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The Pack Method for Compressive Tests of Thin Specimens of Materials Used in Thin-Wall Structures
"The strength of modern lightweight thin-wall structures is generally limited by the strength of the compression members. An adequate design of these members requires a knowledge of the compressive stress-strain graph of the thin-wall material. The "pack" method was developed at the National Bureau of Standards with the support of the National Advisory Committee for Aeronautics to make possible a determination of compressive stress-strain graphs for such material" (p. 133).
Date:
August 23, 1938
Creator:
Aitchison, C. S. & Tuckerman, L. B.
System:
The UNT Digital Library
Effect of the Performance of a Turbosupercharged Engine of an Exhaust-Gas-to-Air Heat Exchanger for Thermal Ice Prevention
This report presents the results of a flight investigation to determine the effect on the performance of a turbosupercharged engine of an exhaust-gas-to-air heat exchanger installed between the engine-exhaust collector ring and the turbosupercharger. The background, results, and discussion of the investigation are described.
Date:
August 23, 1945
Creator:
Look, Bonne C.
System:
The UNT Digital Library
100 Areas: (For technical progress letter No. 111), August 13--August 19
This technical progress report details 100 Area activities for the time period of August 13 through August 19, 1946.
Date:
August 23, 1946
Creator:
Jordan, W. E.
System:
The UNT Digital Library
A Homogeneous High Temperature Power Pile Utilizing Graphite Which Has Been Impregnated With Uranium
Thermal reactors that have a significant fraction of fissioning occurring just above thermal energies are studied. First, the thermal neutron diffusion equation is corrected for fast fission effects. The resulting diffusion equation is shown to be equivalent to the Fermi Age equation corresponding to the same physical assumptions. Next, the one delayed neutron group kinetic equations for the corrected thermal flux are given, and the life time of the thermal neutron is corrected by the average slowing down time. (auth)
Date:
August 23, 1946
Creator:
Daniels, F.
System:
The UNT Digital Library
The Metabolism of Thorium, Protoactinium, and Neptunium in the Rat
From abstract: "The distribution of carrier-free thorium, protoactinium and neptunium in the rat following intramuscular and oral administration has been studied. Oral adsorption for all three is negligible. Following parenteral administration, the skeleton is the organ showing the highest degree of prolonged and selective localization."
Date:
August 23, 1946
Creator:
Lans, H.; Scott, E. G.; Crowley, J. & Hamilton, J. G.
System:
The UNT Digital Library
THE UOBr$sub 2$ DISPROPORTIONATION EQUILIBRIUM
None
Date:
August 23, 1946
Creator:
Gregory, N.W.
System:
The UNT Digital Library
Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine 1 - Analysis of Turbine Performance
A wind tunnel investigation was conducted to determine the performance of a turbine operating as an integral part of a turbojet engine. Data was obtained while the engine was running over full operable range of speeds at various altitudes and flight mach numbers, and with four nozzles of different outlet areas.A maximum turbine efficiency of 0.875 was obtained at altitude of 15 thousand feet, Mach number 0.53, and corrected turbine speed of 5900 rpm.
Date:
August 23, 1948
Creator:
Conrad, Earl W.; Dietz, Robert O., Jr. & Golladay, Richard L.
System:
The UNT Digital Library
Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine 2 - Analysis of Compressor Performance
Compressor performance properties for two 11-stage compressors of 3000-pound-thrust axial-flow turbojet engines were determined. Data are presented for a range of simulated altitudes and a range of Mach numbers for various modifications of the engine.
Date:
August 23, 1948
Creator:
Dietz, Robert O., Jr.; Berdysz, Joseph J. & Howard, Ephraim M.
System:
The UNT Digital Library
Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine 3 - Analysis of Combustion-Chamber Performance
Combustion chamber performance properties of a 3000-pound-thrust axial-flow turbojet engine were determined. Data are presented for a range of simulated altitudes from 15,000 to 45,0000 feet and a range of Mach numbers from 0.23 to 1.05 for various modifications of the engine.
Date:
August 23, 1948
Creator:
Campbell, Carl E.
System:
The UNT Digital Library
Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, 4, Operational Characteristics
An investigation was conducted to evaluate the operational characteristics of a 3000 pound thrust axial flow turbojet engine over a range of simulated altitudes from 2000 to 50,000 feet and simulated flight Mach numbers from 0 to 1.04 throughout the operable range of engine speeds. Engine operating range, acceleration, deceleration, starting, altitude, and flight Mach number compensation of the fuel control system, and operation of the lubrication system at high and low ambient air temperatures were evaluated.
