UNT Libraries Government Documents Department - 100 Matching Results

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100 Areas technical activities report Engineers, January 1951

Description: Monthly reports are given for the B, D, DR, F and H piles. And the Engineering Development Group reports on the: Ball 3-X program, thermocouple slug irradiation and related studies, process water study, metallurgical and corrosion studies, analytical research, heat transfer and temperature effect experiment, assistance to pile physics group, miscellaneous development projects, and a job status report from Engineering Development.
Date: February 2, 1951
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics at transonic speeds of a 69 degree delta wing with a triangular plan-form control having a skewed hinge axis and an overhang balance: transonic-bump method

Description: From Introduction: "Presented in this paper are the results of an investigation of a semispan model of a delta wing with 60^o sweepback at the leading edge which was equipped with a large triangular control having an overhang balance mounted on a skewed hinge axis. The purpose of this investigation was to determine the aerodynamic characteristics of a delta wing with a control which was designed to provide aerodynamic balance at zero control deflection based on the span load distribution of ref… more
Date: February 6, 1951
Creator: Wiley, Harleth G.
Item Type: Refine your search to only Report
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Aerodynamic characteristics including pressure distribution of a fuselage and three combinations of the fuselage with swept-back wings at high subsonic speeds

Description: From Introduction: "The wings were tested in combination with fuselage similar to the one used in the 7- by 10-foot wind-tunnel investigations. The results are reported herein and are compared with results for three similar model wings on the transonic bump (references 1, 2, and 3)."
Date: February 6, 1951
Creator: Sutton, Fred B. & Martin, Andrew
Item Type: Refine your search to only Report
open access

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

Description: 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.
Item Type: Refine your search to only Report
open access

Altitude-test-chamber investigation of performance of a 28-inch ram-jet engine 3: combustion and operational performance of three flame holders with a center pilot burner

Description: Report presenting a direct-connect altitude test chamber investigation of the combustion performance of a 28-inch-diameter ramjet engine with a can-type center pilot burner. Combustion-chamber configurations with three different flame holders were investigated at a simulated flight Mach number of 2.0 and several different altitudes.
Date: February 6, 1951
Creator: Shillito, Thomas B.; Younger, George G. & Henzel, James G., Jr.
Item Type: Refine your search to only Report
open access

An Analytical and Experimental Investigation of the Skin Friction of the Turbulent Boundary Layer on a Flat Plate at Supersonic Speeds

Description: Report presenting a review of turbulent-boundary-layer analyses and experimental data for average skin-friction coefficients on a flat plate in high-speed flow. New solutions are presented which show the effect of using a continuous velocity gradient and the effect of the extent of the laminar sublayer on the average skin-friction coefficient.
Date: February 1951
Creator: Rubesin, Morris W.; Maydew, Randall C. & Varga, Steven A.
Item Type: Refine your search to only Report
open access

Basic Differential Equations in General Theory of Elastic Shells

Description: "The shell shall be considered as a three-dimensional continuous medium; for the coordinate surface, the middle surface of the shell shall be assumed parallel to the bounding surfaces. Let alpha and beta be the curvilinear orthogonal coordinates of this surface, coinciding with the lines of principal curvatures, and gamma the distance along the normal from the point (alpha,beta) of the coordinate surface to any point (alpha, beta, gamma) of the shell" (p. 1).
Date: February 1951
Creator: Vlasov, V. S.
Item Type: Refine your search to only Report
open access

Bronze Furnace History 313 Building

Description: This study was started in May 1949 to find methods of reducing the number of element failures in the salt bath bronze furnaces. Determining the cause of the failure and methods of eliminating them is followed to completion.
Date: February 6, 1951
Creator: Correy, Thos. B.
Item Type: Refine your search to only Report
open access

Calculated Performance of a Direct-Air Nuclear Turbojet-Powered Airplane Using a Split-Flow Reactor and a Separated-Type Shield

Description: 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.
Item Type: Refine your search to only Report
open access

Calculated Performance of a Direct-Air Nuclear Turbojet-Powered Airplane Using a Split-Flow Reactor and a Separated-Type Shield

Description: Memorandum presenting an analysis made to estimate the performance of a direct-air nuclear turbojet-powered airplane with 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 1, 1951
Creator: Doyle, R. B.
Item Type: Refine your search to only Report
open access

Calculation of k-o in a Uranium-Graphite Lattice

Description: Since the 25 content of the uranium to be used in a MTA multiplying lattice is quite uncertain at present, it is necessary to assume various degrees of depletion in order to estimate the multiplication constant K-o and the production of 49 in an infinite uranium-graphite lattice
Date: February 8, 1951
Creator: Adelman, F.
Item Type: Refine your search to only Report
open access

The Corrosion of Various Stainless Steels in Synthetic Waste Solutions

Description: Technical report describing the tests on types 309, 316, and 347 stainless steel. These steels were tested for a total of 779 to 828 hours in three different synthetic waste solutions. Results shoe that the best all-around corrosion resistance to the test conditions was exhibited by 316 stainless steel, but in one solution 347 stainless steel was more resistant. [From Abstract]
Date: February 12, 1951
Creator: English, James L.
Item Type: Refine your search to only Report
open access

