Resource Type
Collection
Serial/Series Title
NACA Research Memorandums
343
NACA Technical Notes
169
Atomic Energy Commission Reports
122
United States Geological Survey Reports
85
Trace elements investigations report
66
Hanford Works Reports
54
Oak Ridge National Laboratory Reports
45
HW (Series)
37
University of California Radiation Laboratory Reports
32
ORNL (Series)
22
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Strontium Program Quarterly Summary Report: November 1958 - January 1959
From Abstract: "This report is one of a sequence of quarterly reports, each designed to up-date its predecessor beginning with HASL-42, "Environmental Contamination from Weapon Tests." Herein are reported data which have accrued since HASL-51. In particular, the levels of strontium 90 in fallout, milk, tap water, vegetation, and foods are given, based on data available from November 1, 1958 to January 30, 1959."
Date:
February 24, 1959
Creator:
Hardy, Edward P., Jr. & Klein, Stanley
System:
The UNT Digital Library
Roll Cladding Uranium-Zirconium and Uranium-Zirconium-Niobium Alloys with Zircaloy-2 for Plate-Type Fuel Elements
From Abstract: "Investigations were made of alternate methods of bonding fuel shapes and the use of alternate core alloys in flat plates. Alternations and additions were made to development facilities needed to fabricate roll-clad plates for the EBWR core. Pilot production of EWBR-type plates proved that the plate cladding process could be adapted to production facilities."
Date:
February 1958
Creator:
Bean, C. H.; Macherey, R. E. & Lindgren, J. R.
System:
The UNT Digital Library
Electronic Devices for Nuclear Physics: November 1, 1955 - January 31, 1956
Report regarding the ongoing development of both multi-alkali photocathodes and improved photomultipliers.
Date:
February 17, 1956
Creator:
Anderson, R. H.; Fowler, G. O.; Greenblatt, M. H. & Sommer, A. H.
System:
The UNT Digital Library
Rocket-Model Investigation of the Rolling Effectiveness of a Fighter-Type Wing-Control Configuration at Mach Numbers From
"An investigation of the rolling effectiveness of spoiler and aileron aerodynamic controls on a fighter-type airplane has been conducted at Mach numbers from 0.6 to 1.5 by the Langley Pilotless Aircraft Research Division by utilizing rocket-propelled test vehicles. No effects of mutual interference between the midspan spoiler and the outboard aileron were detectable. Above the speed of sound, the ailerons were relatively ineffective as compared with the spoiler because of wing twisting" (p. 1).
Date:
February 25, 1952
Creator:
Strass, H. Kurt & Marley, Edward T.
System:
The UNT Digital Library
Additional Experiments With Flat-Top Wing- Body Combinations at High Supersonic Speeds
Memorandum presenting an experimental study of the effects of several variations in configuration geometry on the aerodynamic characteristics of flat-top wing-body combinations. Generally, the configurations consist of one half of a body of revolution mounted beneath a wing of essentially arrow plan form. Results regarding the effect of trailing-edge sweep, effect of the addition of auxiliary bodies, effect of tip-flap deflection, effect of dihedral, effect of leading-edge sweep, effect of fuselage fineness ratio, effect of fuselage profile shape, and static longitudinal stability characteristics are provided.
Date:
February 19, 1957
Creator:
Syvertson, Clarence A.; Wong, Thomas J. & Gloria, Hermilo R.
System:
The UNT Digital Library
Dynamic Stability Investigation of Two Right Circular Cylinders in Axial Free Flight at Mach Numbers From 0.4 to 1.7 Fineness-Ratio- 2.56 Cylinder and Fineness-Ratio-4.0 Cylinder With Flared Afterbody
Memorandum presenting two right circular cylinders tested in axial free flight over a Mach number range of 0.4 to 1.7 by using the rocket-boosted-model technique. Results regarding time history, basic data cross plots, center of pressure, and drag are provided.
Date:
February 28, 1957
Creator:
McFall, John C., Jr.
System:
The UNT Digital Library
Theoretical Performance of Liquid Hydrogen and Liquid Fluorine as a Rocket Propellant
Report of theoretical values of performance parameters for liquid hydrogen and flourine as a rocket propellant for a wide range of fuel-oxidant and expansion ratios. Parameters computed include specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity.