Date:
August 23, 1948
Creator:
Hawkins, W. Kent & Meyer, Carl L.
System:
The UNT Digital Library
Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, Part 5, Performance and Windmilling Drag Characteristics
"An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the performance and windmilling drag characteristics of an original and a modified turbojet engine of the same type. Data have been obtained at simulated altitudes from 5000 to 45,000 feet, simulated flight Mach numbers from 0.09 to 1.08, and engine speeds from 4000 to 12,500 rpm. Engine performance data are presented for both engines to show the effects of altitude at a flight Mach number of 0.25 and of flight Mach number at an altitude of 25,000 feet" (p. 1).
Date:
August 23, 1948
Creator:
Meyer, Carl L. & Bloomer, Harry E.
System:
The UNT Digital Library
A limit pressure coefficient and an estimation of limit forces on airfoils at supersonic speeds
Report presenting the results of an estimation of the limit forces on airfoils at supersonic speeds. The limit pressure coefficient attainable on an airfoil is shown to be about 70 percent of the pressure coefficient for a vacuum over a wide range of Mach numbers.
Date:
August 23, 1948
Creator:
Mayer, John P.
System:
The UNT Digital Library
Operating Temperatures of I-40-5 Turbojet Engine Burner Liners and the Effect of Temperature Variation on Burner-Liner Service Life
Report presenting an investigation of burner liners in a turbojet engine to determine the principal factors limiting the burner-liner service life. The investigation covered a range of engine speeds and testing was conducted to determine whether bare, ceramic-coated, or shielded thermocouples would give the most correct temperature readings.
Date:
August 23, 1948
Creator:
Wilsted, H. D.; Duffy, Robert T. & Grey, Ralph E.
System:
The UNT Digital Library
Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles 1 - Efficiency with 0.45-inch Rotor Blades
"An investigation was made of the first-stage turbine of a Mark 25 torpedo power plant to determine the performance of the unity with two nozzle configurations and a special rotor having 0.45-inch blades instead of the standard length of 0.40 inch. Both nozzles had smaller passages than the nozzles of similar shape that were previously investigated. The performance of the nozzle-blade combinations is evaluated in terms of brake, rotor, and blade efficiency as functions of blade-jet speed ratio for three pressure ratios" (p. 1).
Date:
August 23, 1949
Creator:
Schum, Harold J. & Whitney, Warren J.
System:
The UNT Digital Library
Altitude-Test-Chamber Investigation of Performance of a 28-Inch Ram-Jet Engine 1: Combustion and Operational Performance of Four Combustion-Chamber Configurations
An altitude-test-chamber investigation of a 28-inch-diameter ram-jet engine at a simulated flight Mach number of approximately 2.0 for altitudes of 40,000 to 50,000 feet was conducted at the NACA Lewis laboratory. Three different flame holders, varying in the number and size of the annular gutters, in conjunction with several fuel-injection systems were investigated. The combustion efficiency for the flame-holder fuel-injection system that provided the best over-all operational fuel-air-ratio range (0.03 to 0.075) was over 0.9 at a fuel-air ratio of about 0.065 for the altitude range investigated.
Date:
August 23, 1950
Creator:
Jones, W. L.; Shillito, T. B. & Henzel, J. G., Jr.
System:
The UNT Digital Library
The Decay of Induced Activity in Portland, Barytes, and Brookhaven Cements
The following report describes results from a study of three types of cement (Barytes, Brookhaven, and Portland) exposed in the ORNL Reactor for periods of seven and twenty-eight days.
Date:
August 23, 1950
Creator:
Bowman, W. H.; James, D. L. & Roarty, J. D.
System:
The UNT Digital Library
Influence of tube-entrance configuration on average heat-transfer coefficients and friction factors for air flowing in an Inconel tube
A heat-transfer investigation was conducted with air flowing through an electrically heated Inconel tube having either a long-approach or a right-angle-edge entrance, an inside diameter of 0.402 inch, and a length of 24 inches over a range of Reynolds numbers up to 375,000 and average inside-tube-wall temperatures up to 2000 degrees R. Good correlation of heat-transfer data was obtained for both entrances, which substantiates work previously reported. A fair correlation of friction data was obtained for both entrances. The entrance configuration had little effect on the average heat-transfer and friction coefficients.
Date:
August 23, 1950
Creator:
Lowdermilk, Warren H. & Grele, Milton D.
System:
The UNT Digital Library
Investigation of flap-type ailerons on an untapered wing having an aspect ratio of 3.7, 45 degree sweepback, and an NACA 65A009 airfoil section: Transonic-bump method
Report presenting an investigation to determine the lateral control characteristics of a 20-percent-chord flap-type aileron of various spans on a semispan wing-fuselage model in the transonic speed range. The wing of the model had 45 degrees of sweepback, an aspect ratio of 3.7, a taper ratio of 1.0, and an NACA 65A009 airfoil section parallel to the free stream.
