Technical Report Archive & Image Library (TRAIL) - 991 Matching Results
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- The Determination of Total Plutonium in the Presence of Aluminum
- Introduction: "The adoption of aluminum nitrate as salting agent in the Redox process made it imperative that a method be available for determining plutonium in the presence of aluminum. However, large amounts of aluminum have been found to interfere with the determination of plutonium by the lanthanum fluoride procedure. Previous attempts to increase the accuracy of the lanthanum fluoride method, by precipitating LaF3 from 4 M HF (rather than 2 M), have been successful only when the initial plutonium level was high."
- The Determination of Tributyl Phosphate in Deodorized Shell Base with the Infrared Spectrometer
- The following report describes methods used to determine tributylphosphate in a deodorized shell base. An infrared absorption method is developed to emphasize toward determination of TBP in RCW streams, the organic waste streams.
- The Determination of Uranyl Nitrate in Pretreated Hexone by Infrared Absorption Measurements
- The following report examines methods to determine uranium nitrate hexahydrate on pretreated hexone in the range of 0 to 40 g./l. by infrared absorption measurements.
- The development and performance of two small tunnels capable of intermittent operation at Mach numbers between 0.4 and 4.0
- Report presenting the design, development, and performance of equipment suitable for use by educational institutions for student training and basic compressible-flow research. Supersonic nozzles designed for a range of Mach numbers were tested in the blowdown tunnel and produced average Mach numbers close to the design values.
- Development and Preliminary Investigation of a Method of Obtaining Hypersonic Aerodynamic Data by Firing Models Through Highly Cooled Gases
- Note presenting a method of investigating hypersonic aerodynamic phenomena by firing simple symmetrical models at high velocity through a very cold gas with a low sonic velocity. Schileren photographs and focused shadowgraphs were taken of cylindrical models with conical forebodies with apex angles of 30, 45, and 60 degrees.
- Development for Techniques for Rolling Uranium Metal
- Uranium can be rolled from cast metal or forged ingot to sheet satisfactory for cupping, deep drawing, and similar fabrication procedures by a combination of hot breakdown in the neighborhood of 600 deg C and warm finishing at 225 to 325 deg C. Sheet may also be obtained by hot rolling alone and by warm rolling alone. However, it is difficult to secure a uniform, controlled grain size by hot rolling only and warm rolling is time consuming because of the limited reduction per pass obtainable. The combination of hot and warm rolling afforded best and most practical method to secure good quality sheet in the quantity required. The percent reduction by hot working does not appear to be critical, but at least 60% warm reduction is desirable to obtain complete and controlled grain size by recrystallization with high ductility and strength properties. Except for research investigation, rolling of uranium below 225 deg C is not recommended. In the temperature range considered (below 225 deg C), reduction is difficult and must be limited to one to two percent if edge cracking is to be avoided. Hot rolling of unplated uranium from the as-cast or as-forged surface is recommended, using a bath of 35% Li2CO3 plus 65% K2CO3 for a heating medium. No further preparation other than washing the salt from the hot rolled surface is required before warm rolling, and a bath of Meltemp No. 7 oil is recommended for warm rolling. Work roll speeds and temperatures are not critical, and moderate to light reductions per pass are recommended for easiest rolling and best results. Alternate cross-rolling is recommended during hot breakdown, but continuous rolling in one direction during warm finished is satisfactory. Starting with an as-cast tensile strength averaging 60,000 psi, as-rolled sheet up to 230,000 psi was produced, …
- The Development of a Hollow Blade for Exhaust Gas Turbines
- The subject of the development of German hollow turbine blades for use with internal cooling is discussed in detail. The development of a suitable blade profile from cascade theory is described. Also a discussion of the temperature distribution and stresses in a turbine blade is presented. Various methods of manufacturing hollow blades and the methods by which they are mounted in the turbine rotor are presented in detail.
- The Development of a Melting Method for Conversion of Zirconium Sponge to Corrosion Resistant Ingot
- This report covers an investigation meant to find the feasibility of producing corrosion resistant zirconium from sponge by special melting techniques. The zirconium metal has certain required specifications, such as: the metal must be free from bafnium, and it must be free from other impurities of undesirable neutron cross section.
- Development of a Mobile Compressor and Utility Station
- Report issued by the U.S. Bureau of Mines on the development of a mobile compressor and utility station in the oil-shale mine near Rifle, Colorado during 1949. The report includes photographs and illustrations of the mobile station.
