Refractories for Continuous Reduction of Uranium (open access)

Refractories for Continuous Reduction of Uranium

Report presenting a study that evaluates various types of refractories for use in a refractory-lined vessel that would be used for continuous reduction of uranium tetrafluoride to uranium metal.
Date: February 27, 1956
Creator: Smalley, Allison K.; Hyde, Collin; Allison, Adrian G. & Duckworth, Winston Howard
System: The UNT Digital Library
Aircraft Nuclear Propulsion Project Quarterly Progress Report for Period Ending December 10, 1950 (open access)

Aircraft Nuclear Propulsion Project Quarterly Progress Report for Period Ending December 10, 1950

Technical report detailing expansion of the Aircraft Nuclear Propulsion at the Oak Ridge National Laboratory. Major facilities completed at this time were the Shielding Rector, the ANP Critical Facility, and the 86-in. Cyclotron. Outlines further need for radiation damage studies. [From Summary]
Date: February 27, 1951
Creator: Briant, R. C.; Ellis, C. B. & Cottrell, W. B.
System: The UNT Digital Library
A Method for the Analysis of Radionuclide Mixture Using a Gamma-Beta Scintillation Spectrometer (open access)

A Method for the Analysis of Radionuclide Mixture Using a Gamma-Beta Scintillation Spectrometer

The following report describes a beta and gamma scintillation detector similar to what was used in previous decay studies, yet was modified to make it suitable for the analysis of mixtures of radio-nuclides.
Date: February 27, 1953
Creator: Leboeuf, M. B. & Connally, R. E.
System: The UNT Digital Library
Beneficiation of Monument Number 2 Ore Apache County, Arizona (open access)

Beneficiation of Monument Number 2 Ore Apache County, Arizona

From introduction: The Monument No. 2 mine is in the Navajo Indian Reservation, Apache County, Arizona, about 20 miles southwest from the San Juan River at Mexican Hat, Utah, and 26 miles southwest from Mexican Water, Arizona. The property has been operated, since its discovery, by Vanadium Corporation of America, which holds a 10-year mining lease, granted through the Interior Department, to 43 acres of ground. History of the discovery of the deposit is vague, but reportedly it was first seen around 1942 by a Navajo who mentioned the occurrence to Harry Goulding, Indian trader, who in turn advised D. W. Viles of Vanadium Corporation of America. Minor portions of the deposit are held by Cato Sells and Harvey Black, Navajos, under mining permits issued by the Navajo Tribal Council. The Sells acreage is being operated by Climax Uranium Corporation.
Date: February 27, 1952
Creator: Sheridan, M. J.
System: The UNT Digital Library
Aerodynamic principles for the design of jet-engine induction systems (open access)

Aerodynamic principles for the design of jet-engine induction systems

From Introduction: "It is the purpose of this report to assemble principles of induction-system design for flight to a Mach number of 2 and to use existing data to show the consequences of compromising them."
Date: February 27, 1956
Creator: Davis, Wallace F. & Scherrer, Richard
System: The UNT Digital Library
Tabulated pressure data for several flap-type trailing edge controls on a trapezoidal wing at Mach numbers of 1.61 and 2.01 (open access)

Tabulated pressure data for several flap-type trailing edge controls on a trapezoidal wing at Mach numbers of 1.61 and 2.01

Report presenting an investigation at two Mach numbers for a range of Reynolds numbers to determine the pressure distributions at several spanwise stations 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. The report contains the tabulated pressure data for the complete range of test variables.
Date: February 27, 1956
Creator: Lord, Douglas R. & Czarnecki, K. R.
System: The UNT Digital Library
Aerodynamic Principles for the Design of Jet-Engine Induction Systems (open access)

Aerodynamic Principles for the Design of Jet-Engine Induction Systems

Jet engine induction systems investigations and relationship of air inlets, drag, airframe, pressure recovery, flow and interferences.
Date: February 27, 1956
Creator: Davis, Wallace F. & Scherrer, Richard
System: The UNT Digital Library
High-speed aerodynamic characteristics of horn and overhang balances on a full-scale elevator (open access)

High-speed aerodynamic characteristics of horn and overhang balances on a full-scale elevator

