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Equation of State and Heat Content of Uranium

Description: Report issued by the APDA regarting studies conducted on the state of uranium at different temperature and pressure. Calculations are presented for the differing pressures of uranium; it includes tables.
Date: February 20, 1957
Creator: Brout, Robert H.
Partner: UNT Libraries Government Documents Department
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Nature of atmospheric dust. Progress report to January 15, 1955

Description: Optical microscopic examination of air- and rain-borne dust shows most of the particles to be less than one micron in diameter. Electron microscopic examination of the same dust shows predominantly clusters of particles whose individual diameters are in the range 200 to 1000 A. The residue obtained by filtering rain water through a millipore filter is found to be slightly radioactive in more than half the cases observed.
Date: January 20, 1955
Creator: Heininger, C. & Turkevich, J.
Partner: UNT Libraries Government Documents Department
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Thermal Bowing of Core Subassemblies

Description: Report issued by the APDA over studies conducted on thermal bowing of core sub-assemblies at the Enrico Fermi Atomic Power Plant. As stated in the introduction and summary, "the present report deals with this problem in the design of the Enrico Fermi Reactor and with the method which has been adopted to avoid a positive temperature coefficient of reactivity" (p. 1). This report includes illustrations, and photographs.
Date: February 20, 1959
Creator: De Stordeur, Arnold
Partner: UNT Libraries Government Documents Department
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Ditching Tests of a 1/18-Scale Model of the Lockheed Constellation Airplane

Description: "Tests were made of a 1/18-scale dynamically similar model of the Lockheed Constellation airplane to investigate its ditching characteristics and proper ditching technique. Scale-strength bottoms were used to reproduce probable damage to the fuselage. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and fuselage configurations were simulated" (p. 1).
Date: April 20, 1950
Creator: Fisher, Lloyd J. & Morris, Garland J.
Partner: UNT Libraries Government Documents Department
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Investigation of the Effects of Leading-Edge Flaps on the Aerodynamic Characteristics in Pitch at Mach Numbers From 0.40 to 0.93 of a Wing-Fuselage Configuration With a 45 Degree Sweptback Wing of Aspect Ratio 4

Description: Report presenting an investigation to determine the effects of a number of leading-edge flaps on the aerodynamic characteristics in pitch of a wing-fuselage configuration with a 45 degree sweptback wing. All of the flaps were found to reduce the drag in the medium lift range , but there were no significantly large effects on the lift characteristics for any of the arrangements studied.
Date: August 20, 1953
Creator: Spreemann, Kenneth P. & Alford, William J., Jr.
Partner: UNT Libraries Government Documents Department
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Friction and surface damage of several corrosion-resistant materials

Description: Friction and surface damage of several materials that are resistant to corrosion due to liquid metals was studied in air. The values of kinetic friction coefficient at low sliding velocities and photomicrographs of surface damage were obtained. Appreciable surface damage was evident for all materials tested. The friction coefficients for the combinations of steel, stainless steel, and monel sliding against steel, stainless steel, nickel, Iconel, and Nichrome ranged from 0.55 for the monel-Inconel combination to 0.97 for the stainless-steel-nickel combination; for steel, stainless steel, monel, and tungsten carbide against zirconium, the friction coefficient was approximately 0.47.
Date: February 20, 1952
Creator: Peterson, Marshall B. & Johnson, Robert L.
Partner: UNT Libraries Government Documents Department
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An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc section and 40 degree sweepback: a pressure-distribution study of the aerodynamic characteristics of the wing at Mach number 1.40

Description: Report discussing a pressure-distribution investigation of a wing of a supersonic aircraft in the presence of a fuselage at a specified Mach number and aerodynamic chord. The wing had a quarter chord swept back 40 degrees, an aspect ratio of 4, a taper ratio of 0.5, and 10-percent-thick circular-arc sections perpendicular to the quarter-chord line. The results were compared to a similar investigation at a different Mach number.
Date: April 20, 1951
Creator: Smith, Norman F.; Kainer, Julian H. & Webster, Robert A.
Partner: UNT Libraries Government Documents Department
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Flight Investigation From Mach Number 0.8 to 2.0 to Determine Some Effects of Wing-to-Tail Distance on the Longitudinal Stability and Control Characteristics of a 60 Degree Delta-Wing-Canard Missile

Description: Report presenting a flight investigation using rocket-powered models to determine some of the effects of wing-to-tail distance on the stability and control characteristics of a canard-missile configuration with 60 degree delta wings and control surfaces. Both models were tested over a range of Mach numbers from 0.8 to 2.0, and canard hinge moment and model drag data are presented. Testing indicated that additional fuselage length increases the lift-curve slope slightly and has very little effect on minimum drag.
Date: June 20, 1952
Creator: Brown, Clarence A., Jr. & Lundstrom, Reginald R.
Partner: UNT Libraries Government Documents Department
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Skin-friction drag and boundary-layer transition on a parabolic body of revolution (NACA RM-10)at a Mach number of 1.6 in the Langley 4-by-4 foot supersonic pressure tunnel