- Development of Forging Techniques for Uranium
- Uranium has been successfully forged using a Lobdell-Nazel forging hammer and a forging temperature range of 500 to 650 degrees centigrade. Using standard forging techniques, the metal readily flowed at the temperature chosen. A noticeable increase in tensile strength, yield strength and percent elongation was obtained in forged metal as compared with cast metal. To obtain complete recrystallization and uniform grain size, a minimum of approximately 75 percent reduction in cross section by forging followed by an anneal within the range of 500 to 600 degrees C is required.
- The Development of Plutonium Electrodeposition Methods : Interim Report
- From introduction: "The following report presents a body of information obtained in the Health Instrument Development Laboratory from September, 1948, to the present, and is intended to be a preliminary review of [the study of electrodeposition of plutonium]. Many improvements in technique and methods and investigations along lines not explored are suggested by the present work. These will be undertaken as time permits, and reported at a later time."
- Diffusion and Production of Neutrons by Photon in D₂O
- "The neutron yield resulting from the photo-disintegration of deuterium in heavy water was calculated in this report."
- The Diffusion of a Hot Air Jet in Air in Motion Part 2: The Flow Field in the Transition Zone
- The turbulent diffusion of a hot air jet in air can be divided into two zones, the core and the transition zone. The present report deals with the transitional zone.
- The Distribution of Trace Uranium (VI) in Nitric Acid--TTA--Organic Solvent Mixtures
- Three constants can be used to calculate the distribution coefficient of uranium (VI) with an accuracy of 15% in pentaether-nitric acid mixtures containing up to 1.42M total nitric acid and 0.6M TTA and in cyclohexanone-nitric acid mixtures containing up to 1.0M total nitric acid and 0.5M TTA.
- Ditching Investigation of a 1/10-Scale Model of the Grumman F9F-2 Airplane, TED No. NACA DE 335
- An investigation was made of a 1/10-scale dynamically similar model of the Grumman FgF-2 airplane to study its behavior when ditched. The model was landed in calm water at the Langley Tank No. 2 monorail. Various landing attitudes, speeds, and configurations were investigated. The behavior of the model was determined from visual observations, acceleration records, and motion-picture records of the ditchings. Data are presented in tabular form, sequence photographs, time-history acceleration curves, and plots of attitude and speed against distance after contact.
- Ditching Investigation of a 1/14-Scale Model of the Northrop C-125 Airplane
- "An investigation of a 1/14-scale dynamically similar model of the Northrop C-125 airplane was made to determine the ditching characteristics and proper ditching technique for the airplane. Various conditions of damage, landing attitude, flap setting, and speed were investigated. The behavior of the model was determined from visual observations, motion-picture records, and time-history deceleration records" (p. 1).
- Ditching Investigation of a 1/15-Scale Model of the Convair-Liner Airplane
- A ditching investigation of a model of the Convair-Liner airplane was made to observe the behavior and determine the safest procedure for making an emergency water landing. The ditching model was designed and constructed by the National Advisory Committee for Aeronautics. Design information on the airplane was furnished by the Consolidated Vultee Aircraft Corporation. A three-view drawing of the airplane is shown. The investigation was made in calm water at the Langley tank no. 2 monorail.
- Ditching Investigation of a 1/24-Scale Model of the Boeing B-47 Airplane
- "An investigation of a 1/24-scale dynamically similar model of the Boeing B-47 airplane was made to determine the ditching characteristics and proper ditching technique for the airplane. Various conditions of damage, landing attitude, flap setting, and speed were investigated. The behavior of the model was determined from visual observations, motion-picture records, and time-history deceleration records. The results of the investigation are presented in table form, photographs, and curves" (p. 1).
- Ditching Tests of a 1/18-Scale Model of the Lockheed Constellation Airplane
- "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).
- Ditching Tests With a 1/16-Size Model of the Navy XP2V-1 Airplane at the Langley Tank No. 2 Monorail
- Report discussing tests using a model of the Navy XP2V-1 to study its performance when ditched. From Summary: "Various landing attitudes, speeds, and conditions of damage were simulated. The performance of the model was determined and recorded from visual observations, by recording time histories of the longitudinal decelerations, and by taking motion pictures of the ditchings."
- Downwash in Vortex Region Behind Rectangular Half-Wing at Mach Number 1.91
- Results of an experimental investigation to determine downwash and wake characteristics in region of trailing vortex system behind a rectangular half-wing at Mach number 1.91 are presented. The wing had a 5-percent thick symmetric diamond cross section beveled to a knife edge at the tip. At small angles of attack, downwash angles were in close agreement with predictions of linearized theory based on the assumption of an undistorted vortex sheet. At higher angles of attack, the flow was greatly influenced by the rolling up of the vortex sheet.
