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Preliminary Design Requirements Argonne Boiling Reactor (ARBOR) Facility

Description: From Introduction: "Descriptions of the functional requirements of the facility, together with preliminary concepts of methods for meeting them, are presented in this prospectus."
Date: July 15, 1957
Creator: Fromm, L. W.; Bernsen, S. A.; Bullinger, C. F. & Matousek, J. F.
Partner: UNT Libraries Government Documents Department
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Resistance of Materials to Attack by Liquid Metals

Description: From Forward: "As their contribution, the Metallurgy Division of Argonne National Laboratory was asked to assemble all available unclassified and declassifiable data on the resistance of materials to attack by liquid metals. The resulting collation of data is contained in this report."
Date: July 1950
Creator: Kelman, LeRoy R.; Wilkinson, Walter D. & Yaggee, Frank L.
Partner: UNT Libraries Government Documents Department
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Some Effects of Aileron Deflection on the Static Lateral and Directional Aerodynamic Characteristics of Four Contemporary Airplane Models

Description: Memorandum presenting some effects of aileron deflection on the static lateral and directional aerodynamic characteristics of four airplane models which are representative of aircraft capable of flight at supersonic speeds. The results are presented for subsonic Mach numbers ranging from 0.60 to 0.90 and for supersonic Mach numbers ranging from 1.20 to 1.90. They are limited to the most pertinent aerodynamic effects of ailerons contributing to the lateral and directional characteristics of each airplane type.
Date: July 23, 1957
Creator: Smith, Willard G. & Intrieri, Peter F.
Partner: UNT Libraries Government Documents Department
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Preliminary Evaluation of Flight-Weight XRJ47-W-5 Ram-Jet Engine at a Mach Number of 2.75

Description: Report presenting a free-jet investigation of the performance, burner-shell cooling, and ignition characteristics of a flight-weight 48-inch-diameter XRJ47-W-5 ramjet engine at an inlet Mach number of 2.75 and an angle of attack of 3 degrees. Data were obtained over a range of altitudes, inlet temperatures, and fuel-air ratios.
Date: July 26, 1955
Creator: Welna, Harry J. & Reilly, Dwight H.
Partner: UNT Libraries Government Documents Department
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A Wind-Tunnel Investigation of the Wing Loads Due to Deflected Inboard Ailerons on a 45 Degree Sweptback Wing at Transonic Speeds

Description: Memorandum presenting the effects of deflected inboard ailerons on the wing loads of a 45 degree sweptback wing-body combination in the 16-foot transonic tunnel. The model had a wing with an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections. Results regarding the chordwise pressure distributions, effect of ailerons on wing section loadings, effect of aileron on wing loading, and effects of a deflected aileron on opposite-wing loading are provided.
Date: July 21, 1958
Creator: Heath, Atwood R., Jr. & Igoe, Ann W.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Tests of the Static Longitudinal Characteristics at Low Speed of a Swept-Wing Airplane With Blowing Flaps and Leading-Edge Slats

Description: Memorandum presenting a wind-tunnel investigation of a high-wing airplane with an aspect ratio 6.75 wing with approximately 36 degrees of sweepback in order to determine the lift effectiveness obtainable with trailing-edge blowing flaps in combination with leading-edge slats. Close to theoretical flap effectiveness was obtained with blowing flaps deflected 45, 55, and 65 degrees at low angles of attack. Results regarding the wind tunnel, take-off performance, landing performance, and comparisons with flight data are provided.
Date: July 5, 1957
Creator: James, Harry A. & Maki, Ralph L.
Partner: UNT Libraries Government Documents Department
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The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselage-store Configurations 2 - Swept-wing Heavy-bomber Configuration With Large Store Nacelle. Lateral Forces and Pitching Moments, Mach Number, 1.61

Description: Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference performed in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.6. Separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The configuration investigated simulated a heavy bomber airplane with a large store or nacelle with frontal area equivalent to a twin-engine nacelle.
Date: July 6, 1955
Creator: Smith, Norman F. & Carlson, Harry W.
Partner: UNT Libraries Government Documents Department
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Force and Pressure-Distribution Investigation to High Angles of Attack on All-Movable Triangular and Rectangular Wings in Combination With a Body at Supersonic Speeds