Report presenting high-speed wind tunnel testing of horn- and overhang-balance elevators on a full-scale, semispan, horizontal tail. The effects of unshielding the horn and unsealing the overhang were investigated. Results regarding aerodynamic characteristics, distortions of the tail, and critical Mach numbers are provided.
Date: February 27, 1948
Creator: Cleary, Joseph W. & Krumm, Walter J.
System: The UNT Digital Library
Turbojet-engine evaluation of AISI 321 and AISI 347 stainless steels as nozzle-blade materials (open access)

Turbojet-engine evaluation of AISI 321 and AISI 347 stainless steels as nozzle-blade materials

Report presenting an investigation to evaluate the engine service performance of nozzle-diaphragm blades of AISI 321 and AISI 347 stainless steels. Data were obtained from three nozzle diaphragms alternately bladed with each of the two materials. Results regarding a visual inspection, a metallurgical examination, the mechanism of cracking, and the classification of failures are provided.
Date: February 27, 1950
Creator: Garrett, Floyd B. & Yaker, Charles
System: The UNT Digital Library
Transonic Characteristics of a 45 Degree Sweptback Wing-Fuselage Combination: Effect of Longitudinal Wing Position and Division of Wing and Fuselage Forces and Moments (open access)

Transonic Characteristics of a 45 Degree Sweptback Wing-Fuselage Combination: Effect of Longitudinal Wing Position and Division of Wing and Fuselage Forces and Moments

Report presenting an investigation on a body of revolution with a sweptback wing with a 0.25-mean-aerodynamic-chord point at the maximum body diameter and 1.2 mean aerodynamic chords behind the maximum diameter. The fuselage had a fineness ratio of 10, a 45 degree swept wing with an aspect ratio of 4.0, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Lift, drag, pitching moments, and angles of attack were measured at a range of Mach numbers.
Date: February 27, 1953
Creator: Hallissy, Joseph M. & Bowman, Donald R.
System: The UNT Digital Library
Pressure Recovery, Drag, and Subcritical Stability Characteristics of Three Conical Supersonic Diffusers at Stream Mach Numbers From 1.7 to 2.0 (open access)

Pressure Recovery, Drag, and Subcritical Stability Characteristics of Three Conical Supersonic Diffusers at Stream Mach Numbers From 1.7 to 2.0

A study of a 20 degree and a 25 degree half-angle high mass-flow ratio conical supersonic inlet was made on a 16-inch ram jet in the 8- by 6-foot supersonic tunnel. A greater range of stable subcritical operation was obtained with the low mass-flow ratio inlets; a greater range was obtained with the 25 degree than with the 20 degree half-angle low mass-flow ratio inlet. The high mass-flow ratio inlet had the least drag.
Date: February 27, 1952
Creator: Nussdorfer, Theodore J.; Obery, Leonard J. & Englert, Gerald W.
System: The UNT Digital Library
Preliminary Investigation of the Combustion of Pentaborane and Diborane in a Turbojet Combustor at Simulated Altitude Conditions (open access)

Preliminary Investigation of the Combustion of Pentaborane and Diborane in a Turbojet Combustor at Simulated Altitude Conditions

Report presenting an investigation to determine the combustion characteristics of pentaborane and diborane in a turbojet combustor. Four different test conditions were explored, which varied in inlet total pressure, temperature, and simulated flight conditions. Results regarding the combustor itself and performance of diborane fuel at high altitude are provided.
Date: February 27, 1957
Creator: Gibbs, J. B.; Kaufman, W. B. & Branstetter, J. R.
System: The UNT Digital Library
Outline of the Geology of the U12b.10 Tunnel, Nevada Test Site, Nye County, Nevada (open access)

Outline of the Geology of the U12b.10 Tunnel, Nevada Test Site, Nye County, Nevada

This report briefly describes the geological data of the U12b.10 tunnel at the Nevada Test Site.
Date: February 27, 1963
Creator: Emerick, W. L.; Snyder, R. P. & Bowers, William E.
System: The UNT Digital Library
The Counting Efficiency of Pa²³³ (open access)

