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Polarographic Determination of Uranium in Dust Samples

Description: Abstract: "Samples of dust are collected from the atmosphere with a Mine Safety Appliance Co. electrostatic precipitator and analyzed for uranium by means of a dropping mercury electrode apparatus. Two to three micrograms of uranium can be detected in a cell solution volume of 1 ml. Iron, nickel and chromium present in shop dusts do not interfere. Copper may interfere if present in excess but may be removed by a sulfide precipitation. Directions for preparation of cell solution and operation of… more
Date: August 30, 1943
Creator: Smith, Stanton B.
Partner: UNT Libraries Government Documents Department
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Explosives-TNX Technical Division, Hanford weekly report for period ending August 29, 1944

Description: Hood Worthington reports that slug testing in autoclaves shows improvement to substantiate a meeting on the initial loading of pile B and production for B.F. Babcock report examining five drafts of Operating Standards for the 100 Area. C.W.J. Wende are considering alternative loading schemes due to the observation that lead dummy slugs at the inlet end of a tube may mushroom when subjected to the stress of discharging. J.A. Wheeler reports on heavy metal content of reclaimed slugs compared to n… more
Date: August 30, 1944
Creator: Worthington, H.
Partner: UNT Libraries Government Documents Department
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Correlation of Wind-Tunnel Predictions With Flight Tests of a Twin-Engine Patrol Airplane 2: Lateral- and Directional-Stability and Control Characteristics

Description: "The lateral- and directional-stability and -control characteristics of a twin-engine patrol airplane as predicted from the results of wind-tunnel tests of a powered model and as measured in flight are compared in this report. The predictions from wind-tunnel-test data were in good agreement with the flight-test results. The results show that such predicted flying-qualities characteristics are sufficiently accurate to indicate the unsatisfactory lateral- and directional-stability and -control c… more
Date: August 30, 1945
Creator: Delany, Noel K. & Kauffman, William M.
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of a two-blade NACA 10-(3)(12)-03 propeller

Description: From Introduction: "The particular blade design, the tests of which are described in the present paper, was one necessary to the investigation of the effect of differences in blade-thickness ratios."
Date: August 30, 1948
Creator: Allis, A. E. & Gray, W. H.
Partner: UNT Libraries Government Documents Department
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Langley full-scale tunnel investigation of the characteristics in yaw of a trapezoidal wing of aspect ratio 4 with circular-arc airfoil sections

Description: Report presenting an investigation to determine the characteristics in yaw of a trapezoidal wing of aspect ratio 4 with circular-arc airfoil sections and 0.20-chord rear and drooped-nose flaps. Measurements of lift, lateral force, rolling moment, and yawing moment of four configurations were made for a range of angles of attack and yaw angles.
Date: August 30, 1948
Creator: May, Ralph W., Jr. & Stevens, George L.
Partner: UNT Libraries Government Documents Department
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Supplement to Report on the Brookhaven Nuclear Reactor Prepared for Reactor Safeguard Committee of the Atomic Energy Commission

Description: This technical report provides supplementary information on the Brookhaven nuclear reactor. It details added safety systems, tests, expounds on information included in the original report, describes liquid wastes system, and describes different procedures for operating the nuclear reactor.
Date: August 30, 1948
Creator: Brookhaven National Laboratory
Partner: UNT Libraries Government Documents Department
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Effects of leading-edge devices and trailing-edge flaps on longitudinal characteristics of two 47.7 degree sweptback wings of aspect ratios 5.1 and 6.0 at a Reynolds number of 6.0 x 10(exp 6)

Description: Report presenting an investigation in the 19-foot pressure tunnel to determine the effects of leading-edge stall-control devices and trailing-edge flaps on the longitudinal stability characteristics of a 47.7 degree sweptback wing that could have aspect ratios of 5.1 and 6.0 by using interchangeable wing tips. The effects of wing fences, roughness, and a fuselage were also determined. Results regarding the lift characteristics and lift-drag ratios are also provided.
Date: August 30, 1950
Creator: Salmi, Reino J.
Partner: UNT Libraries Government Documents Department
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Pressure-Rise and Leakage-Loss Characteristics of a Rotating Cowling

Description: Report discussing an experimental and analytical investigation in order to study the pressure-rise and leakage-loss characteristics of rotating cowlings. A comparison of the theoretical and experimental results indicated that pressure-rise characteristics can be predicted if internal-flow losses and internal-flow angle at the cowling-vane trailing edge are known.
Date: August 30, 1950
Creator: Runckel, Jack F. & Hieser, Gerald
Partner: UNT Libraries Government Documents Department
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Calculated Aerodynamic Loadings of M, W, and Delta Wings in Incompressible Flow

Description: Report presenting the results of theoretical incompressible-flow calculations of the spanwise lift distributions, lift-curve slopes, spanwise centers of pressure, aerodynamic centers, coefficients of damping in roll, rolling-moment coefficients due to aileron deflection, and induced-drag coefficients of twenty M, W, and delta wings.
Date: August 30, 1951
Creator: Diederich, Franklin W. & Latham, W. Owen
Partner: UNT Libraries Government Documents Department
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Results of Flight Tests to Determine Drag of Parabolic and Cone-Cylinder Bodies of Very Large Fineness Ratios at Supersonic Speeds

