Technical Report Archive & Image Library (TRAIL) - 140 Matching Results
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- 15 MW Gas-Cooled Closed-Cycle Reactor Power System Study: Final Report, Volumes 1-2
- This report covers a feasibility study for a 15 megawatt gas cooled reactor power system, conducted by the Ford Instrument Company Division of the Sperry Rand Corporation during the months of March to August 1956.
- Acid Formation in the Radiolysis of Phosphorus Esters
- The radiolytic decomposition of tributyl phosphate has been show by burr to product gases, acids, and polymers. the acids that are formed can limit the usefulness of tributyl phosphate for the processing of radioactive materials. The study of acid formation on radiolysis therefor becomes important to us for the understanding of the mechanism of acid formation, the influence of added materials and the effect of the structure of organo- phosphorous compounds. Samples of purified esters have been irradiated in the ORNL cobalt source. Conclusions: (1) The formation of acid from tributyl phosphate during irradiation with cobalt gamma rays involves a mechanism that is not a primary step. Evidence has been obtained for a secondary reaction that is minimized by the presence of certain compounds. (2) Toluene acting as an inhibitor for radiolytic formation of acid may indicate the usefulness of an aromatic hydrocarbon diluent in processing. (3) The aromatic hydrocarbon, when phenyl, was not effective when it was part of the molecule. (4) First tests revealed that dibutyl butyl-phosphonate produced less acid the TBP and may warrant further consideration for process application.
- Altitude performance of pentaborane - JP-4 fuel blends in a modified J47 combustor
- From Introduction: "Experimental investigations of the combustion characteristics of diborane, pentaborane, and pentaborane-hydrocarbon blends in modified turbojet combustors have been conducted at this laboratory at the request of the Bureau of Aeronautics, Department of the Navy, as part of Project Zip. Results of these single-combustor tests are presented in references 2 to 5."
- Analysis of Static Aeroelastic Behavior of Low-Aspect-Ratio Rectangular Wings
- "Slender-body theory is used in conjunction with late theory to analyze the static aeroelastic-divergence behavior of low-aspect-ratio rectangular wings of constant thickness when chordwise deformations are considered. In the analysis, the spanwise variation of the deflection is restricted to a parabola but the chordwise variation is allowed complete freedom. Results show the variation of the divergence speed and mode shape with the aspect ratio" (p. 1).
- Bibliography
- From abstract: This bibliography consists of references pertaining to "Effects of Nuclear Radiation Upon Electronic and Electrical Components", and to "Electronic and Electrical Components for Critical Environments". References were compiled from the Classified and Unclassified report literature and the published literature. The following indexes and abstract journals were used: Weapons Data Index, AEC Card Catalog, Engineering Index (1950-55), and Office of Technical Services, Research Reports (1956-March '57).
- Boundary-Layer-Transition and Heat-Transfer Measurements from Flight Tests of Blunt and Sharp 50 Degree Cones at Mach Numbers from 1.7 to 4.7
- Boundary-layer-transition and heat-transfer measurements were obtained from flight tests of blunt and sharp cones having apex angles of 50 deg. The test Mach number range was from 1.7 to 4.7, corresponding to free-stream Reynolds numbers, based on cone base diameter, of 18. 3 x 10(exp 6) and 32.1 x 10(exp 6), respectively. Transition on both models occurred at a local Reynolds number of 1 x 10(exp 6) to 2 X 10(exp 6) based on distance from the stagnation point. Transition Reynolds numbers based on momentum thickness were between 320 and 380 for the blunt cone. The model surface roughness was 25 rms microinches or greater. Turbulent heat transfer to the conical surface of the blunt cone at a Mach number of 4 was 30 percent less than that to the surface of the sharp cone. Available theories predicted heat-transfer coefficients reasonably well for the fully laminar or turbulent flow conditions.
- Brookhaven National Laboratory Annual Report: 1956
- Report issued by the Brookhaven National Laboratory discussing the work conducted by the lab during the fiscal year of 1956. As stated in the introduction, "the progress and trends of the research program are presented along with a description of the operational, service, and administrative activities of the Laboratory" (p. vii). This report includes tables, illustrations, and photographs.
- Bursting Strength of Unstiffened Pressure Cylinders with Slits
- Note presenting internal-pressure tests made on aluminum-alloy unstiffened cylinders with precut slits to study the effect of slit length and curvature on the hoop stress developed at the bursting pressure. The results are predicted with good accuracy by applying a curvature correction to the method presented in a previous report for computing the strength of flat plates with cracks.
