Technical Report Archive & Image Library (TRAIL) - 1,335 Matching Results
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- Coal Geology of the White Oak Quadrangle, Magoffin and Morgan Counties, Kentucky
- From abstract: The White Oak quadrangle lies near the western edge of the eastern Kentucky coalfield and includes approximately 59 square miles of parts of Magoffin and Morgan Counties, Ky. The outcropping rocks are equivalent to most of the Breathitt formation of Pennsylvanian age. The regional southeast dip of the rocks is interrupted by the Irvine-Paint Creek fault, the Caney anticline, the Grape Creek syncline, and the Johnson Creek fault.
- A Coated Cast Iron Crucible for use with Eutectic Al-Si Alloy in the Temperature Range 595°-650°C
- The feasibility of the coated metal crucible as a container for eutectic Al-Si alloy has been proven by test. Small, enamel-coated cast iron pots has been proven by test. Small, enamel-coated cast iron pots have successfully withstood the chemically aggressive Al-Si alloy and the adverse influence of an oxidizing atmosphere for a period of 3 months at 725°C. A similarly coated castiron crucible containing 450 pounds of eutectic Al-Si alloy was successfully tested for 144 days in a jacketing operation conducted at 595°-650°C. Under the same conditions, the normal service life of clay-bonded graphite and silicon carbide crucibles rarely exceeds 45 days. The coating material is a commercially available enamel capable of withstanding temperatures up to 790°C (1450°F). It is readily applied to the surface of a variety of ferrous metals and alloys; however, best results are obtained with alloys low in chromium and nickel which also have a low thermal expansion coefficient.
- 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.
- Collection of zero-lift drag data on bodies of revolution from free-flight investigations
- Report presenting a compilation of most of the zero-lift drag obtained from free-flight measurements on fin-stabilized bodies of revolution. Results regarding friction drag, base pressure and base drag, pressures on a forward facing step, and fin pressure drag are provided.
- The combinations of thermal and load stresses for the onset of permanent buckling in plates
- A simple and practical method for evaluating the onset of permanent buckling in plates in the presence of combined thermal and compressive load stresses is outlined. A particular application of the method shows reasonable agreement with tests of 17-7 PH stainless-steel square tubes. The results indicate that the compressive load stress which the plate can support at the onset of permanent buckling is substantially reduced as the temperature difference of the plate and adjoining members increases.
- Combustion of Solid Fuels in Thin Beds
- From Introduction: "The investigations described in this report are a continuation and extension of these commercial and pilot-scale tests to include an investigation of the ignition and burning of solid fuels in thin beds, as on traveling - or chain grate stokers and a study of pure crossfeed combustion."
- Combustor performance of a 16-inch ram jet using gaseous hydrogen as fuel at Mach number 3.0
- An investigation was conducted in the NACA Lewis 10- by 10-foot supersonic wind tunnel to evaluate the performance of three burner configurations in a 16-inch ram jet with gaseous hydrogen as fuel. Data were obtained over a fuel-air-ratio range from 0.0030 to 0.0260 (stoichiometric = 0.0292) at a free-stream Mach number of 3.0 and 0 degree angle of attack. The exit nozzle-throat area ratios employed were 0.60 and 0.75.
- Comments on the Determination of the Particle Size Distribution of Thorium Oxide
- Factors affecting the results of thoria particle size distribution measurements by sedimentation procedures currently and recently employed are considered. The effects of thoria concentration, solvent, dispersant, thoria properties, and other factors are discussed.
- Comments on the Transportation of Irradiated Fuel and Radioactive Wastes for M Louis Armand, Euratom Group
- General considerations involving the transportation of irradiated fuel and radioactive wastes are reviewed. It is assumed that many reactors will supply feed to a few large multipurpose chemical plants which ultimately send radioactive waste to a few disposal sites. General economic considerations of irradiated fuel reprocessing, economic aspects of the nuclear economy complex, growth predictions of the nuclear power economy in the U.S., general requirements for the shipment of fuel and waste, regulations applicable to fuel shipment, and permissible radiation levels are discussed.
- Comparative Study of Turbofan and Turbojet Engines
- Report presents a comparison of turbofan and turbojet engines for Mach numbers of up to 3.0 and conventional hydrocarbon fuels. There are four parts of the report: a cycle analysis of turbofan engines and information about their designs, a comparison of several commercial engines proposed for the Air Force, component performance and development problems for turbofan and turbojet engines, and a summary and conclusions based on mission studies.
- Comparison and Evaluation of Two Model Techniques Used in Predicting Bomb-Release Motions
- "For the purpose of calculating bomb trajectories, forces and moments have been measured on bombs of three fineness ratios in the presence of a swept-wing fighter-bomber configuration at a Mach number of 1.61. Trajectories thus obtained have been compared with those from dynamic model tests and an analysis has been made to determine the source of errors and to suggest improvements in both techniques."