Description: Force and pressure distribution studies to high angles of attack on all-movable triangular and rectangular wings in combination with body at supersonic speeds. The ranges of aspect ratios were, for the triangular wings, 3/8 to 4, and for the rectangular wings, 1 to 3.
Date: July 10, 1956
Creator: Hill, William A., Jr. & Kaattari, George E.
Partner: UNT Libraries Government Documents Department
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Some Considerations Regarding the Application of the Supersonic Area Rule to the Design of Airplane Fuselages

Description: Memorandum presenting certain considerations and techniques pertinent to the application of the supersonic area rule to the design of airplane fuselages. Some of the factors considered are an extension of the rule to account for the interference effects of the wing and tail on the general flow field for asymmetrical configurations, the determination of fuselage area developments which result in approximately the minimum wave drag, and the influence of wing parameters and design Mach number on the effectiveness of fuselage shaping.
Date: July 3, 1956
Creator: Whitcomb, Richard T.
Partner: UNT Libraries Government Documents Department
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Reaction of Fluorine With Carbon as a Means of Fluorine Disposal

Description: Report discussing an investigation into the binding of amorphous carbon with flourine to render it inert and easy to vent into the atmosphere.The ease and safety of the procedure are described.
Date: July 18, 1957
Creator: Schmidt, Harold W.
Partner: UNT Libraries Government Documents Department
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Theoretical Performance of Liquid Ammonia and Liquid Fluorine as a Rocket Propellant

Description: "Theoretical values of performance parameters for liquid ammonia and liquid fluorine as a rocket propellant were calculated on the assumption of equilibrium composition during the expansion process for a wide range of fuel-oxidant and expansion ratios. The parameters included were 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" (p. 1).
Date: July 3, 1953
Creator: Gordon, Sanford & Huff, Vearl N.
Partner: UNT Libraries Government Documents Department
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Theoretical Performance of Mixtures of Liquid Ammonia and Hydrazine as Fuel With Liquid Fluorine as Oxidant for Rocket Engines

Description: Report presenting theoretical values of rocket performance parameters for two mixtures of liquid ammonia and hydrazine with flourine as oxidant for a variety of parameters. Parameters included are 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: July 29, 1953
Creator: Gordon, Sanford & Huff, Vearl N.
Partner: UNT Libraries Government Documents Department
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Theoretical Performance of Liquid Hydrazine and Liquid Fluorine as a Rocket Propellant

Description: "Theoretical values of performance parameters for liquid ammonia and liquid fluorine as a rocket propellant were calculated on the assumption of equilibrium composition during the expansion process for a wide range of fuel-oxidant and expansion ratios. The parameters included were 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" (p. 1).
Date: July 3, 1953
Creator: Gordon, Sanford & Huff, Vearl N.
Partner: UNT Libraries Government Documents Department
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Static Longitudinal and Lateral Stability Characteristics Including Effects of Transonic Area Rule and Wing Modification of a 0.10- Scale Model of the Douglas A4D-1 Airplane at Transonic Speeds

Description: Report discussing testing of a model of the Douglas A4D-1 to investigate the static longitudinal characteristics of wing and fuselage modifications and the static lateral characteristics of the basic model.
Date: July 6, 1956
Creator: Bollech, Thomas V. & Wornom, Dewey E.
Partner: UNT Libraries Government Documents Department
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Investigation of Control Effectiveness and Stability Characteristics of a Model of a Low-Wing Missile With Interdigitated Tail Surfaces at Mach Numbers of 2.29, 2.97, and 3.51

Description: "A brief investigation of the longitudinal stability and control effectiveness at supersonic speeds of a model of a low-wing missile with interdigitated tail surfaces was made in the Langley Unitary Plan wind tunnel. The data were obtained at Mach numbers M of 2.29, 2.97, and 3.51 for Reynolds number (based on the mean geometric chord of the wing) of 1.15 x 10(exp 6), 1.14 x 10(exp 6), and 1.11 x 10(exp 6), respectively. Data were obtained for three settings of the longitudinal control surfaces: with deflection of all surfaces, with deflection of the lower surfaces only, and with all surfaces undeflected" (p. 1).
Date: July 14, 1958
Creator: Presnell, John G., Jr.
Partner: UNT Libraries Government Documents Department
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Investigation of Aerodynamic and Icing Characteristics of Water-Inertia-Separation Inlets for Turbojet Engines