Description: Results of a free-flight investigation at supersonic speeds to determine zero-lift drag of a series of bodies of revolution are presented. Configurations tested included two parabolic bodies with fineness ratios of 17.78 and 24.5 and two 8 degree cone-cylinder bodies with fineness ratios of 17.2 and 21.2. Results of previous tests of similar parabolic bodies but with lower fineness ratios are included in this paper for comparison. All bodies for which data are presented in this paper had a base… more
Date: August 30, 1951
Creator: Welsh, Clement J. & de Moraes, Carlos A.
Partner: UNT Libraries Government Documents Department
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Spectrum of turbulence in a contracting stream

Description: The spectrum concept is employed to study the selective effect of a stream contraction on the longitudinal and lateral turbulent velocity fluctuations of the stream. By a consideration of the effect of the stream contraction on a single plane sinusoidal disturbance wave, mathematically not dissimilar to a triply periodic disturbance treated by G. I. Taylor, the effect on the spectrum tensor of the turbulence and hence on the correlation tensor is determined.
Date: August 30, 1951
Creator: Ribner, H. S. & Tucker, M.
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at Mach number of 2.01 of two cruciform missile configurations having 70 degree delta wings with length-diameter ratios of 14.8 and 17.7 with several canard controls

Description: From Introduction: "The present paper contains the results of the investigation of the aerodynamic characteristics at Mach number of 2.01 of the two cruciform wing missiles equipped with larger canard controls and compares the result with that obtained previously with a smaller control."
Date: August 30, 1954
Creator: Spearman, M. Leroy & Robinson, Ross B.
Partner: UNT Libraries Government Documents Department
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Effects of Canopy, Revised Vertical Tail, and a Yaw-Damper Vane on the Aerodynamic Characteristics of a 1/16-Scale Model of the Douglas D-558-II Research Airplane at a Mach Number of 2.01

Description: Report discussing the aerodynamic characteristics in pitch and sideslip of a model of a Douglas D-558-II airplane with and without a yaw-damper vane at Mach number 2.01. A revised model was tested using a canopy and modified vertical tail. The revised configuration was found to have higher directional stability, trim lift coefficients, drag, and more positive effective dihedral than the original configuration.
Date: August 30, 1954
Creator: Robinson, Ross B.
Partner: UNT Libraries Government Documents Department
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A Flight Evaluation of the Stability and Control of the X-4 Swept-Wing Semitailless Airplane

Description: Memorandum presenting an evaluation of the handling qualities of the Northrop X-4 swept-wing semitailless airplane covering a speed range from stall to a Mach number of 0.92 primarily at 30,000 feet. The characteristic problems of tailless airplanes at low speeds, such as marginal longitudinal stability and control resulting in close center-of-gravity limits, were encountered. Results regarding static longitudinal stability characteristics, dynamic stability characteristics, and static lateral … more
Date: August 30, 1954
Creator: Sadoff, Melvin & Crossfield, A. Scott
Partner: UNT Libraries Government Documents Department
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Pressure Distributions on Plug- and Semaphore-Type Spoiler Ailerons on a 35 Degree Sweptback Wing of Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section at High Subsonic Speeds

Description: Report presenting an investigation in the high-speed tunnel to determine the pressure distribution at the 20-, 46-, and 65-percent wing semispan stations on a plug-type spoiler and a segment of a semaphore-type spoiler. The investigation was carried out at a range of Mach numbers and angles of attack. The pressure distributions and integrated section force and moment data are presented without discussion.
Date: August 30, 1954
Creator: Hammond, Alexander D. & Hayes, William C., Jr.
Partner: UNT Libraries Government Documents Department
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CORROSION OF PLATINUM BY UO$sub 2$SO$sub 4$ SOLUTIONS UNDER IRRADIATION

Description: Results indicate that corrosion of the metal is accelerated to a small extent during irradiation. A summary of the results from in-pile loops and in- pile autoclaves is given. (L.M.T.)
Date: August 30, 1956
Creator: Jenks, G.H.
Partner: UNT Libraries Government Documents Department
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Longitudinal and Lateral Stability Characteristics of a 0.04-Scale Model of the Lockheed F-104A Airplane at Mach Numbers of 1.82 and 2.01. Coord. No. AF-245

Description: "An investigation has been made in the Langley 4 by 4-foot supersonic pressure tunnel at Mach numbers of 1.82 and 2.01 to determine the longitudinal and lateral static-stability characteristics of a 0.04-scale model of the Lockheed F-104A airplane. The effects of a modified vertical tail, several ventral-fin arrangements, and several external store arrangements were also determined. The tests were made at Reynolds numbers of 1.02 (exp 6) and 1.382 (exp 6), respectively, based on the wing mean g… more
Date: August 30, 1956
Creator: Spearman, M. Leroy & Driver, Cornelius
Partner: UNT Libraries Government Documents Department
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