuselage configuration having a wing of 60 degree sweepback, aspect-ratio 4, taper ratio 0.6, and NACA 65A006 airf

Description: Report presenting a study of the effect of sweep on wings with the NACA 65A006 airfoil section in the 8-foot high-speed tunnel. This particular investigation included a wing with that airfoil section, 60 degrees of sweepback at the quarter chord, an aspect ratio of 4, and a taper ratio of 0.6. Results regarding force and moment characteristics and wake and downwash characteristics are provided.
Date: January 24, 1951
Creator: Wood, Raymond B. & Fleming, Frank F.
Partner: UNT Libraries Government Documents Department
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Determination and Use of the Local Recovery Factor for Calculating the Effectiveness Gas Temperature for Turbine Blades

Description: In an experimental investigation of local recovery factors for a blade having a pressure distribution similar to that of a typical reaction-type turbine blade, it a was found that the recovery factors were essentially independent of Mach number, Reynolds number, pressure gradient, and position on the blade surface except for regions where the boundary layer was probably in the transition range from laminar to turbulent. The recommended value of local subsonic recovery factor for use in calculat… more
Date: September 24, 1951
Creator: Esgar, Jack B. & Lea, Alfred L.
Partner: UNT Libraries Government Documents Department
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Correlation of Analog Solutions With Experimental Sea-Level Transient Data for Controlled Turbine-Propeller Engine, Including Analog Results at Altitudes

Description: Memorandum presenting a satisfactory correlation obtained between experimental sea-level transient data at constant flight speed and solutions from the analog representation. The representation is accomplished by transfer functions formed from a frequency-response analysis, which is then used to compute system response at altitude.
Date: August 24, 1951
Creator: Lazar, James & DeRocher, Wilfred L., Jr.
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 development of flow and thermal boundary layers in laminar regime on cylinders with arbitrary cross section and transpiration-cooled walls is obtained by use of Karman's integrated momentum equation and an analogous heat-flow equation. Incompressible flow with constant property values throughout boundary layer is assumed. Shape parameters for approximated velocity and temperature profiles and functions necessary for solution of boundary-layer equations are presented as… more
Date: September 24, 1951
Creator: Eckert, E. R. G. & Livingood, John N. B.
Partner: UNT Libraries Government Documents Department
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Effects of Spoiler on Airfoil Pressure Distribution and Effects of Size and Location of Spoilers on the Aerodynamic Characteristics of a Tapered Unswept Wing of Aspect Ratio 2.5 at a Mach Number of 1.90

Description: Report presenting an investigation in the supersonic blowdown tunnel of spoilers on two unswept wing arrangements at Mach numbers of 1.90 and 1.96. The effect of pressure-distribution tests on an unswept airfoil in the presence of a fuselage but without tip effects indicated that spoilers could be oppositely deflected in a manner similar to flap-type ailerons to obtain roll effectiveness without loss in lift. Results regarding force and moment tests are also provided.
Date: January 24, 1951
Creator: Conner, D. William & Mitchell, Meade H., Jr.
Partner: UNT Libraries Government Documents Department
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Flight measurements of the wing-dropping tendency of a straight-wing jet airplane at high subsonic Mach numbers

Description: From Summary: "Flight tests were conducted on a straight-wing fighter-type jet airplane to investigate the lateral-control characteristics associated with a wing-dropping tendency encountered at high subsonic Mach numbers. The chief factors found to account directly for the wing-dropping tendency were a progressive reduction in aileron-control effectiveness with increasing Mach number, and an increase in effective dihedral above a Mach number of 0.8 which made the lateral trim particularly sens… more
Date: April 24, 1951
Creator: Anderson, Seth B.; Ernst, Edward A. & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department
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Investigation of the Effect of a Nacelle at Various Chordwise and Vertical Positions on the Aerodynamic Characteristics at High Subsonic Speeds of a 45 Degrees Sweptback Wing With and Without a Fuselage