Date:
February 6, 1953
Creator:
Gordon, Sanford & Huff, Vearl N.
System:
The UNT Digital Library
Cooling Characteristics of an Experimental Tail-Pipe Burner With an Annular Cooling-Air Passage
Memorandum presenting the tail-pipe fuel ratio, mass flow of combustion gas, and radial fuel flow distribution on cooling requirements of tail-pipe burner with annular cooling-air passage.
Date:
February 26, 1952
Creator:
Koffel, William K. & Kaufman, Harold R.
System:
The UNT Digital Library
Transonic Aerodynamic and Trim Characteristics of a Multi-Engine Delta-Wing Airplane Model
Memorandum presenting an investigation of three models of a delta-wing airplane designed for a long-range subsonic cruise and a supersonic dash. Results regarding the aerodynamic characteristics of the models and effect of elevon deflection on aerodynamic characteristics of the four-engine model are provided.
Date:
February 17, 1956
Creator:
Swihart, John M. & Foss, Willard E., Jr.
System:
The UNT Digital Library
Some Interference Effects That Influence Vertical-Tail Loads at Supersonic Speeds
Memorandum presenting three types of aerodynamic interference originating from forward components of airplanes, which are shown to contribute to decreased vertical-tail effectiveness. The vorticity originating from a slender fuselage ahead of the wing resulted in a marked reduction in vertical-tail effectiveness with angle of attack for one model.
Date:
February 17, 1956
Creator:
Edwards, S. Sherman
System:
The UNT Digital Library
Aerodynamic Effects Caused by Icing of an Unswept NACA 65A004 Airfoil
From Summary: "The effects of ice formations on the section lift, drag, and pitching-moment coefficients of an unswept NACA 65A004 airfoil section of 6-foot chord were studied.. The magnitude of the aerodynamic penalties was primarily a function of the shape and size of the ice formation near the leading edge of the airfoil. The exact size and shape of the ice formations were determined photographically and found to be complex functions of the operating and icing conditions."
Date:
February 1958
Creator:
Gray, Vernon H. & von Glahn, Uwe H.
System:
The UNT Digital Library
Icing Limit and Wet-Surface Temperature Variation for Two Airfoil Shapes Under Simulated High-Speed Flight Conditions
Note presenting an experimental study of the wet-surface temperature and stream conditions that result in ice-free surfaces for bodies in flight through icing clouds, and the results obtained are compared with values calculated using an analytical method. Two symmetrical airfoil models, one of diamond shape and the other of double-circular-arc contour, were used in the investigation. Results regarding the chordwise variation of pressure distribution, chordwise variation of recovery factor, the diamond airfoil, and circular-arc airfoil are provided.
Date:
February 1955
Creator:
Coles, Willard D.
System:
The UNT Digital Library
Effect of Design Changes of Operating Conditions on Combustion and Operational Performance of a 28-Inch Diameter Ram-Jet Engine
Report presenting an investigation of the altitude performance of a 28-inch diameter ram-jet engine using a direct-connect system in an altitude test chamber. The majority of the investigation occurred at Mach number 2 at altitudes above the tropopause (250 degrees Fahrenheit inlet temperature). Various design configurations were explored and runs were made with different types of fuel.
Date:
February 13, 1952
Creator:
Shillito, T. B. & Nakanishi, Shigeo
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 using 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 1951
Creator:
Doyle, R. B.
System:
The UNT Digital Library
A Preliminary Study of the Effect of Boric Oxide Deposits on the Performance of Two Selected Turbine Stator-Blade Shapes
Report discussing testing on the performance of two stator-blade shapes with and without boric oxide deposits. The deposits were found to cause total pressure losses and decreases in the blade-exit flow angle. Information about the cascade throat area, boundary-layer momentum thickness, total pressure ratio, and exit flow angle and tangential component of velocity is provided.
Date:
February 25, 1958
Creator:
Setze, Paul C. & Nusbaum, William J.
System:
The UNT Digital Library
A flight investigation of the practical problems associated with porous-leading-edge suction
From Summary: "A flight investigation has been made of the practical problems associated with the use of porous-leading-edge suction. The wing leading edge of the test airplane was porous over approximately 83 percent of the span and the first 8 percent of the chord on the upper surface. Various other extents of suction area within these limits were also tested."
