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Transistorization of Nuclear Counting Circuits

Description: From Abstract: "The advantage of long operational life, low power drain and miniaturization may be realized in nuclear counting circuits through the use of transistors. The disadvantage of instability, due to the effects of temperature change in the transistor, may be minimized in counting circuit designs. Representative circuits of a binary stage, amplitude discriminator, one shot multivibrator, and ratemeters are included. These were designed using the criteria of an minimum Beta and a maximum Ico."
Date: August 19, 1957
Creator: Graveson, R. T. & Sadowski, H.
Partner: UNT Libraries Government Documents Department
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Transonic Wind-Tunnel Investigation of Static-Pressure Fluctuations in Duct of a Scale Inlet Model of a Supersonic Fighter-Bomber Airplane

Description: Report presenting a transonic investigation of the static-pressure fluctuations in the left duct of a scale inlet model of a supersonic fighter-bomber airplane in the transonic tunnel. Results regarding amplitude characteristics of pressure fluctuations, power-spectral analyses, and flow distortions at compressor face are provided.
Date: August 6, 1957
Creator: Brooks, Joseph D.
Partner: UNT Libraries Government Documents Department
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Investigation of a 1/22-Scale Model of the Republic F-105 Airplane in the Langley 8-Foot Transonic Tunnel: Lateral, Directional, and Additional Longitudinal Static Stability and Control

Description: Report presenting an investigation of the aerodynamic characteristics of various configurations of the Republic F-105 at Mach numbers from 0.60 to 1.13. The primary focus of this report are the static lateral and directional stability and control characteristics of the model. Results regarding force and moment results, longitudinal characteristics, lateral and directional characteristics.
Date: August 23, 1957
Creator: Luoma, Arvo A.
Partner: UNT Libraries Government Documents Department
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Design and performance of flight-type liquid-hydrogen heat exchanger

Description: Report presenting an investigation of a liquid-hydrogen fuel system developed to operate one of the turbojet engines in a twin-engine light bomber at an altitude of 50,000 feet and Mach number 0.75. The heat exchanger was evaluated in an altitude test chamber in conjunction with the complete aircraft fuel system. Results regarding calculated heat-exchanger performance, experimental heat-exchanger performance, and reliability are provided.
Date: August 19, 1957
Creator: Fenn, David B.; Braithwaite, Willis M. & Ordin, Paul M.
Partner: UNT Libraries Government Documents Department
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Design and Performance of Fuel Control for Aircraft Hydrogen Fuel System

Description: Memorandum presenting the system analysis, design, and performance of a control system for an experimental flight-type hydrogen fuel system. The fuel system was designed to investigate some of the problems associated with the utilization of hydrogen as an aircraft fuel. Speed control of the engine was obtained by coupling the hydrogen regulator to the JP-4 fuel control.
Date: August 19, 1957
Creator: Otto, Edward W.; Hiller, Kirby W. & Ross, Phil S.
Partner: UNT Libraries Government Documents Department
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Flight Investigation of a Liquid Hydrogen Fuel System

Description: Memorandum presenting testing of a twin-engine light bomber modified to utilize hydrogen fuel in one of the two engines during flight at an altitude of 50,000 feet. Three completely successful flights were made using hydrogen fuel. Data are presented to show the effect of tank agitation on fuel pressure and fuel losses.
Date: August 19, 1957
Creator: Mulholland, Donald R.; Acker, Loren W.; Christenson, Harold H. & Gough, William V.
Partner: UNT Libraries Government Documents Department
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Altitude chamber evaluation of an aircraft liquid hydrogen fuel system used with a turbojet engine

Description: From Introduction: "The objective of this report are (1) to describe the complete fuel system, (2) to discuss the procedure used for transitions between JP-4 fuel and hydrogen, and (3) to present and discuss engine performance obtained with both fuels, and (4) to review the reliability of the fuel system."
Date: August 19, 1957
Creator: Braithwaite, Willis M.; Fenn, David B. & Algranti, Joseph S.
Partner: UNT Libraries Government Documents Department
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Free Flight Investigation at Transonic Speeds of the Power-on Characteristics Including Some Effects of Sonic Propulsive Jets of a Four Engine Delta Wing Configuration

Description: Report discussing a model of a delta-wing configuration with four engines mounted two to a nacelle below the wing that was tested a variety of Mach numbers and Reynolds numbers. The wing static-pressure coefficients, wing pressure coefficients, and lift coefficient of different configurations are described.
Date: August 16, 1957
Creator: Falanga, Ralph A. & Judd, Joseph H.
Partner: UNT Libraries Government Documents Department
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The Design and Cascade Tests of Free-Streamline and Full-Contour 160 Degree Turning Supersonic-Turbine-Blade Sections

