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Roll Cladding Uranium-Zirconium and Uranium-Zirconium-Niobium Alloys with Zircaloy-2 for Plate-Type Fuel Elements

Description: 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.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Effects Caused by Icing of an Unswept NACA 65A004 Airfoil

Description: 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.
Partner: UNT Libraries Government Documents Department
open access

A Preliminary Study of the Effect of Boric Oxide Deposits on the Performance of Two Selected Turbine Stator-Blade Shapes

Description: 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.
Partner: UNT Libraries Government Documents Department
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Correlations Among Ice Measurements, Impingement Rates Icing Conditions, and Drag Coefficients for Unswept NACA 65A004 Airfoil

Description: "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 … more
Date: February 1958
Creator: Gray, Vernon H.
Partner: UNT Libraries Government Documents Department
open access

A Wind Tunnel Investigation of Several Wingless Missile Configurations at Supersonic Speeds

Description: 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.
Partner: UNT Libraries Government Documents Department
open access

Buffet Tests of an Attack-Airplane Model With Emphasis on Analysis of Data From Wind-Tunnel Tests

Description: Memorandum presenting the buffet characteristics of a scale model of an attack airplane over a range of Mach numbers. The wing had a modified delta plan form with an NACA 0008 airfoil section at the root and an NACA 0005 airfoil section at the tip, a leading-edge sweep of 41.11 degrees, an aspect ratio of 2.91, and a taper ratio of 0.226. Results regarding the frequency spectrum of bending moment, effect of density on root-mean-square bending moment, system damping coefficients, and buffet inpu… more
Date: February 21, 1958
Creator: Davis, Don D., Jr. & Wornom, Dewey E.
Partner: UNT Libraries Government Documents Department
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Experimental Behavior of Pentaborane-Air Combustion Products During Expansion in a Convergent Divergent Nozzle

Description: "In order to evaluate the post combustion behavior of boric oxide, pentaborane-air mixtures, burned to completion at a combustor pressure of 3 atmospheres, were expanded through a 7.1-inch-long convergent-divergent nozzle having a 4-inch-diameter throat and an exit-to-throat area ratio of 1.68. The experimentally determined thrust performance was in good agreement with the ideal equilibrium performance at stagnation temperatures of 3300 deg R and lower. The boric oxide vapor at the combustor ex… more
Date: February 18, 1958
Creator: Branstetter, J. Robert & Setze, Paul C.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Incipient Spin Characteristics of a 1/35-Scale Model of the Convair F-102A Airplane, Coord. No. AF-AM-79

Description: From Summary: "Incipient spin characteristics have been investigated on a 1/35-scale dynamic model of the Convair F-102A airplane. The model was launched by a catapult apparatus into free flight with various control settings, and the motions obtained were photographed. The model was ballasted for the combat loading. All tests were made with the speed brakes and landing gear retracted, and engine effects were not simulated."
Date: February 11, 1958
Creator: Healy, Frederick M.
Partner: UNT Libraries Government Documents Department
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Transonic-Wind-Tunnel Tests of the Aerodynamic Characteristics of a 0.15-Scale Model of the North American Aviation 255-Inch Fin-Stabilized External Store, Coord No. AF-AM-4

Description: "An investigation has been made in the Langley 8-foot transonic tunnels on the aerodynamic characteristics of a 0.15-scale model of the North American Aviation 255-inch fin-stabilized external store over a maximum Mach number range of 0.60 to 1.2 and on the effects of mounting lugs, of fin orientation, of fin aspect ratio, and of fixed-transition. The Reynolds number (based on a body length of 37.50 inches) varied from 9.8 x 10(exp 6) to 13.1 x 10(exp 6). The results indicate that the static ma… more
Date: February 9, 1958
Creator: Fischetti, Thomas L.
Partner: UNT Libraries Government Documents Department
open access

Evaporation, Heat Transfer, and Velocity Distribution in Two-Dimensional and Rotationally Symmetrical Laminar Boundary-Layer Flow