Description: Report presenting an investigation at Mach number 1.6 and a range of Reynolds number of the skin-friction drag and boundary-layer transition of a body of revolution. The body had a parabolic-arc profile, a blunt base, and a fineness ratio of 12.2 (NACA RM-10). Results regarding the effect of surface condition, drag breakdown, and results of boundary-layer surveys are provided.
Date: May 20, 1952
Creator: Czarnecki, K. R. & Marte, Jack E.
Partner: UNT Libraries Government Documents Department
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Large-scale flight measurements of zero-lift drag and low-lift longitudinal characteristics of a diamond-wing-body combination at Mach numbers from 0.725 to 1.54

Description: Report presenting a large-scale diamond-wing-body configuration flown at a range of Mach and Reynolds numbers. The model had a diamond-plan-form wing with an NACA 65A003 airfoil section, a total aspect ratio of 2.31, and 0 degrees sweep of the midchord. Results regarding zero-lift drag and low-lift longitudinal characteristics are provided.
Date: April 20, 1953
Creator: Wallskog, Harvey A. & Morrow, John D.
Partner: UNT Libraries Government Documents Department
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Some Measurements of Buffeting Encountered by Douglas D-558-II Research Airplane in the Mach Number Range From 0.5 to 0.95

Description: Report presenting a flight investigation of the variation of the intensity of buffeting with lift and Mach number using a Douglas D-558-II research airplane over a range of Mach numbers and altitudes. Buffeting was encountered during flight at all Mach numbers attained and during level flight at Mach numbers above 0.9. Results regarding the relationship between lift, angle of attack, and buffeting, buffet frequencies, and intensity of buffeting are provided.
Date: November 20, 1953
Creator: Baker, Thomas F.
Partner: UNT Libraries Government Documents Department
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Analysis of performance of four symmetrical-diagram-type subsonic inlet-stage axial-flow compressors

Description: Report presenting an investigation of four axial-flow single-stage compressors with a hub-tip radius ratio of 0.5 with three objectives related to the ideal symmetrical-velocity-diagram design, the comparison of blade-element turning angle and loss data with cascade data, and the validity of the simplified radial-equilibrium equation. Results regarding the overall performance, blade-element performance, and radial equilibrium considerations are provided.
Date: January 20, 1954
Creator: Jackson, Robert J.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of the Effects of a Fence and a Leading-Edge Notch on the Aerodynamic Loading Characteristics in Pitch of a 45 Degree Sweptback Wing at High Subsonic Speeds

Description: Report presenting an investigation in the high speed tunnel to determine the aerodynamic loading characteristics of a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section. The effects of fences and leading-edge notches over a range of Mach numbers and angles of attack were also explored. Results regarding chordwise load distributions and lateral center of pressure are provided.
Date: October 20, 1953
Creator: Kuhn, Richard E.; Wiggins, James W. & Byrnes, Andrew L., Jr.
Partner: UNT Libraries Government Documents Department
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Performance of a supersonic mixed-flow rotor with a swept leading edge and 0.52 inlet radius ratio

Description: Report presenting testing of a 14-inch supersonic mixed-flow rotor of high specific mass flow and an inlet radius ratio of 0.52, which was designed for impulse operation and uniform work output and tested in Freon-12. Results regarding the overall rotor performance, casing friction, entrance flow, distribution of static pressure on the casing, and exit flow are provided.
Date: November 20, 1953
Creator: Goldstein, Arthur W. & Schacht, Ralph L.
Partner: UNT Libraries Government Documents Department
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Experimental downwash and wake characteristics at subsonic and supersonic Mach numbers behind an unswept, tapered wing, of aspect ratio 2.67 with leading-and trailing-edge flaps

Description: Report presenting the effect of Mach number on the characteristics of the downwash and wake behind an unswept, tapered wing of aspect ratio 2.67 with full-span, 25-percent-chord, leading- and trailing-edge flaps has been determined from wind-tunnel tests. Results regarding downwash characteristics and wake characteristics are provided.
Date: April 20, 1951
Creator: Stivers, Louis S., Jr.; Walker, Harold J. & Beard, Luther, Jr.
Partner: UNT Libraries Government Documents Department
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Review of Current and Anticipated Lubricant Problems in Turbojet Engines

Description: Memorandum presenting a review of the current and anticipated lubricant problems as related to aircraft turbojet engines, which has indicated that the current and anticipated bearing operating temperature ranges to be met are specified. The most promising approaches, including types of lubricants and temperatures, are provided.
Date: April 20, 1951
Partner: UNT Libraries Government Documents Department
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Spontaneous ignition temperatures of pure hydrocarbons and commercial fluids

