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88
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29
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277 Matching Results
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Further End Cap Temperature Calculations
Abstract. Recently (CP-1989) it has been shown that the neutron density, and thus the heat production, at the end of a slug with an A1 cap may be appreciably higher than that at the middle of the slag. A re-examination of earlier temperature calculations is made in light of this effect.
Date:
August 16, 1944
Creator:
Karush, William; Monk, A. T. & Wilkins, J. Ernest, Jr., 1923-2011
System:
The UNT Digital Library
Tests of an Adjustable-Area Exhaust Nozzle for Jet-Propulsion Engines
Report discussing a comparison between a centrifugal-flow-type turbojet engine with an adjustable-area exhaust nozzle and with a series of fixed-area nozzles of various throat diameters. The adjustable-area nozzle was found to be as efficient as the fixed-area nozzles in testing. Information about the corrected static thrust, fuel flow, and tail-pipe gas temperature for both types of nozzles is provided.
Date:
August 16, 1945
Creator:
Wilcox, E. C.
System:
The UNT Digital Library
VACUUM PROBE, STANDARD LEAKS, AND NEEDLE VALVE FOR USE WITH THE HELIUM LEAK DETECTOR
None
Date:
August 16, 1945
Creator:
Samuel, A.J.
System:
The UNT Digital Library
100 Areas: (For technical progress letter No. 110), August 6--August 12
This report details 100 Area reactor operation for the time period of August 6 through August 12, 1946.
Date:
August 16, 1946
Creator:
Jordan, W. E.
System:
The UNT Digital Library
Analytical investigation of effect of water-cooled turbine blades on performance of turbine-propeller power plants
"Finally the work of the report is applied exclusively to consideration of the turbine-propeller power plant because previous performance analyses of the various gas-turbine propulsion systems combine with recent improvements in propeller design indicate that it is this combination which, will give the best over-all performance in the speed ranges considered" (p. 5).
Date:
August 16, 1948
Creator:
Bowman, William D
System:
The UNT Digital Library
Calibration of Air-Flow Meters for J33 Compressor Investigation
Flow-metering devices used by the NACA and by the manufacturer of the J33 turbojet engine were calibrated together to determine whether an observed discrepancy in weight flow of approximately 4 percent for the two separate investigations might be due to the different devices used to meter air flow. A commercial adjustable orifice and a square-edge flat-plate orifice used by the NACA and a flow nozzle used by the manufacturer were calibrated against surveys across the throat of the nozzle. It was determined that over a range of weight flows from 18 to 45 pounds per second the average weight flows measured by the metering device used for the compressor test would be 0.70 percent lower than those measured by the metering device used in the engine tests and the probable variation about this mean would be +/- 0.39 percent. The very close agreement of the metering devices shows that the greater part of the discrepancy in weight flow is attributable to the effect of inlet pressure.
Date:
August 16, 1948
Creator:
Kovach, Karl & Withee, Joseph R., Jr.
System:
The UNT Digital Library
Meeting with Withington of Boeing Aircraft, Col. Demler of A.E.C., Washington, Col. Wassell and Col. Reichert of Wright Field
None
Date:
August 16, 1948
Creator:
Klein, J. H.
System:
The UNT Digital Library
The Coulometric Determination of Acetic Acid
Abstract: "Small amounts of acetic acid, equivalent to 400 ul. of 0.3 to 0.13 g/L. can be titrated coulonatrically in the presence of a 10 to 25-fold excess of HN03 in 70%, isopropanol. An accuracy of +/- 0.1% and a precision of +/- 8.5% (99% limite) are obtained.
Date:
August 16, 1949
Creator:
Carson, W. N. & Ko, Roy
System:
The UNT Digital Library
An NACA Vane-Type Angle-of-Attack Indicator for use at Subsonic and Supersonic Speeds
A vane-type angle-of-attack indicator suitable for measurements at both subsonic and supersonic speeds has been developed by the National Advisory Committee for Aeronautics. A brief history is given of the development, and a wind-tunnel calibration of the indicator is presented, together with a discussion of the corrections to be applied to the indicated readings.
