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Creep Strength of Uranium Alloys at 1500 and 1800 F

Description: Abstract:"The creep resistance of various uranium binary alloys was investigated at 1500 and 1800 F in vacuum. Tests were made on alloys of uranium with beryllium, columbium, molybdenum, tantalum, titanium, and zirconium and on molybdenum-UO2 composites. Of the alloys examined, those of the uranium-molybdenum system exhibited the best creep resistance. At 1500 F, creep rates of about 0.005%/hr were produced in uranium-molybdenum alloys by a stress of 2500 psi and, at 1800 F, similar creep rates… more
Date: May 28, 1953
Creator: Saller, Henry A.; Stacy, J. T.; Eddy, N. S. & Klebanow, H. L.
Partner: UNT Libraries Government Documents Department
open access

Calibration of a Peak Current Gage Developed at Sandia Corporation

Description: Abstract: Methods are presented for calibrating a peak current gage which was developed at Sandia in the spring of 1953.
Date: December 28, 1953
Creator: Baker, G. E.; Looney, T. C.; Pafford, W. B. & Reis, George E.
Partner: UNT Libraries Government Documents Department
open access

Miscellaneous Studies of Fluorocarbons and Fluorocarbon-Uranium Hexafluoride Systems

Description: During the exploration of the possible use of an extraction process for the separation of gaseous cascade impurities from uranium hexafluoride, a number of short exploratory studies were carried out. These included (1) experimental determination of the vapor pressure and liquid density of perfluorodibutylcylicether, (2) calculation of the liquid vapor-equilibria of the systes perfluoro-n-pentane-uranium hexafluoride and 1,2-dichlorohexafluoropropane-uranium hexafluoride, and (3) derivation of e… more
Date: December 28, 1953
Creator: Posey, J. C. & Barber, E. J.
Partner: UNT Libraries Government Documents Department
open access

Results of a Power-on Flight of a 1/10-Scale Rocket-Propelled Model of the Convair XF2Y-1 Airplane at a Mach Number of 1.53

Description: Report discussing testing on a scale model of the Convair XF2Y-1 airplane with solid-fuel rocket motors that simulate full-scale turbojet-engine characteristics at a height of 35,000 feet with full afterburning at Mach number 1.53. The model was found to have dynamic lateral instability, but these results were not likely to be found in a full-scale airplane. Information about the pitching moment, directional stability, lift-curve slope, and drag coefficients is provided.
Date: September 28, 1953
Creator: Bland, William M., Jr. & Nelson, Robert L.
Partner: UNT Libraries Government Documents Department
open access

Matched performance characteristics of a 16-stage axial-flow compressor and a 3-stage turbine

Description: Report presenting component performance data for one modification of a 16-stage compressor and a 3-stage turbine to determine the matched performance characteristics of an engine with those components. The compressor surge line and infinite exhaust-nozzle-area equilibrium operating line restricted the region of matched compressor-turbine operation. Results regarding the engine operation with modified compressor and three-stage turbine, effect of leakage on engine operation, component efficienci… more
Date: April 28, 1953
Creator: Rebeske, John J., Jr. & Dugan, James F., Jr.
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of Pressures on Base and Rear Part of Fuselage of the Bell X-1 Research Airplane at Transonic Speeds, Including Power Effects

Description: Report presenting measurements made on the Bell X-1 airplane to determine the pressures on the fuselage base and rear portion of the fuselage during level flight. Measurements were made in the power-off condition and with the engine operating. Information about the power-off pressures and jet effects is provided.
Date: January 28, 1953
Creator: Knapp, Ronald J. & Johnson, Wallace E.
Partner: UNT Libraries Government Documents Department
open access

Some Measurements of the Buffet Region of a Swept-Wing Research Airplane During Flight to Supersonic Mach Numbers

Description: Report presenting measurements of the intensity of buffeting experienced by the Douglas D-558-II research airplane at a range of Mach numbers. Buffeting was encountered at both subsonic and supersonic Mach numbers and the intensity of the buffeting varied with Mach number and airplane normal-force coefficient.
Date: May 28, 1953
Creator: Baker, Thomas F.
Partner: UNT Libraries Government Documents Department
open access

A correlation by means of transonic similarity rules of the experimentally determined characteristics of 18 cambered wings of rectangular plan form

Description: The effects of one type of camber on the aerodynamic characteristics of rectangular wings at high subsonic and transonic speeds have been studied by applying the transonic similarity rules to the correlation of experimental data for a series of 18 cambered wings having NACA 63A2XX and 63A4XX sections, aspect ratios from 1 to 4, and thicknesses from 4 to 8 percent. The data were obtained by use of a transonic bump over a Mach number range of 0.6 to 1.1.
Date: September 28, 1953
Creator: McDevitt, John B.
Partner: UNT Libraries Government Documents Department
open access

Data on Spoiler-Type Ailerons

Description: Report presenting information about spoiler-type ailerons, which are of interest because they give high reversal speeds for the thin, flexible wings now used. A bibliography on spoiler-type controls is also provided.
Date: October 28, 1953
Creator: Lowry, John G.
Partner: UNT Libraries Government Documents Department
open access

Effects of wing elasticity on the aerodynamic characteristics of an airplane configuration having 45 degrees sweptback wings as obtained from free-flight rocket-model tests at transonic speeds

Description: Flight testing at transonic speeds occurred on two rocket-propelled models of an airplane configuration with 45 degree sweptback wings of aspect ratio 4 and with different stiffnesses. Longitudinal stability, lift, and drag characteristics were determined by analysis of the response of the models to disturbances in pitch. Results regarding lift, model vibrations, aeroelastic effects on lift, static stability, damping in pitch, and drag are provided.
Date: January 28, 1953
Creator: Vitale, A. James
Partner: UNT Libraries Government Documents Department
open access