Description: Report presenting an investigation of a nacelle at various chordwise positions and vertical locations on a semispan model of a wing with and without a fuselage through a range of Mach numbers. The investigation was made to determine the interference characteristics between the nacelle and the model and to determine the effect of the fuselage on nacelle interference.
Date: September 24, 1951
Creator: Silvers, H. Norman; King, Thomas J., Jr. & Pasteur, Thomas B., Jr.
Partner: UNT Libraries Government Documents Department
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Free-Spinning Tunnel Investigation of a 1/20-Scale Model of the McDonnell F2H-3 Airplane

Description: Memorandum presenting an investigation conducted in the 20-foot free-spinning tunnel on a 1/20-scale model of the McDonnell F2H-3 airplane. The effects of control settings and movement on the erect spin and recovery characteristics of the model were determined for the take-off condition and for the condition with full wing-tip fuel tanks installed.
Date: July 24, 1951
Creator: Wilson, Jack H.
Partner: UNT Libraries Government Documents Department
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The effects of camber and twist on the aerodynamic loading and stalling characteristics of a large-scale 45 degree swept-back wing

Description: Report presenting pressure-distribution measurements on two large-scale semispan wing-fuselage models with 45 degrees of sweepback, an aspect ratio of 6, a taper ratio of 0.5, and 10-percent-thick sections normal to the quarter-chord line. Adding camber and twist to a wing significantly improved the upper surface loading of the wing at a lift coefficient of 0.4 through a reduction in the peak negative pressure coefficient. Results regarding loading characteristics and stalling characteristics a… more
Date: January 24, 1951
Creator: Hunton, Lynn W. & Dew, Joseph K.
Partner: UNT Libraries Government Documents Department
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Secondary Flows in Annular Cascades and Effects on Flow in Inlet Guide Vanes

Description: Qualitative discussion is presented of the general nature of secondary flows in stationary annular cascades with thin wall boundary layers and radial design variation of circulation. Deviations from ideal mean outlet flows (based on blade-element performance) exist in potential-flow region of vanes because of conditions imposed by end-wall boundaries, displacement of wall boundary layers toward blade suction surfaces, and irrotationality requirement. As a consequence of existence of nonuniform … more
Date: August 24, 1951
Creator: Lieblein, Seymour & Ackley, Richard H.
Partner: UNT Libraries Government Documents Department
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Some Effects of Solidity on Turning Through Constant-Thickness Circular-Arc Guide Vanes in Axial Annular Flow

Description: Memorandum presenting an investigation conducted on sheet metal, circular-arc compressor inlet guide vanes in an annular cascade with untapered walls to determine the effect of solidity on turning through a blade row. Guide vanes of 30 and 40 degrees camber were investigated over a range of solidity from 0.5 to 4.0. Results regarding the effect of solidity on turning angle, comparison with two-dimensional methods, application of results, and total-pressure losses are provided.
Date: August 24, 1951
Creator: Mankuta, Harry & Guentert, Donald C.
Partner: UNT Libraries Government Documents Department
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The Linearized Characteristics Method and Its Application to Practical Nonlinear Supersonic Problems

Description: "The methods of characteristics has been linearized by assuming that the flow field can be represented as a basic flow field determined by nonlinearized methods and a linearized superposed flow field that accounts for small changes of boundary conditions. The method has been applied to two-dimensional rotational flow where the basic flow is potential flow and to axially symmetric problems where conical flows have been used as the basic flows. In both cases the method allows the determination of… more
Date: July 24, 1951
Creator: Ferri, Antonio
Partner: UNT Libraries Government Documents Department
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Analysis of the effects of wing interference on the tail contributions to the rolling derivatives

Description: From Introduction: "This report presents calculations of the angularity of the air stream with respect to the vertical tail for a rolling airplane, the interference effects of the wing being taken into account. A discussion of the factors which enter into the calculations is given and equations for applying the side-wash results to the determination of the tail contributions to the rolling-stability derivatives are included. The results are compared with some available experimental data."
Date: January 24, 1951
Creator: Michael, William H., Jr.
Partner: UNT Libraries Government Documents Department
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