- The Choice in Thorium Oxide Slurries for the Prevention of Caking in Circulating Systems
- A qualitative theory for cake formation in ThO2 slurries is presented. The sphere formation which occurs in "Standard" slurry can be explained on the same basis. The irregular and unpredictable yield strength is easily fitted into the theory. On the basis of this theory, the writer has been led to the conclusion that only colloidally stable slurries, or slurries with crystallites or comminution-resistant particles which are large enough to overcome colloidal effects (probably larger than 0.1u) can be used with assurance in the ThO2 reactor system. This conclusion holds for 300 gm/kg slurries as well as for more concentrated mixtures.
- A collection of data for zero-lift damping in roll of wing-body combinations as determined with rocket-powered models equipped with roll-torque nozzles
- Report presenting the zero-lift damping-in-roll derivative as experimentally determined through high subsonic, transonic, and low supersonic speeds by a torque-nozzle forced-roll technique utilizing rocket-propelled models. Data from the the investigations is used to show the effects of wing plan form and airfoil section and the effects of aeroelasticity. Results regarding sweepback, aspect ratio, taper ratio, thickness ratio, airfoil-section shape, delta wings, increase in number of semispan wings from three to four, aeroelastic effects, and comparisons with theory are provided.
- Compendium of Experimental Results of the Circulation of Aqueous Thorium Oxide Slurries in Toxoids
- Data are presented for all toroid runs which circulated aqueous thorium oxide slurries between Aug, 1054, and October, 1956. In addition, a tabulation of the properties of numerous thoria preparations is presented.
- Component Performance Investigation of J71 Experimental Turbine 9 - Effect of First-Stator Adjustment;Internal Flow Conditions of J71-97 Turbine With 87-Percent-Design Stator Area
- "An experimental radial-survey investigation of the J71-97 three-stage turbine equipped with a first stator having a throat area 87 percent of the design value was conducted at one turbine operating point. The first-, second-, and third-stage mass-averaged efficiencies were 0.897, 0.843, and 0.755, respectively. The corresponding over-all turbine efficiency was 0.856" (p. 1).
- Compressible Laminar Boundary Layer Over a Yawed Infinite Cylinder With Heat Transfer and Arbitrary Prandtl Number
- "The equations are presented for the development of the compressible laminar boundary layer over a yawed infinite cylinder. For compressible flow with a pressure gradient the chordwise and spanwise flows are not independent. Using the Stewartson transformation and a linear viscosity-temperature relation yields a set of three simultaneous ordinary differential equations in a form yielding similar solutions. These equations are solved for stagnation-line flow for surface temperatures from zero to twice the free-stream stagnation temperature and for a wide range of yaw angle and free-stream Mach number" (p. 1017).
- Condition Surveys of Pavements Subjected to Channelized Traffic: Report 1, Davis-Monthan Air Force Base, Tucson, Arizona
- Preface: The purpose of this report is to present the results of a condition survey performed on taxiway 14, Davis-Monthan Air Force Base, in accordance with addendum 6 to Instructions and Outline, "Condition Survey for Existing Pavements."
- Contact of the Burro Canyon Formation with the Dakota Sandstone, Slick Rock District, Colorado, and Correlation of the Burro Canyon Formation
- Report discussing the contact and weathering of the Burro Canyon formation shales and Dakota sandstone as well as other connections of the Burro Canyon formation.
- A Convenient Table for Determining Metastable Transitions in Mass Spectra
- Report issued by the Bureau of Mines on a table developed for determining metastable transitions. The table is presented. This report includes tables, and illustrations.
- Copper Mines and Prospects Adjacent to Landlocked Bay, Prince William Sound, Alaska
- Report issued by the Bureau of Mines over explorations to find prospective copper mines near Valdez, Alaska. The results of the explorations are presented. This report includes tables, maps, and illustrations.
- Critical Mass Measurements on Graphite U²³⁵ Systems
- Abstract: "Measurements have been made on pseudo-cylindrical graphite-enriched uranium unreflected systems. These measurements include both critical mass determinations and time dependent measurements using a pulsed neutron source to drive the assemblies."
- Curve Plotting Routine for the Oracle
- A general program has been written to plot curves on the Oracle curve plotter. A description of the code and complete instructions for preparation of input tapes and operation of the code are given. The code tape is available from the Mathematics Panel or from the author.
- Deflection Equations for Various Loading of Circular-Arc Curved Beams
- In analyzing stresses, deflections, and forces in piping and certain structural systems, it is useful to have a set of equations giving the deflections at any point of a curved beam in terms of the various loads acting on the beam. This technical report presents the deflection equations for a curved circular-arc beam of variable length. The cases treated include in-plane and out-of-plane bending due to forces and moments applied to the end of the beam in three principal directions, and uniformly distributed loads applied along the beam in these three directions. Deflections were calculated by the strain energy method using Castigliano's theorem.