Description: The fundamental boundary layer equations for the flow, temperature and concentration fields are presented. Two dimensional symmetrical and unsymmetrical and rotationally symmetrical steady boundary layer flows are treated as well as the transfer boundary layer. Approximation methods for the calculation of the transfer layer are discussed and a brief survey of an investigation into the validity of the law that the Nusselt number is proportional to the cube root of the Prandtl number is presente… more
Date: February 1958
Creator: Frössling, Nils
Partner: UNT Libraries Government Documents Department
open access

Impact on a Compressible Fluid

Description: "Upon impact of a solid body on the plane surface of a fluid, there occurs on the vetted surface of the body an abrupt pressure rise which propagates into both media with the speed of sound. Below, we assume the case where the speed of propagation of sound in the body which falls on the surface of the fluid may be regarded as infinitely large in comparison with the speed of propagation of sound in the fluid; that is, we shall assume that the falling body is absolutely rigid. IN this case, the e… more
Date: February 1958
Creator: Egorov, I. T.
Partner: UNT Libraries Government Documents Department
open access

Qualitative Simulator Study of Longitudinal Stick Forces and Displacements Desirable During Tracking

Description: In this study in which an airplane simulator with one degree of freedom (pitch) was used, results were determined for three conditions of airplane dynamics. For an undamped natural frequency of 1/2 cps with a damping ratio of 0.18 and for an undamped natural frequency of 1 cps with a damping ratio of 0.11, moderate longitudinal stick forces and displacements were desired.
Date: February 1958
Creator: Faber, Stanley
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of Effects of Atmospheric Turbulence and Moderate Maneuvers on Bending and Torsional Moments Encountered by a Helicopter Rotor Blade

Description: Note presenting flight tests conducted with a medium-size single-rotor helicopter, of which one blade was equipped with strain gages, to determine the relative effects of atmospheric turbulence and moderate maneuvers on the periodic rotor blade moments. The results indicate no significant increase in the total blade moments due to atmospheric turbulence of moderate pull-up maneuvers which produced center-of-gravity acceleration increments of less than about 0.15g. Results regarding moment recor… more
Date: February 1958
Creator: Ludi, LeRoy H.
Partner: UNT Libraries Government Documents Department
open access

Temperature-Pressure-Time Relations in a Closed Cryogenic Container

Description: Note presenting an experimental study using liquid nitrogen made to verify the existence of a temperature gradient as the factor causing the increase in pressure and to investigate the effect on pressure of altering the temperature gradient. The effect on pressure of different heat-leak rates into the container and different quantities of liquid was also investigated. Results regarding the typical pressure history and temperature gradient, effect of stirring liquid on pressure, effect of heat-l… more
Date: February 1958
Creator: Huntley, Sidney C.
Partner: UNT Libraries Government Documents Department
open access

Creep of Aluminum-Copper Alloys During Age Hardening

Description: Note presenting a study of the interrelation of aging during creep and of creep during aging in polycrystalline aluminum alloys containing 1 to 4 percent copper. Experimental procedures included interrupted creep tests, tensile tests of crept specimens, quantitative metallographic determination of the percent precipitation during creep, hardness measurements on unstressed and stressed aged alloys, X-ray studies of deformation in the crystalline lattice, and microscopic examination of the surfac… more
Date: February 1958
Creator: Underwood, E. E.; Marsh, L. L. & Manning, G. K.
Partner: UNT Libraries Government Documents Department
open access

Experimental Thermal Conductivities of the N2D4 Is in Equilibrium to 2NO2 System

Description: Report presenting an investigation of direct measurements of the thermal conductivity of reacting gas systems. The hot-wire measurement technique was used at a range of temperatures and pressures. A comparison of the theoretical and experimental results are provided.
Date: February 1958
Creator: Coffin, Kenneth P. & O'Neal, Cleveland, Jr.
Partner: UNT Libraries Government Documents Department
open access