Date:
August 16, 1949
Creator:
Mitchell, Jesse L. & Peck, Robert F.
System:
The UNT Digital Library
On Reflection of Shock Waves from Boundary Layers
Measurements are presented at Mach numbers from about 1.3 to 1.5 of reflection characteristics and the relative upstream influence of shock waves impinging on a flat surface with both laminar and turbulent boundary layers. The difference between impulse and step waves is discussed and their interaction with the boundary layer is compared. General considerations on the experimental production of shock waves from wedges and cones and examples of reflection of shock waves from supersonic shear layers are also presented.
Date:
August 16, 1949
Creator:
Liepmann, H. W.; Roshko, A. & Dhawan, S.
System:
The UNT Digital Library
Preliminary Aerodynamic Investigation of the Effect of Camber on a 60 Degree Delta Wing with Round and Beveled Leading Edges
Memorandum presenting an exploratory investigation to determine the aerodynamic effects of camber on a 60 degree apex delta-wing model conducted in the 300 mph 7- by 10-foot tunnel. Camber variation was accomplished through the deflection of full-span round and 25 degree beveled leading-edge flaps on a flat-sided triangular plan-form wing.
Date:
August 16, 1949
Creator:
Riebe, John M. & Fikes, Joseph E.
System:
The UNT Digital Library
Procedures in Magnetic Measurements at the University of California Radiation Laboratory, Berkeley: Fields Which are Constant or Vary Slowly with Time
The flux standard is a device which will give a known flux-linkage change to be used as a calibration. At the Radiation Laboratory, two types of flux standards are used, a stationary type and a portable type.
Date:
August 16, 1949
Creator:
Richardson, Robert E.
System:
The UNT Digital Library
Effects of Varying the Size and Location of Trailing-Edge Flap-Type Controls on the Aerodynamic Characteristics of a Unswept Wing at a Mach Number of 1.9
Report presenting an investigation to determine the effects of flap size and location on an unswept semispan wing in combination with a half-fuselage. The wing had an aspect ratio of 2.5, a taper ratio of 0.625, and 6-percent-thick modified double-wedge airfoil sections. Results regarding wing characteristics and flap characteristics are provided.
Date:
August 16, 1950
Creator:
Mitchell, Meade H., Jr.
System:
The UNT Digital Library
Low-speed tests of a model simulating the phenomenon of control-surface buzz
Report presenting low-speed tests of an airfoil model with a freely hinged flap attached to spoilers which passed through slots in the airfoil ahead of the hinge line. Testing indicated that buzz is not caused simply by buffeting of a flap by separated flow. Results regarding the oscillations experienced with the spoiler and flap in several positions are provided.
Date:
August 16, 1950
Creator:
Phillips, William H. & Adams, James J.
System:
The UNT Digital Library
Stability characteristics at low speed of a 1/4-scale Bell X-5 airplane model with various modifications to the basic model configurations
Report presenting an investigation of the low-speed longitudinal, lateral, and directional stability characteristics if a 1/4-scale model of a preliminary Bell X-5 airplane design with modifications to the basic model configuration. Results regarding the dive brakes, trailing-edge fillets, extended wing tips, fences, wing incidence, and fins are provided.
Date:
August 16, 1950
Creator:
Becht, Robert E. & Few, Albert G., Jr.
System:
The UNT Digital Library
The Crystal Structures of Oxalic Acid Dihydrate and Alpha Iodic Acid as Determined by Neutron Diffraction
The crystal structure of oxalic acid dihydrate and alpha iodic acid were determined by neutron diffraction. Several modern techniques were utilized in analyzing the data, including Fourier series, structure factor inequalities, statistical intensity distributions, least squares, and Fourier peak shape analysis. The positions of all the atoms, including hydrogen, were determined.
Date:
August 16, 1954
Creator:
Garrett, B. S.