Date:
August 23, 1950
Creator:
MacLeod, Richard G.
System:
The UNT Digital Library
A Note on the Mechanism of the Formation of Alpha-Acylamino Ketones from Amino Acids
The reaction of alanine-1-C14 and phenylalanine-1-C14 with acetic anhydride in the presence of pyridine has been studied and the carboxyl group of the amino acid has been shown to be the exclusive source of carbon dioxide involved.
Date:
August 23, 1950
Creator:
Fry, Arthur & Rapoport, Henry
System:
The UNT Digital Library
Summary of Normal Accelerations, Gust Velocities, and Operating Practices, From April to August 1949 of a Twin-Engine Airplane in Commercial Transport Operations
Report presenting the first sample of time-history data of airspeed, altitude, and normal accelerations obtained by the NACA VGH recorder in transport operations. This data defines the distribution of normal accelerations and airspeeds in greater detail than what was obtainable with the V-G recorder. Results regarding effective gust velocities, proportion of time spent in rough air, values of airspeed in descent, and variations in load experience are provided.
Date:
August 23, 1950
Creator:
Steiner, Roy & McDougal, Robert L.
System:
The UNT Digital Library
Analysis of supernatants 234-5 Building
The Pu in one batch (160 gms) is precipitated in a purification hood and waste supernatant is then transferred to the storage tank in one of the recovery hoods. Under normal process conditions a small amount of Pu remains in the supernatant. However, it is possible, though extremely unlikely, that the entire 160 grams would be transferred to the waste storage tank. The supernatants are transferred to an evaporator where they are concentrated. This evaporator has dimensions approximately the same as those of the storage tank, however, as concentration proceeds, the remaining solution can pass to a geometry more favorable for a chain reaction. There should be definite assurance before evaporation is begun that the amount of Pu in the evaporator does not exceed 160 grams. It is concluded that there is no objection, from a nuclear safety standpoint, to the discontinuance of analysis of the supernatants.
Date:
August 23, 1951
Creator:
Gast, P.F.
System:
The UNT Digital Library
Relation of engine turbine-blade life to stress-rupture properties of the alloys, Stellite 21, Hastelloy B, Cast S-816, Forged S-816, X-40, Nimonic 80, Refractory 26, N-155, and Iconel X
An investigation was conducted to relate the engine performance of the heat-resistant alloys, Stellite 21, Hastelloy B, cast S-816, forged S-816, X-40, Nimonic 80, Refractory 26, N-155, and Iconel X to their stress-rupture properties. The engine test consisted of the repetition of a 20-minute cycle, 15 minutes at rated speed and approximately 5 minutes at idle. The results of the investigation indicated a direct correlation between stress-rupture life and blade life for the relatively low-strength alloys. The stress-rupture life and blade life for the relatively high-strength alloys did not correlate because of the effects of the vibratory stresses and the corrosive-gas atmosphere.
Date:
August 23, 1951
Creator:
Garrett, F. B. & Yaker, C.
System:
The UNT Digital Library
Two-dimensional cascade investigation of the maximum exit tangential velocity component and other flow conditions at the exit of several turbine blade designs at supercritical pressure ratios
The nature of the flow at the exit of a row of turbine blades for the range of conditions represented by four different blade configurations was evaluated by the conservation-of-momentum principle using static-pressure surveys and by analysis of Schlieren photographs of the flow. It was found that for blades of the type investigated, the maximum exit tangential-velocity component is a function of the blade geometry only and can be accurately predicted by the method of characteristics. A maximum value of exit velocity coefficient is obtained at a pressure ratio immediately below that required for maximum blade loading followed by a sharp drop after maximum blade loading occurs.
Date:
August 23, 1951
Creator:
Hauser, Cavour H. & Plohr, Henry W.
System:
The UNT Digital Library
Yawed-Landing Investigation of a Model of the Convair Y2-2 Airplane, TED No. NACA DE 363
"A model of the Convair Y2-2 airplane was tested in Langley tank no. 2 to determine whether satisfactory stability in yawed landings was possible with a certain ventral fin. Free-body landings were made in smooth and rough water at two speeds and two rates of descent with the model yawed 15 degrees. The behavior of the model was determined by visual observations and from motion-picture records" (p. 1).
Date:
August 23, 1951
Creator:
Hoffman, Edward L. & Fisher, Lloyd J.
System:
The UNT Digital Library