Date:
February 1954
Creator:
Hunter, Paul A. & Johnson, Harold I.
System:
The UNT Digital Library
Correlations Among Ice Measurements, Impingement Rates Icing Conditions, and Drag Coefficients for Unswept NACA 65A004 Airfoil
"An empirical relation has been obtained by which the change in drag coefficient caused by ice formations on an unswept NACA 65A004 airfoil section can be determined from the following icing and operating conditions: icing time, airspeed, air total temperature, liquid-water content, cloud droplet impingement efficiencies, airfoil chord length, and angles of attack. The correlation was obtained by use of measured ice heights and ice angles. These measurements were obtained from a variety of ice formations, which were carefully photographed, cross-sectioned, and weighed" (p. 1).
Date:
February 1958
Creator:
Gray, Vernon H.
System:
The UNT Digital Library
Preliminary Investigation of Cyclic De-Icing of an Airfoil Using an External Electric Heater
"An investigation was conducted in the NACA Lewis icing research tunnel to determine the characteristics and requirements of cyclic deicing of a 65,2-216 airfoil by use of an external electric heater. The present investigation was limited to an airspeed of 175 miles per hour. Data are presented to show the effects of variations in heat-on and heat-off periods, ambient air temperature, liquid-water content, angle of attack, and. heating distribution on the requirements for cyclic deicing" (p. 1).
Date:
February 4, 1952
Creator:
Lewis, James P. & Bowden, Dean T.
System:
The UNT Digital Library
Penetration of Air Jets Issuing from Circular, Square, and Elliptical Orifices Directed Perpendicularly to an Air Stream
From Summary: "An experimental investigation was conducted to determine the penetration of air jets directed perpendicularly to an air stream. Jets issuing from circular, square, and elliptical orifices were investigated and the jet penetration at a position downstream of the orifice was determined- as a function of jet density, jet velocity, air-stream density, air-stream velocity, effective jet diameter, and orifice flow coeffIcient. The jet penetrations were determined for nearly constant values of air-stream density at three tunnel-air velocities arid for a large range of jet velocities and densities."
Date:
February 1950
Creator:
Ruggeri, Robert S.; Callaghan, Edmund E. & Bowden, Dean T.
System:
The UNT Digital Library
A Photographic Study of Freezing of Water Droplets Falling Freely in Air
From Summary: "A photographic technique for investigating water droplets of diameter less than 200 microns falling freely in air at temperatures between 0 C and -50 C has been devised and used to determine: (1) The shape of frozen droplets, (2) The occurrence of collisions of partly frozen or of frozen and liquid droplets, and (3) The statistics on the freezing temperatures of individual free-falling droplets."
Date:
February 25, 1952
Creator:
Dorsch, Robert G. & Levine, Joseph
System:
The UNT Digital Library
Impingement of Water Droplets on a Rectangular Half Body in a Two-Dimensional Incompressible Flow Field
"Trajectories of water droplets moving in the ideal two-dimensional flow field ahead of a body of rectangular cross section and infinite extent in the downstream direction have been calculated by means of a differential analyzer. Data on collection efficiency and distribution of water impingement are presented" (p. 1).
Date:
February 1956
Creator:
Lewis, William & Brun, Rinaldo J.
System:
The UNT Digital Library
A Wind Tunnel Investigation of Several Wingless Missile Configurations at Supersonic Speeds
Report presenting an investigation of several wingless missile configurations for a range of Mach numbers to determine their lift, drag, and pitching-moment coefficients. Results for missiles having nose controls and missiles having tail controls are provided. The results were also compared to a conventional missile with wings.
Date:
February 3, 1958
Creator:
Reese, David E., Jr.
System:
The UNT Digital Library
Investigation at Mach Number 1.91 of Spreading Characteristics of Jet Expanding From Choked Nozzles
Report presenting an investigation at Mach number 1.91 to determine the gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles using total-temperature surveys. Results regarding the preliminary development and jet spreading characteristics of the different types of nozzles are provided.
Date:
February 11, 1952
Creator:
Rousso, Morris D. & Baughman, L. Eugene
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