- Drag Investigation of Some Fin Configurations for Booster Rockets at Mach Numbers Between 0.5 and 1.4
- Report discussing testing to obtain data on booster drag estimates and to investigate the drag of various booster fin configurations. Several tie-rod-braced fin assemblies were investigated with various types and arrangement of tie rods as well as a cantilever fin assembly. The cantilever fin assembly was found to have roughly the same drag coefficients as the most efficient tie-rod-braced assembly.
- Dynamic Investigation of Turbine-Propeller Engine Under Altitude Conditions
- Memorandum presenting an investigation of the dynamics of a turbine-propeller engine in the altitude wind tunnel employing the frequency-response technique for a range of pressure altitudes form 10,000 to 30,000 feet. The investigation showed that the dynamic responses generalized for pressure altitude over the range of frequencies investigated. Results regarding steady-state characteristics, the linearity investigation, and dynamic characteristics are provided.
- The dynamic lateral control characteristics of airplane models having unswept wings with round-and sharp-leading-edge sections
- Report presenting an investigation in the free-flight tunnel for the purpose of comparing the dynamic lateral control characteristics of airplane models with round- and sharp-leading-edge wing sections. The two dynamic models used in the investigation had different mass characteristics and had different types of inertia. Results regarding the interpretation of flight-test results, high-inertia model, and normal-inertia model are provided.
- Dynamic Response of Control Servo System Installed in NAES-Equipped SB2C-5 Airplane (BuAer No. 83135)
- "Dynamic--response measurements for various conditions of displacement and rate signal input, sensitivity setting, and simulated hinge moment were made of the three control-surface servo systems of an NAES-equipped remote-controlled airplane while on the ground. The basic components of the servo systems are those of the General Electric Company type G-1 autopilot using electrical signal sources, solenoid-operated valves, and hydraulic pistons. The test procedures and difficulties are discussed" (p. 1).
- Dynamic Similitude Between a Model and a Full-Scale Body for Model Investigation at Full-Scale Mach Number
- Note presenting an analysis for interpreting results of dynamic tests of a model investigated at full-scale Mach number in terms of the corresponding full-scale body. The analysis indicates that dynamic similarity for such a condition can be closely approximated although the effect of gravity is not to scale.
- Dynamics of a turbojet engine considered as a quasi-static system
- Report presenting a determination of the dynamic characteristics of a typical turbojet engine with a centrifugal compressor, a sonic-flow turbine-nozzle diaphragm, and a fixed-area exhaust nozzle. Results indicate that a linear differential equation for engine acceleration as a function of fuel flow and engine speed for operation near a steady-state operating condition can be written.
- The effect of accelerating a hypothetical aircraft through the transonic range with controls fixed
- Memorandum presenting Mach number histories of the motion experienced by a hypothetical, small, straight-wing aircraft accelerating at various rates through an assumed controls-fixed pitch-down balance change in the transonic range. Two approximate analytical solutions of the longitudinal equations of motion are developed which are based on certain simplifying assumptions indicated by the differential-analyzer results.
- Effect of air distribution on radial temperature distribution in one-sixth sector of annular turbojet combustor
- Report presenting an experimental investigation in a one-sixth sector of an annular turbojet combustor to determine a method of controlling radial exhaust-gas-temperature distribution in a gas-turbine combustion chamber. The adjustment in controlling air was made by ducting the dilution air into the combustion zone in a predetermined manner through hollow radial struts or by modifying the basket-wall open-hole area. Results regarding the temperature distribution, temperature-rise efficiency, total-pressure loss, and altitude operating limits are provided.
- Effect of an Autopilot Sensitive to Yawing Velocity on the Lateral Stability of the Douglas D-558-II Airplane
- A theoretical investigation has been made to determine the effect on the lateral stability of the Douglas D-58-II airplane of an autopilot sensitive to yawing velocity. The effects of inclination of the gyro spin axis to the flight path and of tire lag in the autopilot were also determined. The flight conditions investigated included landing at sea level, approach condition at 12,000 feet, and cruising at 50,000 feet at Mach numbers of 0.80 and 1.2. The results of the investigation indicated that the lateral stability characteristics of the D-558-II airplane for the flight condition discussed should satisfy the Air Force - Navy period-damping criterion when the proposed autopilot is installed. Airplane motions in sideslip subsequent to a disturbance in sideslip are presented for several representative flight conditions in which a time lag in the autopilot of 0.10 second was assumed.
