Serial/Series Title
BNL (Series)
25
Brookhaven National Laboratory Reports
25
Atomic Energy Commission Reports
23
AEC research and development report
10
NACA Research Memorandums
9
North American Aviation Reports
8
HW (Series)
5
Hanford Works Reports
5
NACA Technical Reports
4
Report (U.S. Atomic Energy Commission)
4
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Salt Bath Heat Transfer Rates for Uranium Plate
Experiment to study temperature conditions during a five-minute heating cycle in the annealing of uranium sheets used as fissile material.
Date:
February 1, 1962
Creator:
Burditt, R. B.
System:
The UNT Digital Library
Transient Temperature Simulation of Reactor Primary Loop
Report issued by the APDA over simulator studies conducted on their Developmental Fast Breeder Reactor. The simulator studies were "designed to predict both the normal and abnormal operating characteristics of the APDA Developmental Fast Breeder Reactor" (p. 1). This report includes tables, and illustrations.
Date:
February 1, 1956
Creator:
Olson, Richard G. & Ritchie, Donald J.
System:
The UNT Digital Library
A comparison of two methods for the spectrochemical analysis of plutonium
Report describing the methods, discrepancies, accuracy of methods, and conclusions of two different analytical methods of spectrochemical analysis of plutionium.
Date:
February 1, 1950
Creator:
Van Tuyl, H. H.
System:
The UNT Digital Library
Progress Report for the Month of January, 1952
This progress report of the Battelle Memorial Institute covers information in many categories. These include development of ceramic fuel elements, general ceramics, uranium and its alloys, thorium and its alloys, development of metallic fuel elements and assemblies, metals and alloys for reactor components, miscellaneous metallurgical work, liquid coolants and fuels, reactor engineering studies, and mechanism development.
Date:
February 1, 1952
Creator:
Russell, H. W.; Nelson, H. R. & Dayton, R. W.
System:
The UNT Digital Library
Dynamics of the Supercritical Water Reactor
From introduction: "The work described in this report was carried out as part of the feasibility study (ORNL-117) of a supercritical water reactor (SCWR) for use in nuclear propulsion of aircraft. The object of this work was to study the dynamic behavior of a particular design of supercritical water reactor. Numerical results are presented in Appendix I."
Date:
February 1, 1953
Creator:
Goertzel, Gerald, 1919-; Shapiro, Mathew M. & Soodak, Harry
System:
The UNT Digital Library
The Elimination of Microwave Reflections
Abstract: "The reflections of microwaves from the walls of a plasma-containing vessel are studied. The probable cause of the reflections is discussed, and several suggestions are made for eliminating the reflections from the waveguide in the vessel and particularly from the pyrex vessel wall and copper tubing surrounding the pyrex. Quarter-wave-thick carbon-filled plastics or glasses having a very low vapor pressure room most promising when placed inside the pyrex cylinder. BaTiO3 appears to be an excellent material when placed outside the vacuum."
Date:
February 1, 1955
Creator:
Beard, David
System:
The UNT Digital Library
Organic Moderated Reactor Experiment : Safeguards Summary
Abstract: This report presents a description of the Organic Moderated Reactor Experiment (OMRE), of the hazards associated with this experiment, and all of the safeguards taken to ensure the safety of the operating personnel and the population of the surrounding area.
Date:
February 1, 1958
Creator:
Sletten, H. L. & Blue, L. R.
System:
The UNT Digital Library
Irradiation Swelling, Phase Reversion, and Intergranular Cracking of U-10 wt % Mo Fuel Alloy
Abstract: A fuel development program has been conducted, to investigate the behavior of U-10 wt% Mo alloy at the fission rates and temperatures anticipated in Core I of the Hallam Nuclear Power Facility.
Date:
February 1, 1965
Creator:
Willard, R. M. & Schmitt, A. R.
System:
The UNT Digital Library
The NAA 47 U - 10 Mo Fuel Irradiation Program for HNPF Core 1
Abstract: Atomics International conducted a fuel irradiation program to investigate and define the behavior of U-10 Mo fuel at the temperatures and fission rates anticipated in Hallam Nuclear Power Facility (HNPF) Core I.