System:
The UNT Digital Library
The Fabrication of Subassemblies for the Supercritical-Water Reactor
In studies of the fabrication of fuel subassemblies for the supercritical-water reactor, the limited ductility of stainless steel-UOâ‚‚ fuel sheet made the fabrication of corrugated-flat-plate-type subassemblies impractical. A fabricable MTR-type assembly, 5/8 in. square and 30 in. long, was developed. Methods for edge cladding fuel sheet were developed and a brazing alloy, GE-75, was found to be corrosion resistant in supercritical water.
Date:
August 16, 1954
Creator:
Keeler, J. R. & Hare, Alan W.
System:
The UNT Digital Library
THE FABRICATION OF SUBASSEMBLIES FOR THE SUPERCRITICAL-WATER REACTOR
In studies of the fabrication of fuel subassemblies for the supercritical-water reactor, the limited ductility of stainless steel-UO/sub 2/ fuel sheet made the fabrication of corrugated-flat-plate-type subassemblies impractical. A fabricable MTR-type assembly, 5/8 in. square and 30 in. long, was developed. Methods for edge cladding fuel sheet were developed and a brazing alloy, GE-75, was found to be corrosion resistant in supercritical water. (auth)
Date:
August 16, 1954
Creator:
Keeler, J.R. & Hare, A.W.
System:
The UNT Digital Library
Investigation of impulse-type supersonic compressor with hub-tip ratio of 0.6 and turning to axial direction 2: stage performance with three different sets of stators
Report presenting an impulse-type supersonic compressor designed for turning to the axial direction that was tested in air with three different sets of stator blades at eight angle settings.
Date:
August 16, 1955
Creator:
Wilcox, Ward W.
System:
The UNT Digital Library
Matching of Auxiliary Inlets to Secondary-Air Requirements of Aircraft Ejector Exhaust Nozzles
Report presenting an analysis of the problems associated with matching secondary-air requirements of ejector exhaust nozzles and auxiliary inlets has been made for free-stream Mach numbers up to 2.0. The analysis indicated that inlets located in the free stream supply higher pressure recovery than ejectors generally require for optimum net internal thrust at Mach numbers above about 1.4. Net-thrust gains can be achieved by immersing the auxiliary inlet in a boundary layer where the inlet-momentum penalty is less.
Date:
August 16, 1955
Creator:
Hearth, Donald P.; Englert, Gerald W. & Kowalski, Kenneth L.
System:
The UNT Digital Library
A New Approach to Concatenation of Pulsed Columns
A method of performing a series of solvent extractions using a minimum of pulse generators is briefly outlined.
Date:
August 16, 1955
Creator:
Ludlow, J. O.
System:
The UNT Digital Library
Performance of Inconel 550 Turbine Blades in a Turbojet Engine and Effects of Different Forging Temperatures and Heat Treatments
Report presenting an investigation to determine the effects of forging at 1950 degrees and 2150 degrees Fahrenheit as well as the effects of several heat treatments on the performance of Inconel 550 in a turbojet engine. Differences in engine performance of the different turbine blades could not be associated with consistent differences in microstructure or grain size. Results regarding blade performance, blade elongation during engine operation, microstructure of as-heat-treated blades, grain size, metallurgical studies of failed blades, stress-rupture tests, and hardness are provided.
Date:
August 16, 1955
Creator:
Gyorgak, C. A.; Johnston, J. R. & Weeton, J. W.
System:
The UNT Digital Library
Preliminary Analysis of Performance of Turbojet Engines Used as Pumps for Boundary-Layer Control
Memorandum presenting a determination of the effects on engine performance of using turbojet engines for boundary-layer control by suction at the engine inlet or by bleeding air from the compressor outlet for three current production engines. Results regarding bleed, suction, and variable-area turbine are provided.
Date:
August 16, 1955
Creator:
Conrad, E. William
System:
The UNT Digital Library
Preparation of Spherical Uranium Particles - Report of Invention
This is a report of what may be an invention in a process or processes for preparing roughly spherical uranium metal particles suitable for use in matrix type nuclear reactor fuel elements.
Date:
August 16, 1955
Creator:
Roake, William Earl
System:
The UNT Digital Library