The Counting Efficiency of Pa²³³

Description: 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-
Item Type: Refine your search to only Report
open access

Dynamic stability and control characteristics of a vertically rising airplane model in hovering flight

Description: Report presenting an investigation to determine the stability and control characteristics of a vertically rising airplane model. Results of preliminary hovering flight tests are made in still air, away from the interference effects of the ground and side walls, and with normal airplane-type controls operating in the slipstream.
Date: February 23, 1951
Creator: Bates, William R.; Lovell, Powell M., Jr. & Smith, Charles C., Jr.
Item Type: Refine your search to only Report
open access

Effect of an Increase in Angle of Dead Rise on the Hydrodynamic Characteristics of a High-Length-Beam-Ratio Hull

Description: Report presenting an investigation in Langley tank no. 1 to determine the effects of increasing the angle of dead rise on various hydrodynamic qualities of a flying-boat hull with a length-beam ratio of 15. Results regarding the longitudinal stability, spray characteristics, take-off performance, rough-water landing characteristics, and a summary chart are provided.
Date: February 1951
Creator: Whitaker, Walter E., Jr. & Bryce, Paul W., Jr.
Item Type: Refine your search to only Report
open access

The effects of centrally mounted wing-tip tanks on the subsonic aerodynamic characteristics of a wing of aspect ratio 10 with 35 degrees of sweepback

Description: Report presenting an investigation of the effects of three centrally mounted wing-tip tanks on the aerodynamic characteristics of a cambered wing with an aspect ratio of 10 and 35 degrees of sweepback. Testing occurred over a range of Mach and Reynolds numbers and lift, drag, and pitching-moment were measured.
Date: February 21, 1951
Creator: Tinling, Bruce E. & Kolk, W. Richard
Item Type: Refine your search to only Report
open access

Effects of Furnance Pressures on Quality of Remelted Uranium : Final Report, Production Test 314-59-M

Description: The following report follows a test for remelting and casting uranium scrap specified that a pressure of 25 microns or less must be attained within the furnace before a charge is melted. The report was made to evaluate the effect of furnace pressures upon the quality if recast uranium metal.
Date: February 15, 1951
Creator: Kattner, W. T.
Item Type: Refine your search to only Report
open access

The Effects of Increasing the Leading-Edge Radius and Adding Forward Camber on the Aerodynamic Characteristics of a Wing With 35 Degrees of Sweepback

Description: Report presenting a wind-tunnel investigation to determine the effects of a section modification on the aerodynamic characteristics of a wing with 35 degrees of sweepback. The wing was modified by increasing the leading-edge radius of the NACA 64A010 section and adding a small amount of camber to the forward portion of the chord. Lift, drag, pitching-moment, and trailing-edge-flap hinge-moment characteristics of the modified wing are compared with results from the original wing.
Date: February 9, 1951
Creator: Demele, Fred A. & Sutton, Fred B.
Item Type: Refine your search to only Report
open access

The effects of Mach number and Reynolds number on the aerodynamic characteristics of several 12-percent-thick wings having 35 degrees of sweepback and various amounts of camber

Description: Report presenting a comparison of the lift, drag, and pitching-moment characteristics of several wings with 35 degrees of sweepback and various amounts of camber in wind-tunnel testing. Six semispan model wings were tested, three with an aspect ratio of 10 and three with an aspect ratio of 5. Results regarding model distortion under aerodynamic loads, effects of Reynolds number, effects of Mach number, and effects of camber are provided.
Date: February 23, 1951
Creator: Tinling, Bruce E. & Kolk, W. Richard
Item Type: Refine your search to only Report
open access

Effects of Several Arrangements of Rectangular Vortex Generators on the Static-Pressure Rise Through a Short 2:1 Diffuser

Description: Memorandum presenting an investigation of a 2:1 area-ratio diffuser of length equal to the inlet diameter with several arrangements of simple rectangular vortex generators over a speed range up to an inlet Mach number of 0.5. The investigation was for an inlet boundary layer of 5 percent of the inlet diameter, a condition for which this diffuser had substantial separated areas with no vortex generators. Results regarding the diffuser with no vortex generators, counterrotating vortex generators,… more
Date: February 20, 1951
Creator: Valentine, E. Floyd & Carroll, Raymond B.
Item Type: Refine your search to only Report
open access

Effects on longitudinal stability and control characteristics of a B-29 airplane of variations in stick-force and control-rate characteristics obtained through use of a booster in the elevator-control system

Description: The longitudinal stability and control characteristics of a B-29 airplane have been measured with a control surface booster incorporated in the elevator-control system. The measurements were obtained with the booster operating to provide various control-force gradients and various maximum rates of control motion. Results are presented which show the effect of these booster parameters on the handling qualities of the test airplane.
Date: February 1951
Creator: Mathews, Charles W.; Talmage, Donald B. & Whitten, James B.
Item Type: Refine your search to only Report
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