Description: Memorandum presenting the flow characteristics of two supersonic-impulse-turbine-blade sections designed for a turning angle of 160 degrees. Results regarding the full-contour blade, free streamline blades, and a comparison of the performance are provided.
Date: August 16, 1957
Creator: Westphal, Willard R.
Partner: UNT Libraries Government Documents Department
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Relation of Turbojet and Ramjet Combustion Efficiency to Second-Order Reaction Kinetics and Fundamental Flame Speed

Description: Theoretical studies of the turbojet and ramjet combustion process are summarized and the resulting equations are applied to experimental data obtained from various combustor tests. The theoretical treatment assumes that one step in the over-all chain of processes which constitute jet-engine combustion is sufficiently slow to be the rate-controlling step that determines combustion efficiency.
Date: August 5, 1957
Creator: Childs, J. Howard; Reynolds, Thaine W. & Graves, Charles C.
Partner: UNT Libraries Government Documents Department
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A Fuselage Addition to Delay Drag-Rise Mach Number of Subsonic Airplanes at Lifting Conditions

Description: "The addition of fuselage volume, concentrated on top of the forward portion of the fuselage, for the purpose of delaying the drag-rise Mach number of subsonic airplanes at lifting conditions is investigated. The additions have been designed on the basis of the area rule and other important considerations to provide greater practicability of application compared with shapings previously investigated. The addition delayed the drag-rise Mach number by an increment of approximately 0.03 for a configuration having a wing with moderate thickness and 35 deg of sweepback at a lift coefficient of 0.3. A lesser delay was obtained for a configuration with a thicker wing. The additions increase the nonlinearities of the variations of pitching moment with lift" (Abstract).
Date: August 6, 1957
Creator: Whitcomb, Richard T.
Partner: UNT Libraries Government Documents Department
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Aerodynamic Forces on a Vibrating Unstaggered Cascade

Description: "The unsteady aerodynamic forces, [based on two-dimensional incompressible flow considerations], are determined for an unstaggered cascade, the blades of which are vibrating in phase in an approach flow parallel to the blades" (p. 1).
Date: August 1957
Creator: Söhngen, H.
Partner: UNT Libraries Government Documents Department
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Study of the Micro-Nonuniformity of the Plastic Deformation of Steel

Description: "The plastic flow during deformation of real polycrystalline metals has specific characteristics which distinguish the plastic deformation of metals from the deformation of ordinary isotropic bodies. One of these characteristics is the marked micro-nonuniformity of the plastic deformation of metals. P.O. Pashkov demonstrated the presence of a considerable micro-nonuniformity of the plastic deformation of coarse-grained steel wit medium or low carbon content" (p. 1).
Date: August 1957
Creator: Chechulin, B. B.
Partner: UNT Libraries Government Documents Department
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Two-dimensional airfoil characteristics of four NACA 6A-series airfoils at transonic Mach numbers up to 1.25

Description: "A two-dimensional wind-tunnel investigation of the flow and force characteristics of four NACA 6A-series airfoils with thickness ratios of 4, 6, and 9 percent has been conducted in the Langley airfoil test apparatus at at transonic Mach numbers between 0.8 and 1.25. The Reynolds number range for these tests varied from 2.6 x 10(6) to 2.8 x 10(6). As was expected, the airfoils exhibited a smooth transition in force coefficients from a Mach number of 1.0 to the values obtained at the higher speeds. Lift-curve slope and maximum lift-drag ratio correlated very well on a basis of the transonic similarity laws at Mach numbers above 1.0, but below that value the correlation was not good" (p. 1).
Date: August 6, 1957
Creator: Ladson, Charles L.
Partner: UNT Libraries Government Documents Department
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Stability of Laminar Boundary Layer Near a Stagnation Point Over an Impermeable Wall and a Wall Cooled by Normal Fluid Injection

Description: Note presenting a theoretical determination of minimum critical Reynolds numbers for laminar instability of two-dimensional stagnation flows over a wall cooled by normal fluid injection. The individual and net effects of wall temperature and normal fluid injection on the stability characteristics of the laminar boundary layer are investigated.
Date: August 1957
Creator: Morduchow, Morris; Grape, Richard G. & Shaw, Richard P.
Partner: UNT Libraries Government Documents Department
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A Method Utilizing Data on the Spiral, Roll-Subsidence, and Dutch Roll Modes for Determining Lateral Stability Derivatives From Flight Measurements

Description: Note presenting a method for determining lateral stability derivatives from flight measurements, which is obtained by arranging the lateral equations of motion in such form that information from each of the three modes of lateral motion may be utilized. The method permits determination of all the important derivatives without requiring an estimation of any of the derivatives. Results regarding the probable errors in measurements, errors in derivatives, effect of side-force rate derivatives, and some improvements in the method are provided.
Date: August 1957
Creator: Klawans, Bernard B. & White, Jack A.
Partner: UNT Libraries Government Documents Department
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Tensile properties of Inconel X sheet under rapid-heating and constant-temperature conditions