Date:
February 1, 1965
Creator:
Schmitt, A. R.; Willard, R. M. & Magnus, D. K.
System:
The UNT Digital Library
Performance of Cesium Thermionic Diodes Operated in Series-Parallel Circuits
Introduction: The purpose of this experiment is to determine the loss of electrical power output due to operating many unequally-heated cesium diodes, connected in series and parallel circuits.
Date:
February 1, 1963
Creator:
Holland, J. W.
System:
The UNT Digital Library
Final Design of Sodium-Heated, Modular, Steam Generators for the SCTI
Abstract: The following report covers the final design of the modular steam generators.
Date:
February 1, 1965
Creator:
Casey, D. F.; Hammer, J. J.; Logan, D. & Williams, M. C.
System:
The UNT Digital Library
Metallurgical Laboratory, Chemical Research - Radiation Chemistry, Report for the Period Ending January 15, 1945
Technical report with short reports covering (1) Effect of radiation on water and aqueous systems; (2) Effect of neutrons on graphite; (3) Effect of radiation on solid compounds; and (4) Scattering, stopping-power, ion-pair production, etc.
Date:
February 1, 1945
Creator:
Burton, Milton, 1902- & Allen, A. O. (Augustine O.)
System:
The UNT Digital Library
A Conceptual Design of a Thorium-Uranium (233) Power Breeder Reactor
From abstract: A conceptual design study has been performed for a sodium cooled, graphite moderated, thermal power-breeder reactor utilizing the Thorium-Uranium 233 breeding cycle. Several aspects of the design of the system are considered but no attempt has been made to supply all the details. It appears that the design presented is feasible and will allow the production of economic power as well as full utilization of thorium resources.
Date:
February 1, 1954
Creator:
Henrie, J. O. & Weisner, E. F.
System:
The UNT Digital Library
Comparative Tests of the Strength and Tightness of Commercial Flush Rivets of One Type and NACA Flush Rivets in Machine-Countersunk and Counterpunched Joints
Report discusses an investigation that was conducted to compare the strength and tightness of machine-countersunk flush-riveted joints assembled with NACA flush rivets and a type of commercial flush rivet. A comparison was also generated between the strength and tightness of counterpunched flush-riveted joints assembled with the same types of rivet. NACA's flush-riveted joints tended to be stronger and tighter than the commercial joints.
Date:
February 1, 1944
Creator:
Mandel, Merven W.
System:
The UNT Digital Library
Performance of Several Half-Conical Side Inlets at Supersonic and Subsonic Speeds
Report discussing an evaluation of a series of half-conical side inlets mounted on the fuselage of a supersonic aircraft at various Mach numbers. Information about the maximum total-pressure recovery, asymmetrical operation of the twin-duct system, potential reduction in stable mass-flow range, boundary-layer diverter height, and engine mass flow is described.
Date:
February 1, 1956
Creator:
Stitt, Leonard E.; Cubbison, Robert W. & Flaherty, Richard J.
System:
The UNT Digital Library
Afterburner Performance With Combustion-Chamber Lengths From 10 to 62 Inches at Several Afterburner-Inlet Temperatures
Effect of variation of combustion chamber length and inlet temperature on low pressure-loss sea level afterburner. A 70-percentage-point reduction in combustion efficiency resulted when the combustion-chamber length was reduced from 62 to 10 inches.
Date:
February 1, 1956
Creator:
Ciepluch, Carl C.; Velie, Wallace W. & Burley, Richard R.
System:
The UNT Digital Library
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane triangular wing of aspect ratio 2 with NACA 0008-63 section
Report presenting an investigation of a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0008-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date:
February 1, 1951
Creator:
Smith, Donald W. & Heitmeyer, John C.
System:
The UNT Digital Library
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane triangular wing of aspect ratio 2 with NACA 0005-63 section
Report presenting a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0005-63 sections in streamwise planes has been investigated at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date:
February 1, 1951
Creator:
Smith, Donald W. & Heitmeyer, John C.