- Effect of an End Plate on the Aerodynamic Characteristics of a 20.55 Degree Sweptback Wing with an Aspect Ratio of 2.67 and a Taper Ratio of 0.5.: Transonic-Bump Method
- "An investigation by the transonic-bump method conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effect of an end plate on the aerodynamic characteristics of a 20.55 degree sweptback wing with an aspect ratio of 2.67 and a taper ratio of 0.5 indicated that the end plate affected the aerodynamic characteristics of the wing at transonic Mach numbers in the same manner as has been observed for swept and unswept wings at low speeds" (p. 1).
- Effect of an unswept wing on the contribution of unswept-tail configuration to the low-speed static and rolling-stability derivatives of a midwing airplane model
- Report presenting an investigation conducted in the stability tunnel to determine the effect of an unswept wing on the contribution of unswept-tail configurations to the low-speed-static- and rolling-stability derivatives of a midwing airplane model. The results show that there tend to be only small differences in the tail contributions to the static-lateral-stability derivatives for configurations with the wing on and wing off.
- Effect of aspect ratio on the air forces and moments of harmonically oscillating thin rectangular wings in supersonic potential flow
- Report presenting the effect of aspect ratio on the air forces and moments of an oscillating flat rectangular wing in supersonic potential flow.
- Effect of aspect ratio on the air forces and moments of harmonically oscillating thin rectangular wings in supersonic potential flow
- This report treats the effect of aspect ratio on the air forces and moments of an oscillating flat rectangular wing in supersonic potential flow. The linearized velocity potential for the wing undergoing sinusoidal torsional oscillations simultaneously with sinusoidal vertical translations is derived in the form of a power series in terms of a frequency parameter. The series development is such that the differential equation for the velocity potential is satisfied to the required power of the frequency parameter considered and the linear boundary conditions are satisfied exactly. The method of solution can be utilized for other plan forms, that is, plan forms for which certain steady-state solutions are known.
- The effect of aspect ratio on the subsonic aerodynamic characteristics of wings with NACA 65(sub 1)-210 sections
- Report presenting the results of tests of four model wings of aspect ratios 1, 2, 4, and 6 and with NACA 65(sub 1)-210 sections. The experimental lift-curve slope is compared with predictions from theory. Results regarding lift, drag, and pitching moment, lift-curve slope, drag divergence, minimum drag, and pitching moment are provided.
- Effect of blade-root fit and lubrication on vibration characteristics of ball-root-type axial-flow-compressor blades
- Report presenting the vibration characteristics of several symmetrical ball-root-type blades simulating the mass and natural frequency of axial-flow-compressor blades under various mounting conditions by subjecting them to controlled periodic excitation and centrifugal loading. Results regarding loose single ball-root mounting, loose-lubricated, single ball-root mounting, double ball-root mounting, and damping measurements are provided.
- The Effect of Changes in the Leading-Edge Radius on the Aerodynamic Characteristics of a Symmetrical, 9-Percent-Thick Airfoil at High-Subsonic Mach Numbers
- Report of an investigation into the effect of leading-edge radius on the high-speed aerodynamic characteristics of a symmetrical, 9-percent-thick airfoil using three different airfoils at several Mach and Reynolds numbers. Information about the normal-force coefficients, drag coefficients, moment coefficients about the quarter chord, pressure-distribution diagrams, Schileren photographs, and a comparison with data obtained in other tunnels is included.
- Effect of chemical reactivity of lubricant additives on friction and surface welding at high sliding velocities
- Report presenting an investigation of the effect of chemical reactivity of lubricant additives on friction at high sliding velocities. The investigation was conducted with a kinetic-friction apparatus consisting of an elastically restrained spherical rider specimen sliding on a rotating steel disk lubricated with cetane containing lubricant additives of different chemical reactivities. Results regarding chlorine compounds and sulfur compounds are provided.
- Effect of Compressibility and Camber as Determined From an Investigation of the NACA 4-(3)(08)-03 and 4-(5)(08)-03 Two-Blade Propellers Up to Forward Mach Numbers of 0.925
- Report presenting testing of two NACA two-blade propellers at a range of blade angles and Mach numbers. The effect of compressibility and design section camber are presented for each propeller. The results indicated that if the outboard sections of a propeller are the thinnest, the design of the propellers should incorporate loading distribution that is concentrated in the tip sections.
- Effect of compressor-outlet bleedoff on turbojet-engine performance
- An investigation was conducted in the NACA Lewis altitude wind tunnel to determine the effect of compressor-outlet bleedoff on the performance of an axial-flow turbojet engine equipped with a variable-area exhaust nozzle. Results presented indicate the effect of compressor-outlet bleedoff on performance at altitudes of 25,000 and 40,000 feet and a flight Mach number of 0.53. Variation of performance with bleedoff flow is indicated for operation with fixed- and variable-area exhaust nozzles. Temperature and pressure losses through the bleedoff ducting system are also discussed.