Description: From Summary: "Results of rapid-heating tests of Inconel X sheet are presented for nominal temperature rates of 0.2 degrees F to 100 degrees F per second under constant tensile load conditions. Yield and rupture stresses obtained under rapid-heating conditions are compared with the results of conventional tensile stress-train tests at elevated temperatures. A marked increase in strength is observed with increased temperature rates."
Date: August 1957
Creator: Kurg, Ivo M.
Partner: UNT Libraries Government Documents Department
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Review and Investigation of Unsatisfactory Control Characteristics Involving Instability of Pilot-Airplane Combination and Methods for Predicting These Difficulties From Ground Tests

Description: Report presenting tests of a bomber and fighter airplane with experimental power control systems in order to explore some unsatisfactory control characteristics that seem to result from dynamic instability. The main explanation found in testing was the presence of static friction in the control valves of hydraulic-power control systems.
Date: August 1957
Creator: Phillips, William H.; Brown, B. Porter & Matthews, James T., Jr.
Partner: UNT Libraries Government Documents Department
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Stability Limits and Burning Velocities for Some Laminar and Turbulent Propane and Hydrogen Flames at Reduced Pressure

Description: Note presenting the effect of reduced pressure on blowoff, flashback, and burning velocities of propane-oxygen-nitrogen burner flames were studied. The pressure exponent of burning velocity, 0.22, was nearly the same as for hydrogen-air flames; stability loops showed the same blowoff and flashback characteristics as were previously observed for hydrogen-air flames. Of the two system, the hydrogen-air system showed larger burning velocity, greater stability toward reduced pressure, and higher reaction order, and the propane-oxygen-nitrogen system showed the larger reactivity based on flashback.
Date: August 1957
Creator: Fine, Burton
Partner: UNT Libraries Government Documents Department
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Flight-Test Investigation on the Langley Control-Line Facility of a Model of a Propeller-Driven Tail-Sitter-Type Vertical-Take-Off Airplane with Delta Wing During Rapid Transitions

Description: Note presenting a flight-test investigation made on the control-line facility to determine the longitudinal stability and control characteristics of a model of a propeller-driven tail-sitter-type vertical-take-off airplane with delta wing during rapid transitions from hovering flight to forward flight and back to hovering. Results regarding transition from hovering flight to forward flight, transition from forward flight to hovering flight, and evaluation of control-line technique are provided.
Date: August 1957
Creator: Schade, Robert O.
Partner: UNT Libraries Government Documents Department
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Compressive Stress-Strain Properties of 17-7 PH and AM 350 Stainless-Steel Sheet at Elevated Temperatures

Description: Note presenting compressive stress-strain test results for 17-7 PH and AM 350 stainless-steel sheet in the heat-treated and annealed conditions for temperatures from room temperature to 1200 degrees Fahrenheit. Representative stress-strain curves are given for both materials at the test temperatures.
Date: August 1957
Creator: Stein, Bland A.
Partner: UNT Libraries Government Documents Department
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A Discussion of Cone and Flat-Plate Reynolds Numbers for Equal Ratios of the Laminar Shear to the Shear Caused by Small Velocity Fluctuations in a Laminar Boundary Layer

Description: "By use of the linear theory of boundary-layer stability and Schlichting's formula for the maximum amplification of a disturbance, an approximate relation is derived between the Reynolds number on a cone and the Reynolds number on a flat plate for equal closeness to transition. The indication is that the ratio of the cone Reynolds number for transition, based on the distance to the cone apex, to the plate Reynolds number for transition, based on the distance to the leading edge, is not in general equal to 3, as has been suggested by other investigators, but varies from 3 when transition occurs at the minimum critical Reynolds number to unity when transition occurs at a large multiple of the critical Reynolds number" (p. 1).
Date: August 1957
Creator: Tetervin, Neal
Partner: UNT Libraries Government Documents Department
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Effects of blade plan form on free-space oscillating pressures near propellers at flight Mach numbers to 0.72

Description: Report presenting a series of measurements made on the oscillating pressures near a tapered-blade-plan-form propeller at flight Mach numbers up to 0.72. Flight Mach number, power, and engine speed were controlled in an attempt to duplicate the conditions of a previous flight investigation. Results regarding effects of flight Mach number, effect of engine speed, and effects of engine power are provided.
Date: August 1957
Creator: Kurbjun, Max C.
Partner: UNT Libraries Government Documents Department
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Low-speed experimental investigation of the magnus effect on various sections of a body of revolution with and without a propeller

Description: Report presenting an investigation at low speed to determine the Magnus effect on various sections of a body of revolution of which several sections could be rotated either as individual units or in combinations. The investigation included the measurement of the Magnus effect on the body alone and on the body with a three-blade propeller.
Date: August 1957
Creator: Queijo, M. J. & Fletcher, Herman S.
Partner: UNT Libraries Government Documents Department
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