- Die Design for Hot Presses ; [Bibliography]
- Abstract: "This is a selective bibliography of books and periodical articles relating to die design of hot presses. Sources consulted include: ASM Review of Metal Literature, 1950-1954; Chemical Abstracts, 1950-1055; Engineering Index, 1950-1055; Industrial Arts Index, 1950-March 1957; Metallurgical Abstracts, 1950-1953; Nuclear Science Abstracts, 1950-March 1957; Physics Abstracts, 1950-1955; the library card catalog, and the Technical Information Division AEC card catalog."
- Dielectric Constant and Electrical Resistivity of Natural-State Cores
- The following report covers measurements of electrical resistivity and dielectric constant that were made on parts of 27 cores from the Morrison formation in the Colorado Plateau uranium province as part of a program to obtain basic data on the physical properties of the rock in and near uranium-mineralized zones.
- Dynamic Longitudinal Stability Characteristics of a Swept-Wing Fighter-Type Airplane at Mach Numbers Between 0.36 and 1.45
- Memorandum presenting an investigation of a swept-wing fighter-type airplane not equipped with an automatic pitch damper that made pulse maneuvers at altitudes from 10,000 to 40,000 feet over a Mach number range from 0.36 to 1.45 to determine the longitudinal stability characteristics and derivatives for an original-wing and an extended wing-tip configuration. Results regarding the original wing, extended wing, and influence of wing-tip extensions are provided.
- Effect of an Interface on Transient Temperature Distribution in Composite Aircraft Joints
- Note presenting testing of geometrically related structural joints representing typical skin-stringer cross sections under radiant heating to simulate the effects of aerodynamic heating. The presence of an interface was found to have a significant effect on the temperature distribution in all geometries tested and thus must be considered in temperature calculations. Interface conductance values were computed for each of the 15 fabricated specimens.
- Effect of fuselage length and a canopy on the static longitudinal and lateral stability characteristics of 45 degrees sweptback airplane models having fuselages with square cross sections
- Report presenting a wind-tunnel investigation at low speed to determine the effects of fuselage nose length and a canopy on the static longitudinal and lateral stability characteristics of a complete model with a fuselage with square cross sections, a 45 degree sweptback wing, and a 45 degree sweptback horizontal tail.
- The Effect of Solid Admixtures on the Velocity of Motion of a Free Dusty Air Jet
- "In dusty air flows occurring in industrial practice in transport by air pressure of friable materials, in the drying, annealing, and so forth, of a pulverized solid mass in suspension, and in other processes, the concentration of solid particles usually has a magnitude of the order of 1 kg per 1 kg of air. At such a concentration, the ratio of the volume of the particles to the volume of the air is small (less than one-thousandth part). However, regardless of this, the presence of a solid admixture manifests itself in the rules for the velocity distribution of the air in a dusty air flow" (p. 1).
- Effect of spanwise variations in gust intensity on the lift due to atmospheric turbulence
- The effect of spanwise variations in gust intensity on the power spectrum directly due to atmospheric turbulence is calculated for several analytic approximations to the correlation function or power spectra of atmospheric turbulence, for several spanwise weighing functions (span loadings), and for various angles of sweepback.
- Effects of Inlet Modification and Rocket-Rack Extension on the Longitudinal Trim and Low-Lift Drag of the Douglas F5D-1 Airplane as Obtained with a 0.125-Scale Rocket-Boosted Model Between Mach Numbers of 0.81 and 1.64: TED No. NACA AD 399
- From Summary: "A flight investigation was conducted to determine the effects of inlet modification and rocket-rack extension on the longitudinal trim and low-lift drag of the Douglas F5D-1 airplane. The investigation was conducted with a 0.125-scale rocket-boosted model between Mach Numbers of 0.81 and 1.64. This paper presents the changes in trim angle of attack, trim lift coefficient, and low-lift drag caused by the modified inlets alone over a small part of the test Mach number range and by a combination of the modified inlets and extended rocket racks throughout the remainder of the test."
- Evaluation of Several Ram-Jet Combustor Configurations Using Pentaborane Fuel
- Report presenting an investigation of several combustor configurations to determine if the length of the engine could be reduced. Testing indicated that when using a highly reactive fuel in the low subsonic region of the diffuser, part of the engine length can be eliminated.