Description: "The results of an investigation of several internal water-inertia-separation inlets consisting of a main duct and an alternate duct designed to prevent automatically the entrance of large quantities of water into a turbojet engine in icing conditions are presented. Total-pressure losses and icing characteristics for a direct-ram inlet and the inertia-separation inlets are compared at similar aerodynamic and simulated icing conditions. Complete ice protection for inlet guide vanes could not be achieved with the inertia-separation inlets investigated" (p. 1).
Date: July 26, 1950
Creator: von Glahn, Uwe & Blatz, Robert E.
Partner: UNT Libraries Government Documents Department
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Improvements in Heat Transfer for Anti-Icing of Gas-Heated Airfoils with Internal Fins and Partitions

Description: "The effect of modifying the gas passage of hollow metal airfoils by the addition of internal fins and partitions was experimentally investigated and comparisons were made among a basic unfinned airfoil section and two airfoil designs having metal fins attached at the leading edge of the internal gas passage. An analysis considering the effects of heat conduction in the airfoil metal was made to determine the internal modification effectiveness that may be obtained in gas-heated components, such as turbojet-inlet guide vanes, support struts, hollow propeller blades, and thin wings" (p. 1).
Date: July 1950
Creator: Gray, Vernon H.
Partner: UNT Libraries Government Documents Department
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Boundary-Layer-Transition Measurements in Full-Scale Flight

Description: Report presenting tests of the extent of laminar flow that can be obtained with practical wing-surface conditions. Chemical sublimation was used for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight. A method of continuous monitoring using heat temperature resistance gauges was also used on one wing.
Date: July 28, 1958
Creator: Banner, Richard D.; McTigue, John G. & Petty, Gilbert, Jr.
Partner: UNT Libraries Government Documents Department
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Investigation of Aerodynamic and Icing Characteristics of a Flush Alternate Inlet Induction System Air Scoop

Description: "An investigation has been made in the NACA Lewis icing research tunnel to determine the aerodynamic and icing characteristics of a full-scale induction-system air-scoop assembly incorporating a flush alternate inlet. The flush inlet was located immediately downstream of the offset ram inlet and included a 180 deg reversal and a 90 deg elbow in the ducting between inlet and carburetor top deck. The model also had a preheat-air inlet" (p. 1).
Date: July 24, 1953
Creator: Lewis, James P.
Partner: UNT Libraries Government Documents Department
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Use of Truncated Flapped Airfoils for Impingement and Icing Tests of Full-Scale Leading-Edge Sections

Description: From Summary: "In an effort to increase the operational range of existing small icing tunnels, the use of truncated airfoil sections has been suggested. With truncated airfoils, large-scale or even full-scale wing-icing-protection systems could be evaluated. Therefore, experimental studies were conducted in the NACA Lewis laboratory icing tunnel with an NACA 651-212 airfoil section to determine the effect of truncating the airfoil chord on velocity distribution and impingement characteristics. A 6-foot-chord airfoil was cut successively at the 50- and 30-percent-chord stations to produce the truncated airfoil sections, which were equipped with trailing-edge flaps that were used to alter the flow field about the truncated sections. The study was conducted at geometric angles of attack of 00 and 40, an airspeed of about 156 knots, and volume-median droplet sizes of 11.5 and 18.6 microns. A dye-tracer technique was used in the impingement studies."
Date: July 24, 1956
Creator: von Glahn, Uwe H.
Partner: UNT Libraries Government Documents Department
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Preliminary Aerodynamic Data Pertinent to Manned Satellite Reentry Configurations

Description: Report presenting some experimental data and calculations for a variety of aerodynamic shapes considered for use as manned reentry vehicles. Three types of vehicles were tested: non-lifting bodies, lifting bodies, and airplane-like vehicles. All of the configuration types were found to be suitable for use as manned reentry vehicles with certain fin and flap modifications for certain shapes.
Date: July 21, 1958
Creator: Penland, Jim A. & Armstrong, William O.
Partner: UNT Libraries Government Documents Department
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