The Counting Efficiency of Pa²³³

Abstract: "The counting efficiency of Pa²³³ has been determined by comparison of the counting rate of Pa²³³, under stated conditions, with the disintegration rate of U²³³ produced by Pa²³³ decay."
Date: February 27, 1951
Creator: Karraker, David George, 1923-
System: The UNT Digital Library
Summary of Research on Experimental Refractory Bodies of High-Melting Nitrides, Carbides, and Uranium Dioxide (open access)

Summary of Research on Experimental Refractory Bodies of High-Melting Nitrides, Carbides, and Uranium Dioxide

First 31 pages of a quarterly report discussing the progress made on research projects during the period from October 1950 to December 1950. This section of the report discusses progress on studies of the metabolic properties of various elements.
Date: February 27, 1951
Creator: Chiotti, P. & Hamilton, J. G.
System: The UNT Digital Library
Recovery of Tuballoy From Solutions Containing Fluoride Ion (open access)

Recovery of Tuballoy From Solutions Containing Fluoride Ion

"Another extraction method is described herein for the quantitative recovery of tuballoy from solutions containing high concentrations of fluoride ion. The method consists of the addition of aluminum nitrate to the solution in order to complex the fluoride ion, followed by saturation with calcium nitrate and extraction of the tuballoy with dibutyl carbitol.
Date: February 27, 1945
Creator: Smith, Fred; Tober, Frank W., 1919-1995; Lord, E. J.; Andrews, L. J. & Gates, J. W., Jr.
System: The UNT Digital Library
Preliminary Data on Fallout From the Fall 1961 USSR Test Series: Staff Report (open access)

Preliminary Data on Fallout From the Fall 1961 USSR Test Series: Staff Report

From introduction: "Following the USSR announcement of its intention to resume testing, arrangements were made for the three stations collecting individual rainfall samples to begin analyses for short-lived nuclides. Some of the data are now available and are reported here." From Data: "The available data, including samples for Houston, Texas and Louisville, Kentucky are given in the tables at the end of this report."
Date: February 27, 1962
Creator: U.S. Atomic Energy Commission. Health and Safety Laboratory.
System: The UNT Digital Library
Pressure Recovery, Drag, and Subcritical Stability Characteristics of Conical Supersonic Diffusers With Boundary-Layer Removal (open access)

Pressure Recovery, Drag, and Subcritical Stability Characteristics of Conical Supersonic Diffusers With Boundary-Layer Removal

A study of two 20 degrees half-angle, low mass-flow ratio conical supersonic inlets with cone boundary-layer bleed was made on a 16-inch ram-jet engine in the Lewis 8- by 6-foot supersonic wind tunnel. A greater stable subcritical range of operation was obtained with the bleed inlets than with the corresponding inlet without boundary-layer bleed. The drag added by the bleed system was small.
Date: February 27, 1952
Creator: Obery, Leonard J.; Englert, Gerald W. & Nussdorfer, Theodore J.
System: The UNT Digital Library
Comparison of Turbojet-Engine Altitude Performance Characteristics and Ignition Limits With MIL-F-5624A Fuel, Grades JP-3 and JP-4 (open access)

Comparison of Turbojet-Engine Altitude Performance Characteristics and Ignition Limits With MIL-F-5624A Fuel, Grades JP-3 and JP-4

The performance of MIL-F-5624A fuels, grades JP-3 and JP-4, was investigated in an axial-flow turbojet engine over a range of altitude conditions of 10,000 to 55,000 feet. Examination of the fuel flow, combustion efficiency, and net thrust specific fuel consumption showed the grade JP-4 fuel to be slightly inferior to the grade JP-3 fuel, although the altitude ignition limits were essentially equal for the two fuels over a range of flight Mach numbers and fuel-inlet temperatures.
Date: February 27, 1952
Creator: Braithwaite, Willis M. & Renas, Paul E.
System: The UNT Digital Library
Experimental investigation of ejector-nozzle metal temperatures (open access)