A transonic wind-tunnel investigation of the effects of body indentation, as specified by the transonic drag-rise rule, on the aerodynamic characteristics and flow phenomena of an unswept-wing-body combination

Description: Report presenting comparisons of the aerodynamic characteristics and flow phenomena at transonic speeds for two unswept zero-taper-ratio wing-body combinations. The first had a cylindrical afterbody, while the second had an indented afterbody in the region of the wing-body juncture. Results regarding force characteristics, flow surveys, and an interpretation of the results are provided.
Date: January 28, 1953
Creator: Williams, Claude V.
Partner: UNT Libraries Government Documents Department
open access

A transonic wind-tunnel investigation of the longitudinal stability and control characteristics of a 0.09-scale model of the Bell X-5 research airplane and comparison with flight

Description: Report presenting an investigation conducted in the 8-foot transonic tunnel to determine the longitudinal stability and control characteristics of a 0.09-scale model of the Bell X-5 research airplane. Lift, drag, pitching-moment, elevator hinge-moment, and pressure-distribution results are presented for a range of Mach and Reynolds numbers. Results regarding lift and drag characteristics, longitudinal stability and control characteristics, dynamic-response characteristics, elevator hinge-moment… more
Date: October 28, 1953
Creator: Bielat, Ralph P. & Campbell, George S.
Partner: UNT Libraries Government Documents Department
open access

Free-Fall Measurements of the Effects of Wing-Body Interference on the Transonic Drag Characteristics of Swept-Wing-Slender-Body Configurations

Description: Report presenting the results of testing of bodies and wing-body combinations by the free-fall method in order to provide information about drag characteristics of airplanes and their component parts at transonic speeds. Two models with a fineness-ratio-12 body of revolution with 45 degree sweptback wings located at different positions were dropped and equipped with improved drag measuring instrumentation and pressure measuring orifices on the portion of the body expected to be influenced by th… more
Date: May 28, 1953
Creator: Kurbjun, Max C. & Thompson, Jim Rogers
Partner: UNT Libraries Government Documents Department
open access

Investigation of a 10-Stage Subsonic Axial-Flow Research Compressor 4: Individual Stage Performance Characteristics

Description: Report presenting a determination of the individual stage performance for a 10-stage axial-flow compressor from circumferentially fixed radial rake measurements of total temperature and total pressure obtained at the discharge of each stage. Results regarding compressor performance, stage performance, and some general remarks are provided.
Date: April 28, 1953
Creator: Budinger, Ray E. & Serovy, George K.
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Effects of Wing and Tail Modifications on the Low-Speed Stability Characteristics of a Model Having a Thin 40 Degree Swept Wing of Aspect Ratio 3.5

Description: Report presenting an investigation of the effects of wing and tail modifications on the low-speed stability characteristics of a model with thin 40 degree swept wings of aspect ratio 3.5. The main purpose was to improve some of the undesirable longitudinal stability characteristics observed in flight of several airplanes with similar wing geometry. The use of flaps, the position of the horizontal tail, and the use of chord extensions are all explored as possible solutions.
Date: April 28, 1953
Creator: Weil, Joseph; Sleeman, William C., Jr. & Byrnes, Andrew L., Jr.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation at High Subsonic Speeds of the Static Longitudinal and Static Lateral Stability Characteristics of a Wing-Fuselage Combination Having a Triangular Wing of Aspect Ratio 2.31 and an NACA 65A003 Airfoil

Description: Report presenting an investigation in the high-speed tunnel to determine the static longitudinal and static lateral stability characteristics of a wing-fuselage combination with a triangular wing with an aspect ratio of 2.31 and an NACA 65A003 airfoil section. The tests occurred over a range of Mach numbers from 0.40 and 0.95 and separate testing was also conducted with small notches added to the leading edge of the wings.
Date: August 28, 1953
Creator: Wiggins, James W.
Partner: UNT Libraries Government Documents Department
open access

Permissible limits for reactor cooling water assimilated by humans

Description: A permissible limit for the release of waste cooling water from the Hanford reactors into the Columbia River must be determined not only from the effect on humans of assimilation of the radioactive isotopes in the water, but also from the effects of temperature, submersion dose, and metabolism of radioisotopes on fish and other aquatic life in the river, and of concentration in plants of the radioisotopes in irrigation water from the river, with eventual consequences to humans. This report deri… more
Date: May 28, 1953
Creator: Clukey, H. V.
Partner: UNT Libraries Government Documents Department
open access

Process Test MR-105-15, Production increases by the use of venturi orifices

Description: Process Test MR-105-14 presented the basis for the use of supplemental and venturi orifices in certain regions of a reactor operating in accordance with the scram before boiling limit, and provided for the reactor testing of the supplemental orifice. It is the purpose of the test, described in this report to demonstrate the feasibility of using venturi orifices on a reactor so that maximum production gains may be achieved under this new limit.
Date: July 28, 1953
Creator: Robb, J. E.
Partner: UNT Libraries Government Documents Department
open access

Studies on Cell Division, 1. Alpha Radiation as a Division Inhibiting Agent

Description: Report discussing a study aimed at learning about cell division and the effects of radiation alpha radiation on the process of cell division. This was done by correlating changes in the biochemical state of cells and the inhibition of cell division. Materials and methods are included as well as experimental results and data.
Date: April 28, 1953
Creator: Spoerl, Edward S. & Balske, R. J.
Partner: UNT Libraries Government Documents Department
open access

Remarks on Reactivity Control in Light Water Moderated Reactors

Description: Report discussing the effects of thermal diffusion length and certain details in the design of light water moderated reactors and their effect on reactivity.
Date: May 28, 1953
Creator: Stoker, R. L.
Partner: UNT Libraries Government Documents Department
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