Drag Minimization for Wings in Supersonic Flow, With Various Constraints

Description: Report presenting a study of the minimization of inviscid fluid drag for thin aerodynamic shapes subject to imposed constraints on lift, pitching moment, base area, or volume. The problem is transformed to one or determining a two-dimensional potential flow satisfying either Laplace's or Poisson's equations with boundary values fixed by the imposed conditions.
Date: February 1958
Creator: Heaslet, Max A. & Fuller, Franklyn B.
Partner: UNT Libraries Government Documents Department
open access

Charts Relating the Compressive and Shear Buckling Stresses of Longitudinally Supported Plates to the Effective Deflectional Stiffness

Description: "A stability analysis is made of long flat rectangular plates subjected to both shear and compressive loads. The edges of the plates are taken to be simply supported and the plates are supported along one or two intermediate longitudinal lines by lines of deflectional springs (elastic line supports). The results of the analysis are presented in the form of charts that are useful in the determination of the buckling load of plates stiffened by stringers or webs" (p. 1).
Date: February 1958
Creator: Johnson, Aldie E., Jr.
Partner: UNT Libraries Government Documents Department
open access

Turbulent Flow Through Porous Resistances Slightly Inclined to the Flow Direction

Description: "Analytical and experimental studies have been made of the channel flow of air through porous resistances inclined at an angle of 3.5 degrees to the axis of the channel with the air discharging to the atmosphere. These studies determine the channel wall shape that would yield a uniform discharge through the porous resistance" (p. 1).
Date: February 1958
Creator: Loeffler, Albert L., Jr. & Perlmutter, Morris
Partner: UNT Libraries Government Documents Department
open access

Comparison of hydrodynamic-impact acceleration and response for systems with single and with multiple elastic modes

Description: Report presenting hydrodynamic impact testing made with a multimode elastic model consisting of a rigid prismatic float and a flexible wing and a comparison with similar experimental results for a single-mode system and with theoretical solutions. Testing was conducted in smooth water at two fixed trims and two flight-path angles over a range of velocities. Results regarding accelerations, time histories, oscillatory accelerations, elastic-body acceleration data, and rigid-body acceleration dat… more
Date: February 1958
Creator: Miller, Robert W.
Partner: UNT Libraries Government Documents Department
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Effect of lubricant base stock on rolling-contact fatigue life

Description: Report presenting five lubricants of different base stock tested using groups of 1/2-inch air-melt AISI M-1 tool-steel balls under rolling-contact fatigue conditions in the fatigue spin rig. A methyl silicone, mineral oil, glycol, sebacate, and adipate were used. All other test conditions were held constant at a test temperature of 100 degrees Fahrenheit and a maximum theoretical Hertz stress of 725,000 pounds per square inch in compression.
Date: February 1958
Creator: Carter, Thomas L.
Partner: UNT Libraries Government Documents Department
open access

Accelerations in Transport-Airplane Crashes

Description: From Introduction: "A study of crash-impact survival in light airplanes is reported in references 1 and 2. A similar study for fighter airplanes is reported in reference 3. This report discusses crash-impact survival in transport airplanes."
Date: February 1958
Creator: Preston, G. Merritt & Pesman, Gerard J.
Partner: UNT Libraries Government Documents Department
open access

Effectiveness of boundary-layer control, obtained by blowing over a plain rear flap in combination with a forward slotted flap, in deflecting a slipstream downward for vertical take-off

Description: The wing employed in this investigation had a 67-percent-chord slotted flap in combination with a 33-percent-chord plain rear flap equipped with a full-span blowing nozzle. The tests were conducted in a static-thrust facility at the Langley Aeronautical Laboratory. The investigation indicated that the plain rear flap alone with a low momentum coefficient for boundary-layer control provided larger turning angles than the combined slotted and plain flaps without boundary-layer control.
Date: February 1958
Creator: Spreemann, Kenneth P.
Partner: UNT Libraries Government Documents Department
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