- Expected numbers of maxima and minima of a stationary random process with non-Gaussian frequency distribution
- Report presenting a method for calculating the expected number of maxima or minima of a random process with non-Gaussian frequency distribution from the statistical moments of the process and its first two derivatives. The effects of skewness and kurtosis can also be calculated provided the required moments are known.
- Experimental Determination at Subsonic Speeds of the Oscillatory and Static Lateral Stability Derivatives of a Series of Delta Wings With Leading-Edge Sweep From 30 to 86.5 Degrees
- Memorandum presenting a determination of the static lateral stability of six delta wings at subsonic speeds. In addition, two of the wings with 82.5 degree and 75 degree sweep of the leading edge were oscillated in yaw about the 50-percent point of the root chord in order to determine the effects of frequency and amplitude on the combination lateral stability derivatives resulting from the motion. Results regarding the static characteristics and oscillatory characteristics are provided.
- An Experimental Hydrodynamic Investigation of the Inception of Vortex Ventilation
- Results are presented from a hydrodynamic investigation of the inception of vortex ventilation on modified-flat-plate rectangular lifting surfaces of aspect ratio 0.25 differing in scale and thickness ratio. Two types of bubble-formation processes are described. Inception speeds were correlated for bubble formation in the high angle-of-attack range by using the Froude number and for that in the low angle-of-attack range by expressing the speed as a function of the thickness ratio.
- Experimental investigation of performance of single-stage transonic compressor with guide vanes turning counter to direction of rotor whirl
- Report presenting testing of a transonic compressor rotor with double-circular-arc blade sections and inlet guide vanes turning counter to the direction of rotor whirl to determine the effect of blade-row interaction on the performance of a transonic rotor. Results regarding overall performance, guide-vane performance, rotor-inlet conditions, rotor-outlet conditions, consideration of radial equilibrium, blade-element performance, and axial asymmetry in rotor-outlet flow are provided.
- Experimental Investigation of Vibratory Stresses in a Concentric-Ring Direct-Air-Cycle Nuclear Fuel Element
- "Preliminary tests made by the General Electric Company indicated that aerodynamic loads might cause large enough distortions in the thin sheet-metal rings of a nuclear fuel element to result in structural failure. The magnitude of the distortions in a test fuel element was determined from strains measured with airflow conditions simulating those expected during engine operation. The measured vibratory strains were low enough to indicate the improbability of failure by fatigue. A conservative estimate of the radial deflection that accompanied peak strains in the outer ring was +0.0006 inch" (p. 1).
- Experimental Performance of a 5000-Pound-Thrust Rocket Chamber Using a 20-Percent-Fluorine - 80-Percent-Oxygen Mixture With RP-1
- Memorandum presenting an evaluation of the performance increase resulting from the addition of 20 percent fluorine to the oxygen-RP-1 propellant combination in a 5000-pound-thrust rocket engine at a chamber pressure of 650 pounds per square inch absolute. Runs were made with the engine water cooled and regeneratively cooled.
- Experimental performance of a 5000-pound-thrust rocket chamber using a 20-percent-fluorine-80-percent-oxygen mixture with RP-1
- An investigation of the performance increase resulting from the addition of 20 percent fluorine to the oxygen-RP-1 propellant combination in a 5000-pound-thrust rocket engine at a chamber pressure of 650 pounds per square inch absolute.
- An Experimental Study at High Subsonic Speeds of Several Tail Configurations on a Model Having a 45 Degree Sweptback Wing
- Memorandum presenting an investigation conducted in the 7- by 10-foot tunnel of the static longitudinal and lateral stability characteristics of a model with a 45 degree sweptback wing of aspect ratio 4 and with several different tail arrangements. The tail configurations studied had unswept, rectangular surfaces and included a T-tail and conventional fuselage-mounted horizontal and vertical tails. Results regarding wing-fuselage characteristics, effects of afterbody shape, effect of tail configuration on stability, and comparison of swept- and unswept-wing configurations are provided.
- Experimentally determined natural vibration modes of some cantilever-wing flutter models by using an acceleration method
- From Summary: "Three-dimensional views are presented of the first three natural vibration mode shapes of ten cantilever-wing models. A table of normalized deflections at six spanwise and five chordwise stations is included for each mode. These mode shapes were measured by a rather unique experimental technique using grains of sand as accelerometers."
- Exploratory study of ground proximity effects on thrust of annular and circular nozzles
- The proximity of the ground to an annular nozzle can result in thrust augmentation of up to 50 percent. The magnitude of thrust augmentation was a function of ground-to-nozzle distance, nozzle configuration, and nozzle pressure ratio. With a conventional circular nozzle a thrust reduction of 15 to 40 percent due to ground effect was obtained. The degree of thrust reduction was primarily a function of nozzle pressure ratio and ground-to-nozzle distance.
