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Mechanical Properties of Zirconium-Tin Alloys

Description: Abstract: "The mechanical properties and corrosion resistance of induction-melted, zirconium-tin alloys have been determined. The alloys investigated contained from zero to five per cent tin and up to 0.3% carbon. The zirconium used was United States Bureau of Mines sponge zirconium. The mechanical properties investigated include the tensile, hot-hardness, and impact properties."
Date: December 22, 1952
Creator: Schwope, A. D. & Chubb, Walston
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hydrogen Embrittlement of Zirconium

Description: Abstract: "The amount of hydrogen normally present in zirconium and zirconium alloys suffices to reduce their ductility greatly in an impact test at room temperature, after slow cooling from 600 F. Quenching from 600 F or above gives high impact strength, as does removal of hydrogen by high-temperature vacuum annealing. This report discusses the evidence on hydrogen embrittlement, the diffusion, solid solubility, and equilibrium pressure of hydrogen of hydrogen in zirconium, the microstructure,… more
Date: August 22, 1952
Creator: Dayton, Russell Wendt; Schwope, A. D.; Muehlenkamp, G. T.; Saller, Henry A.; Dickerson, R. F.; Schwartz, C. M. et al.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Corrosion of Aluminum in Alum Coagulated Process Water

Description: The following report provides the results of an accelerated corrosion test that was performed to compare the effect of two coagulants on the corrosion rates of aluminum slug jacket alloy and 72S. Additionally, some analytical data on the water from the two treatments were obtained and are presented in this report.
Date: January 22, 1952
Creator: Dalrymple, R. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Hanford Works monthly report, December 1951

Description: This is a progress report of the production reactors on the Hanford Reservation for the month of December 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: January 22, 1952
Creator: Prout, G. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Boiling limits

Description: Uncontrolled boiling of the water in a process tube might result in serious damage to a pile. Consequently, it is desirable to maintain header pressure generally sufficient to sweep out any steam which might be formed. Since the header pressure required to remove the steam depends upon the power output of the tube, the power level of a tube or pile is limited by the pressure available. In the past, tube power limitations have been specified and interpretations thereof. Recently a through study,… more
Date: January 22, 1952
Creator: Vanderwater, R. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department

[Price family with carriage]

Description: Photograph of Daniel Price and his family with a horse drawn carriage. Price stands outside the open door of the carriage, holding his hat. His family sits inside looking out the windows. A man sits at the front holding the reins.
Date: July 22, 1952
Creator: WBAP-TV (Television station : Fort Worth, Tex.)
Item Type: Refine your search to only Photograph
Partner: UNT Libraries Special Collections

[Price Daniels and his family]

Description: Photograph of Price Daniels and his family with a carriage. Daniels stands outside the door holding a hat and looking to the right. His family sits inside the carriage looking out the window and waving at the camera. There is a house in the background.
Date: July 22, 1952
Creator: WBAP-TV (Television station : Fort Worth, Tex.)
Item Type: Refine your search to only Photograph
Partner: UNT Libraries Special Collections

[Price family poses with carriage]

Description: Photograph of two children of the Price family posing with a carriage driver in the front seat as he holds the reins. The driver and one of the children are wearing cowboy hats. A woman is visible smiling and getting out of the cab of the carriage in the background.
Date: July 22, 1952
Creator: WBAP-TV (Television station : Fort Worth, Tex.)
Item Type: Refine your search to only Photograph
Partner: UNT Libraries Special Collections
open access

THE CORROSION RESISTANCE OF SEVERAL ALLOYS IN AN HF-H$sub 2$O ATMOSPHERE AT HIGH TEMPERATURES

Description: Tests indicate that of the various alloys tssted for corrosion resistance when exposed 10 an HF-HP atmosphere at 1070 F, the Cr-Ni alloys, as a group, give the best corrosion resistance where strength at high temperature is desired. Other alloys have given excellent results but the lack of strength at the higher temperatures or cost, is against their use in production equipment. (auth)
Date: January 22, 1952
Creator: Ritchie, C.F. & Teter, E.K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hydrogen Embrittlement of Zirconium