System:
The UNT Digital Library
Calculated Performance of a Direct-Air Nuclear Turbojet-Powered Airplane Using a Split-Flow Reactor and a Separated-Type Shield
Memorandum presenting an analysis made to estimate the performance of a direct-air nuclear turbojet-powered airplane with a split-flow reactor and a separated-type shield. The analysis was for flight Mach numbers of 0.9 and 1.5 and covered a range of altitudes, reactor-wall temperatures, turbine-inlet temperatures, compressor pressure ratios, and airplane lift-drag ratios.
Date:
February 1, 1951
Creator:
Doyle, R. B.
System:
The UNT Digital Library
Knock-limited performance of several internal coolants
The effect of internal cooling on the knock-limited performance of an-f-28 fuel was investigated in a CFR engine, and the following internal coolants were used: (1) water, (2), methyl alcohol-water mixture, (3) ammonia-methyl alcohol-water mixture, (4) monomethylamine-water mixture, (5) dimethylamine-water mixture, and (6) trimethylamine-water mixture. Tests were run at inlet-air temperatures of 150 degrees and 250 degrees F. to indicate the temperature sensitivity of the internal-coolant solutions.
Date:
February 1, 1944
Creator:
Bellman, Donald R. & Evvard, John C.
System:
The UNT Digital Library
Investigation of the Low-Speed Aerodynamic Characteristics of a Variable-Sweep Airplane Model With a Twisted and Cambered Wing
Report presenting an investigation to determine the low-speed characteristics of a variable-sweep airplane model with a twisted and cambered wing. The wing was designed to have a uniform load distribution at a Mach number 1.10 and a lift coefficient of 0.25 and 50 degrees sweep. Results regarding lift characteristics, drag characteristics, lift-drag ratio, pitching-moment characteristics, dynamic pressure and downwash at the tail, effect of flaps, and lateral stability characteristics are provided.
Date:
February 1, 1952
Creator:
Kemp, William B., Jr.; Becht, Robert E. & Few, Albert G., Jr.
System:
The UNT Digital Library
An investigation of the aerodynamic characteristics at transonic Mach numbers of a swept-wing supersonic bomber configuration
Report presenting an investigation of the aerodynamic characteristics of a swept-wing supersonic bomber configuration conducted in the 8-foot transonic tunnel. The wing had an aspect ratio of 3.5, taper ratio of 0.2, 47 degrees of sweepback of the 0.25-chord line, and airfoil sections which were 5.5 percent thick parallel to the plane of symmetry. Results regarding the longitudinal force characteristics, effects of wing incidence, a modified wing, various auxiliary wing devices, and horizontal-tail height are provided.
Date:
February 1, 1956
Creator:
Bielat, Ralph P. & Cooper, J. Lawrence
System:
The UNT Digital Library
An investigation at Mach numbers of 1.41 and 2.01 of the aerodynamic characteristics of a swept-wing supersonic bomber configuration
Report presenting an investigation of a swept-wing supersonic bomber configuration in the 4- by 4-foot supersonic pressure tunnel. Testing occurred at Mach numbers of 1.41 and 2.01 and a designated Reynolds number based on the wing mean aerodynamic chord. The model had a tapered wing with an aspect ratio of 3.5, a taper ratio of 0.2, a thickness ratio of 5.5 percent and 47 degrees sweep of the quarter-chord line. The investigation included the longitudinal and lateral force characteristics and various combinations of its components, including several jet nacelle installations.
Date:
February 1, 1956
Creator:
Smith, Norman F. & Hasel, Lowell E.
System:
The UNT Digital Library
Effects of two trailing-edge controls on the aerodynamic characteristics of a rectangular wing and body combination at Mach numbers from 3.00 and 5.05
Report presenting an investigation made to determine experimentally the effects of two types of trailing-edge controls on the aerodynamic characteristics of a wing-body combination consisting of a 4-percent-thick wing of rectangular plan form and a slender body of revolution. The variations of lift coefficient with angle of attack of the flap-wing-body combination and spoiler-wing-body combination were generally nonlinear. Results regarding the trailing-edge flap control and trailing-edge spoiler controls are provided.
Date:
February 1, 1956
Creator:
Gloria, Hermilo R. & Wong, Thomas J.
System:
The UNT Digital Library