Experimental investigation of ejector-nozzle metal temperatures

Metal temperatures were obtained on a full-scale ejector nozzle installed on an afterburner operating at exhaust-gas temperatures up to 3450 degrees R. A favorable afterburner-outlet temperature profile helped keep the primary-jet nozzle components cool. The ejector shroud temperatures were much more sensitive to secondary airflow than were temperatures on the primary-jet nozzle.
Date: February 27, 1957
Creator: Shillito, Thomas B. & Koffel, William K.
System: The UNT Digital Library
Comparison of Combustion Reactivity of Ethyldecaborane Fuels With Typical Hydrocarbon Fuels on Basis of Spray Flammability Limits of Fuel-Rich Mists and Calculated Lean-Limit Flame Temperatures for Fuel Vapor-Air Systems (open access)

Comparison of Combustion Reactivity of Ethyldecaborane Fuels With Typical Hydrocarbon Fuels on Basis of Spray Flammability Limits of Fuel-Rich Mists and Calculated Lean-Limit Flame Temperatures for Fuel Vapor-Air Systems

From Summary: "The spray flammability limits of various high-energy fuels and hydrocarbon fuels were determined experimentally in an apparatus which measured the minimum percent of oxygen by volume that would permit the ignition of a particular fuel. The fluids investigated were ethyldecaboranes, aliphatic hydrocarbons, olefins, aromatic hydrocarbons, and esters."
Date: February 27, 1957
Creator: Wise, Paul H. & Lipschitz, Abraham
System: The UNT Digital Library
A summary of the longitudinal and lateral stability and control characteristics obtained from rocket-model tests of a swept-wing fighter-type airplane at Mach numbers from 0.5 to 1.9 (open access)

A summary of the longitudinal and lateral stability and control characteristics obtained from rocket-model tests of a swept-wing fighter-type airplane at Mach numbers from 0.5 to 1.9

Report presenting a flight investigation of a swept-wing fighter-type airplane to determine drag coefficients, longitudinal and lateral stability derivatives, effects of aeroelasticity on rolling effectiveness, and the effect of the engine jet exhaust on the trim characteristics over the range of Mach numbers.
Date: February 27, 1957
Creator: Mitcham, Grady L.
System: The UNT Digital Library
Lateral Stability Characteristics of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane (open access)

Lateral Stability Characteristics of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane

"The XF-12 airplane is a high-performance photo-reconnaissance aircraft designed for the Army Air Forces by the Republic Aviation Corporation. An investigation of a 1/8.33 - scale powered model was made in the Langley l9-foot pressure tunnel to obtain information relative to the aerodynamic design of the airplane. The model was tested with and without the original vertical tail. and with two revised tails. For the revised tail no. 1, the span of the original vertical .tail was increased about 15 percent and the portion of the vertical tail between the stabilizer and fuselage behind the rudder hinge line was allowed to deflect simultaneously with the main rudder" (p. 1).
Date: February 27, 1947
Creator: Pepper, Edward & Foster, Gerald V.
System: The UNT Digital Library
The effect of high solidity on propeller characteristics at high forward speeds from wind-tunnel tests of the NACA 4-(3)(06.3)-06 and NACA 4-(3)(06.4)-09 two-blade propellers (open access)

The effect of high solidity on propeller characteristics at high forward speeds from wind-tunnel tests of the NACA 4-(3)(06.3)-06 and NACA 4-(3)(06.4)-09 two-blade propellers

From Summary: "Tests of two-blade propellers having the NACA 4-(3)(06.3)-06 and NACA 4-(3)(06.4)-09 blade designs (blade activity factors of 179 and 263, respectively) have been made in the Langley 8-foot high-speed tunnel through a range of blade angle from 20 degrees to 70 degrees for free-stream Mach numbers from 0.165 to 0.725 to determine the effects of high solidity and compressibility on propeller characteristics. The tests are part of a general investigation of propellers at high forward speeds. Results previously reported for similar tests of two-blade propellers having the NACA 4-308-03 and NACA 4-308-045 blade designs (blade activity factors of 87 and 133, respectively) are included for comparison. The results showed that the 0.06- and 0.09-solidity blades, although producing efficiencies of the order of 90 percent, were less efficient than blades of conventional solidity."
Date: February 27, 1947
Creator: Delano, James B.
System: The UNT Digital Library