Description: The amount of hydrogen normally present in zirconium and zirconium alloys suffices to reduce their ductility greatly in an impact test at room temperature, after slow cooling from 6OO deg F. Quenching from 6OO deg F or above gives high impact strength, as does removal of hydrogen by hightemperature vacuum aanealing. The evidence on hydrogen embrittlement, the diffusion, solid solubility, and equilbrium pressure of hydrogen in zirconium the microstructure, and the effects of hydrogen and heat tr… more
Date: August 22, 1952
Creator: Dayton, R. W.; Schwope, A. D.; Muehlenkamp, G. T.; Saller, H. A.; Dickerson, R. F.; Schwartz, C. M. et al.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of stabilizing fins and a rear-support sting on the base pressure of a body of revolution in free flight at Mach numbers from 0.7 to 1.3

Description: From Summary: "Ogive-cylindrical fuselages of fineness ratio 11 have been flight-tested with and without stabilizing fins. Base-pressure measurements over a range of free-stream Mach numbers from 0.7 to 1.3 indicated that the fins reduced the base drag. A rear-support sting similar to those used in wind tunnels was tested with one of the fuselages and found to reduce base suction by 40 percent at subsonic speeds, but to have little effect at Mach numbers above 1.15."
Date: September 22, 1952
Creator: Hart, Roger G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary air-flow and thrust calibrations of several conical Cooling-air ejectors with a primary to secondary temperature ratio of 1.0 I :diameter ratios of 1.21 and 1.10

Description: Report presenting an investigation of the performance of several conical cooling-air ejectors at primary jet pressure ratios from 1 to 10, secondary shroud pressure ratios from 0.60 to 4.00, and primary to secondary temperature ratio of 1.0. The investigation centered on primary air flow, secondary air flow, primary nozzle thrust, and gross ejector thrust.
Date: July 22, 1952
Creator: Greathouse, W. K. & Hollister, D. P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of water vapor on combustion of magnesium hydrocarbon slurry fuels in small-scale afterburner

Description: Report presenting testing of JP-3 fuel and a slurry of 60 percent powdered magnesium in JP-3 fuel in a small-scale afterburner in the presence of large quantities of water vapor. The results indicated that total temperature, combustion efficiency, and air specific impulse were improved when the magnesium slurry was used, but the improvements came at the cost of increased liquid consumption.
Date: October 22, 1952
Creator: Tower, Leonard K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of the Effects of Variations in the Reynolds Number Between 0.4 X 10(Exp 6) 3.0 X 10(Exp 6) on the Low-Speed Aerodynamic Characteristics of Three Low-Aspect-Ratio Symmetrical Wings With Rectangular Plan Forms

Description: Report presenting an investigation of the effect of Reynolds number and the addition of leading-edge roughness on the aerodynamic characteristics of wings with aspect ratio 1, 2, and 3, a rectangular plan form, square-cut wing tips, and NACA 0012 airfoil sections. Results regarding lift and moment, lift-curve slope, and maximum lift are provided.
Date: September 22, 1952
Creator: Jones, George W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Turbines for Driving Supersonic Compressors 2: Performance of First Configuration With 2.2 Percent Reduction in Nozzle Flow Area

Description: "The experimental performance of a modified turbine for driving a supersonic compressor is presented and compared with the performance of the original configuration to illustrate the effect of small changes in the ratio of nozzle-throat area to rotor-throat area. Performance is based on the performance of turbines designed to operate with both blade rows close to choking. On the basis of the results of this investigation, the ratio of areas is concluded to become especially critical in the desi… more
Date: July 22, 1952
Creator: Stewart, Warner L.; Schum, Harold J. & Wong, Robert Y.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics of two 25-percent-area trailing-edge flaps on an aspect ratio 2 triangular wing at subsonic and supersonic speeds