Description: From Summary: "The spontaneous ignition temperatures of 94 pure hydrocarbons and 15 fuels and commercial fluids were determined by a crucible method. The resulting data for the pure compounds are presented as functions of hydrocarbon structure."
Date: December 20, 1950
Creator: Jackson, Joseph L.
Partner: UNT Libraries Government Documents Department
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Tabulated pressure coefficients and aerodynamic characteristics measured on the wing of the Bell X-1 airplane in an unaccelerated low-speed stall, in push-overs at Mach numbers of 0.83 and 0.99, and in a pull-up at a Mach number of 1.16

Description: "Tabulated pressure coefficients and aerodynamic characteristics are presented for six spanwise stations on the left wing of the Bell X-1 research airplane. These data were obtained in an unaccelerated low-speed stall, in push-overs at Mach numbers of approximately 0.83 and 0.99, and in a pull-up at a Mach number of approximately 1.16" (p. 1).
Date: September 20, 1951
Creator: Knapp, Ronald J.
Partner: UNT Libraries Government Documents Department
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Tabulated Pressure Coefficients and Aerodynamic Characteristics Measured in Flight on the Wing of the D-558-I Research Airplane Through a Mach Number Range of 0.80 to 0.89 and Throughout the Normal-Force-Coefficient Range at Mach Numbers of 0.61, 0.70, 0.855, and 0.88

Description: "Tabulated pressure coefficients and aerodynamic characteristics obtained in flight from pressure distributions over six chordwise rows of orifices on the right wing of the D-558-I research airplane (BuAero No. 37972) are presented. The data were obtained through a Mach number range of 0.80 to 0.89 and throughout the normal-force-coefficient range at Mach numbers of 0.61, 0.70, 0.855, and 0.88. This paper supplements similar tabulated data which have been presented in NACA RM L50J10 and NACA RM L50L12a" (p. 1).
Date: August 20, 1951
Creator: Keener, Earl R. & Bandish, Rozalia M.
Partner: UNT Libraries Government Documents Department
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Effective Modulus in Plastic Buckling of High-Strength Aluminum-Alloy Sheet

Description: Memorandum presenting results of compressive tests on duplicate longitudinal specimens from sheets of 76S-T6 and R301-T aluminum alloys in three thicknesses as graphs of tangent modulus, secant modulus, and are plotted against stress on a dimensionless basis.
Date: September 20, 1951
Creator: Miller, James A. & Jacobs, Pearl V.
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of Forced-Convection Heat-Transfer Characteristics of Lead-Bismuth Eutectic

Description: The forced-convection heat-transfer characteristics of lead-bismuth eutectic were experimentally investigated. Experimental values of Nusselt number for lead-bismuth fell considerably below predicted values. The addition of a wetting agent did not change the heat transfer characteristics.
Date: September 20, 1951
Creator: Lubarsky, Bernard
Partner: UNT Libraries Government Documents Department
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An Investigation at Transonic Speeds of the Effects of Control Chord and Span on the Control Characteristics of a Tapered Wedge-Type Wing of Aspect Ratio 2.5: Transonic-Bump Method

Description: Report presenting an investigation to determine the control characteristics of flap-type controls of various chords and spans on an unswept wing with a modified double-wedge section, an aspect ratio of 2.5, and a taper ratio of 0.625.The control chords in the study were 25, 35, and 45 percent of the wing chord, and the control spans were 25, 50, and 75 percent of the wing semispan. The data from the study indicated that the control-parameter values are approximately proportional to control chord or span for the chords tested.
Date: September 20, 1951
Creator: Vogler, Raymond D.; Lockwood, Vernard E. & Turner, Thomas R.
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of Effect of Jet Exit Configuration on Thrust and Drag

Description: Memorandum presenting an investigation of the problem of performance losses occurring when airplanes equipped with afterburner and cooling-air ejector installations are flown with the afterburner inoperative. Two sources of the performance losses occurring under some operation conditions were identified: an overexpansion of the propulsive jet and an internal shock system and the excessive pumping action resulting from the off-design.
Date: December 20, 1951
Creator: Callaghan, Edmund E. & Coles, Willard D.
Partner: UNT Libraries Government Documents Department
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The Effect on Zero-Lift Drag of an Indented Fuselage or a Thickened Wing-Root Modification to a 45 Degree Sweptback Wing-Body Configuration as Determined by Flight Tests at Transonic Speeds

Description: Report presenting a study of rocket-powered models at transonic speeds to determine the effect on the zero-lift drag coefficient of an indented fuselage modification and a thickened wing-root modification of a swept-wing airplane configuration. Results regarding the variation of drag coefficient with Mach number, effect of wing root thickening, and wing-plus-interference drag coefficients for the tested models are provided.
Date: September 20, 1951
Creator: Pepper, William B.
Partner: UNT Libraries Government Documents Department
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