- Effect of dihedral change on the theoretical dynamic lateral response characteristics of a low-aspect-ratio straight-wing supersonic airplane
- Memorandum presenting the results of a theoretical investigation of the lateral response and stability characteristics of the X-3 research airplane (Douglas Model No. 499D). Included are time histories calculated by a computer showing the effect of various disturbances on the lateral response of the airplane with 0 degrees geometric dihedral and -5 degrees dihedral.
- The Effect of End Plates on Swept Wings at Low Speed
- Note presenting an investigation made in the 300 mph 7 - by 10-foot tunnel to determine the effects of various sizes and shapes of end plates on the aileron characteristics and on the aerodynamic characteristics in pitch and yaw of a wing of aspect ratio 2 with no taper and a sweepback of 45 degrees and of a wing of aspect ratio 4, taper ratio 0.6, and sweepback of 46.7 degrees. The addition of end plates to the swept wings increased the lift-curve slope, reduced the maximum lift-drag ratio, generally decreased the maximum lift coefficient, and increased the longitudinal stability slightly in the low lift coefficient range.
- Effect of fuel volatility on altitude starting limits of a turbojet engine
- The effect of fuel volatility on altitude starting limits of an axial-flow-compressor-type turbojet engine was investigated using fuels with Reid vapor pressures of 1.1 and 5.4 pounds per square inch. At flight Mach numbers from 0.40 to 0.85, the AN-F-58 fuel allowed consistent windmilling at altitudes 2000 to 8000 feet higher than was obtained with the 1.1-pound Reid vapor pressure fuel. At a flight Mach number of 0.25, ignition could not be established at any altitude with the lower-volatility fuel.
- Effect of heat and power extraction on turbojet-engine performance 1: analytical method of performance evaluation with compressor-outlet air bleed
- Report presenting an analytical investigation of the performance of a turbojet engine with air bled off at the compressor outlet. A wide range of engine and flight conditions are covered and air bleeds of 0 to 15 percent of the air mass flow are considered. Results are provided in the form of generalized performance charts that are applicable to a wide range of operating conditions.
- Effect of heat and power extraction on turbojet-engine performance 2: effect of compressor-outlet air bleed for specific modes of engine operation
- Report presenting the calculation of the effect of air bleed from the compressor outlet on the performance of turbojet engines with variable-area and rated-area tail-pipe nozzles using generalized performance charts. The effect of altitude, compressor-inlet temperature, and flight Mach number on engine performance with air bleed are provided.
- Effect of heat and power extraction on turbojet-engine performance 3: analytical determination of effects of shaft-power extraction
- Report presenting an analysis of the performance of an axial-flow-type turbojet engine operating with shaft-power extraction by matching experimentally determined component characteristics of a typical axial-flow engine. General working charts are provided to investigate engine performance with variable and rated tail-pipe-nozzle area operation at constant turbine-inlet temperature, engine speed, and thrust.
- Effect of Heat-Capacity Lag on a Variety of Turbine-Nozzle Flow Processes
- Note presenting the computation of the effect of heat-capacity lag in the adiabatic expansion of a gas through a turbine nozzle computed using a one-dimensional analysis of a representative flow process. A number of parameter variations in the flow process are considered to determine the factors that amplify this effect and to show the magnitude of the deviation from equilibrium conditions.
- Effect of Heat-Capacity Lag on the Flow Through Oblique Shock Waves
- Report presenting an analysis of the effects of variable heat capacity on the flow parameters for oblique shock waves at high supersonic speeds at sea level. Two sets of data are provided: one for conditions immediately behind the shock wave at active degrees of freedom and another for asymptotic conditions behind the shock wave where all degrees of freedom are in equilibrium.
- Effect of horizontal tail on low-speed static lateral stability characteristics of a model having 45 degree sweptback wing and tail surfaces
- Report presenting an investigation in the stability tunnel to determine the effects of changes in horizontal-tail size and location on the static lateral stability characteristics of a complete model with wing and tail surfaces having the quarter-chord line swept back 45 degrees. Available procedures for predicting the effect of the horizontal tail on directional stability were found to be unreliable when applied to swept-tail configurations.
- Effect of Humidity on Performance of Turbojet Engines
- Report presenting an experimental and analytical investigation to determine the effect of humidity on turbojet-engine performance. The humidity effect was found to be very small with the magnitude depending on the basis of comparison. Results regarding the calculated humidity correction factors, experimental effect of humidity of engine performance, and variation of saturation specific humidity with altitude are provided.