Description: Report presenting the results of an investigation of flap-type controls on a low-aspect-ratio triangular wing using NACA 0005-63 sections for a constant-chord and a constant-percent-chord control surface. Two flap profiles were investigated: one with a true contour and the other with a blunt trailing edge. Results regarding lift, drag, pitching moment, hinge moment, and rolling moments were obtained for several Mach numbers, a constant Reynolds number, and a range of angles of attack.
Date: July 22, 1952
Creator: Boyd, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Some Primary Variables of Rectangular Vortex Generators on the Static-Pressure Rise Through a Short Diffuser

Description: Memorandum presenting an investigation of a 2:1 area ratio conical diffuser of length equal to the inlet diameter with separate variation of several basic parameters for simple nontwisted counterrotating rectangular vortex generators over a considerable range of inlet-boundary-layer thickness. The maximum values of static-pressure rise were determined for angle of attack, spacing, aspect ratio, and span-to-inlet boundary-layer thickness. Results for the diffuser with no vortex generators, effec… more
Date: May 22, 1952
Creator: Valentine, E. Floyd & Carroll, Raymond B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Wind-Tunnel Results of an Investigation of the Flutter of Sweptback- and Triangular-Wing Models at Mach Number 1.3

Description: Memorandum presenting flutter tests of untapered, low-aspect-ratio, sweptback-wing models and of triangular-wing models of solid magnesium, aluminum, and steel construction in an intermittent supersonic wind tunnel at Mach number 1.3. Flutter data are presented for 31 sweptback wing models and 24 triangular-wing models. The flutter boundaries are indicated on plots of streamwise thickness ratio and aspect ratio.
Date: May 22, 1952
Creator: Tuovila, W. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Method of Estimating the Stick-Fixed Longitudinal Stability of Wing-Fuselage Configurations Having Unswept or Swept Wings

Description: Memorandum presenting a method for calculating the stick-fixed longitudinal stability of a wing-fuselage configuration at subcritical Mach numbers. The method applies to unswept- and swept-wing configurations. The stability parameters estimated by the method show reasonable agreement with the experimental values for the 23 configurations used in the comparison.
Date: January 22, 1952
Creator: McLaughlin, Milton D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of three types of blunt trailing edges on the aerodynamic characteristics of a plane tapered wing of aspect ratio 3.1, with a 3-percent- thick biconvex section

Description: Report presenting effects of wing trailing-edge bluntness on aerodynamic characteristics of a wing-body combination at a range of Mach numbers and Reynolds numbers. Modifications were made to the rear half of a basic plane tapered wing of aspect ratio 3.1 and a 3-percent-thick, circular-arc, biconvex section with three types of trailing-edge shapes. Results regarding the lift characteristics, pitching-moment characteristics, drag characteristics, and maximum lift-drag ratio are provided.
Date: July 22, 1952
Creator: Dugan, Duane W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Shielded Total-Pressure Tube at Transonic Speeds

Description: Report presenting testing of a shielded total-pressure tube with a curved venturi entry in order to obtain the variation of total-pressure error with angle of attack from a range of 0 to 60 degrees and for a range of Mach numbers. The critical angle was found to vary from about 57 degrees at Mach number 0.90 to 56 degrees at Mach number 1.10.
Date: January 22, 1952
Creator: Gracey, William; Pearson, Albin O. & Russell, Walter R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Summary of some effective aerodynamic twisting-moment coefficients of various wing-control configurations at Mach numbers from 0.6 to 1.7 as determined from rocket-powered models

Description: A summary of some effective aerodynamic twisting-moment coefficients of various wing-control configurations for use at a range of Mach numbers. The values obtained were determined by the combined use of experimentally determined free-flight data and subsonic aerodynamic theory.
Date: January 22, 1952
Creator: Strass, H. Kurt
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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