- Extrusion Die Design : [bibliography]
- "This is a selective bibliography of books and periodical articles relating to extrusion die design with special emphasis on extrusion of beryllium. Material on the extrusion process has been included when it contains information that might be of possible help in die designing."
- Feasibility Investigation of a Closed Cycle Boiling Water Reactor for the Propulsion of a Merchant Ship
- Summary: The scope and intent of this report is to demonstrate the feasibility of a nuclear powered tanker for service in the United States Maritime Fleet.
- A flight investigation of area-suction and blowing boundary-layer control on the trailing-edge flaps of a 35 degree swept-wing-carrier-type airplane
- Report presenting flight tests on an FJ-3 airplane to determine the flight characteristics of a carrier-type airplane with area-suction and blowing boundary-layer control on the trailing-edge flaps. Measurements were made of lift, drag, and bleed-air requirements for the different types of boundary-layer control systems. Results regarding lift, drag, flow requirements, performance, pilots' opinions, and approach-speed criteria are provided.
- Flight investigation of pentaborane fuel in 9.75-inch-diameter ram-jet engine with downstream fuel injection
- Report presenting a flight test of pentaborane fuel in an air-launched ramjet engine with a design free-stream Mach number of 1.8. The ramjet used in the investigation had a revised spray bar-flameholder configuration. Results regarding propulsive thrust and propulsive-thrust specific fuel consumption are provided.
- Flight Investigation of Pentaborane Fuel in 9.75-inch-diameter Ram-jet Engine With Downstream Fuel Injection
- Flight investigation of pentaborane fuel in 9.75- inch-diameter ramjet engine with downstream fuel injection.
- Free-Flight Skin Temperature and Pressure Measurements on a Slightly Blunted 25 Deg Cone-Cylinder-Flare Configuration to a Mach Number of 9.89
- "Skin temperatures and surface pressures have been measured on a slightly blunted cone-cylinder-flare configuration to a maximum Mach number of 9.89 with a rocket-propelled model. The cone had a total angle of 25 deg and the flare had a 10 deg half-angle. Temperature data were obtained at eight cone locations, four cylinder locations, and seven flare locations; pressures were measured at one cone location, one cylinder location, and three flare locations" (p. 1).
- Free-Spinning-Tunnel Investigation of a 1/25-Scale Model of the McDonnell F3H-2N Airplane
- Memorandum presenting an investigation in the 20-foot free-spinning tunnel on a 1/25-scale model of the McDonnell F3H-2N airplane. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model were determined for the clean condition. Results regarding erect spins, engine gyroscopic moments, inverted spins, spin-recovery parachute, and landing condition tests are provided.
- Full-Scale Free-Jet Investigation of a Two-Shock Side-Inlet Diffuser at Mach 2.75 and a Comparison With a Single-Shock Diffuser
- Memorandum presenting a full-scale free-jet investigation of a two-shock side-inlet diffuser at Mach umber 2.75 in an altitude test chamber. Data were obtained over ranges of free-stream total pressure and temperature. Results regarding diffuser mass-flow ratio, critical pressure recovery, diffuser static-pressure variation, and diffuser-outlet flow conditions are provided.
- Full-Scale Investigation of Several Jet-Engine Noise-Reduction Nozzles
- A number of nozzles which use the mixing interference of adjacent jets for noise suppression were investigated. Reductions in sound power of nearly 70 percent (5 db) with thrust losses of 1 percent were achieved. A method of calculating the limiting frequency affected by this type of suppression nozzle, that is , multiple-slot nozzles, is presented. Data are shown which indicate that further large reductions in sound power are not likely with mixing-interference nozzles.
- Further Experiments on the Stability of Laminar and Turbulent Hydrogen-Air Flames at Reduced Pressures
- "Stability limits for laminar and turbulent hydrogen-air burner flames were measured as a function of pressure, burner diameter, and composition. On the basis of a simple flame model, turbulent flashback involved a smaller effective penetration distance than laminar flashback. No current theoretical treatment predicts the observed pressure and diameter dependence of laminar and turbulent blowoff" (p. 1).
- Ground Simulator Studies of the Effects of Valve Friction, Stick Friction, Flexibility, and Backlash on Power Control System Quality
- Note presenting tests on a power control system by means of a ground simulator to determine the effects of various combinations of valve friction and stick friction on the ability of the pilot to control the system. The results show that, when valve friction was present in a rigid system, the introduction of stick friction was beneficial in that it restored some of the quality lost because of the valve friction. Results regarding the rigid control system, flexible control system, and control system with backlash are provided.