- Comparison and Evaluation of Two Model Techniques Used in Predicting Bomb-Release Motions
- "For the purpose of calculating bomb trajectories, forces and moments have been measured on bombs of three fineness ratio sin the presence of a swept-wing fighter bomber configuration at a Mach number of 1.61. Trajectories thus obtained have been compared with those from dynamic model tests and an analysis has been made to determine the source of errors and to suggest improvements in both techniques." (p. 1).
- Comparison of calculated and experimental load distributions on thin wings at high subsonic and sonic speeds
- A method for calculating the aerodynamic loading on a wing in combination with a body is presented. Calculated results are compared with experimentally measured data for two wing-body configurations throughout a range of Mach number up to 1.0. The magnitude and the distribution of spanwise loading of the calculated data are generally in good agreement with the experimental data.
- A comparison of carrier approach speeds as determined from flight tests and from pilot-operated simulator studies
- Report presenting a simplified analog simulator that can be used to predict the minimum comfortable approach speeds that could be used in carrier landings for airplanes that are limited by their ability to control altitude. Predicted speeds from initial tests on several planes are compared with values from flight tests in order to indicate the validity of simulator results.
- Comparison of Combustion Reactivity of Ethyldecaborane Fuels With Typical Hydrocarbon Fuels on Basis of Spray Flammability Limits of Fuel-Rich Mists and Calculated Lean-Limit Flame Temperatures for Fuel Vapor-Air Systems
- From Summary: "The spray flammability limits of various high-energy fuels and hydrocarbon fuels were determined experimentally in an apparatus which measured the minimum percent of oxygen by volume that would permit the ignition of a particular fuel. The fluids investigated were ethyldecaboranes, aliphatic hydrocarbons, olefins, aromatic hydrocarbons, and esters."
- Comparison of effect of a turbojet engine and three cold-flow configurations on the stability of a full-scale supersonicle inlet
- Increasing the volume and length of the duct behind the inlet affected the inlet stability at Mach 2.0 and zero angle of attack. Close approximation of the inlet stability limit of the J34 engine-inlet configuration was obtained by a cold-pipe configuration having a length and volume approaching that measured to the engine turbine. Variation of these parameters had a small effect on the minimum subcritical stable mass flow below a cowl-lip-position parameter of 44 degrees and appeared to have a negligible effect on the inlet pressure-recovery - mass-flow curve. Initial buzz frequency and minimum cowl-lip-position parameter for complete buzz-free operation varied with configuration.
- Comparison of Experimental and Theoretical Zero-Lift Wave-Drag Results for Various Wing-Body-Tail Combinations at Mach Numbers Up to 1.9
- "Comparisons are made of experimental and theoretical zero-lift wave drag for several nose shapes, wing-body combinations, and models of current airplanes at Mach numbers up to 1.0. The experimental data were obtained from tests in the Ames 6- by 6-foot supersonic wind tunnel and at the NACA Wallops Island facility. The theoretical drag was found by use of linear theory utilizing model area distributions" (p. 1).
- Comparison of experimental with theoretical total-pressure loss in parallel-walled turbojet combustors
- "An experimental investigation of combustor total-pressure loss was undertaken to confirm previous theoretical analyses of effects of geometric and flow variables and of heat addition. The results indicate that a reasonable estimate of cold-flow total-pressure-loss coefficient may be obtained from the theoretical analyses. Calculated total-pressure loss due to heat addition agreed with experimental data only when there was no flame ejection from the liner at the upstream air-entry holes" (p. 1).
- Comparison of low-lift drag at Mach numbers from 0.74 to 1.37 of rocket-boosted models having externally braced wings and cantilever wings
- Report presenting an investigation to determine whether the low-lift drag of a rocket-model airplane-like configuration could be reduced at transonic and low supersonic Mach numbers by reducing wing thickness while external braces were used to provide the necessary bending strength. The investigation was conducted with two rocket models of aspect ratio 3.04, and unswept braced tapered wings mounted on fuselages with the same fineness ratios and cross-sectional area distributions. Data was compared to a previous study involving a model with a thicker cantilever wing.
- Comparison of Mechanical Properties of Flat Sheets, Molded Shapes, and Postformed Shapes of Cotton-Fabric Phenolic Laminates
- Report presenting testing to determine the properties of several untreated commercial cotton-fabric pheonlic sheet laminates, the same sheets after exposure to a postforming heating cycle, industrially postformed shapes made from those materials, industrially molded and laboratory-molded shapes, and flat panels postformed in the laboratory from the laboratory-molded shapes. Results regarding tensile properties, flexural properties, and water absorption are provided.
- Comparison of NACA 65-series compressor-blade pressure distributions and performance in a rotor and in cascade
- An investigation has been conducted to compare the performance of NACA 65-series compressor blades in two-dimensional cascade with that in an axial flow compressor. Blade pressure distributions were obtained by the use of a mercury-seal pressure-transfer device. The comparison indicated that cascade data accurately predicted the turning angle and blade pressure distribution obtained in the compressor at design conditions.
- A Comparison of Plants and Soils as Prospecting Guides for Uranium in Fall River County, South Dakota
- A report about a comparison of the uranium content of plants and soils as prospecting guides for uranium made for areas of known mineralization in Fall River County, South Dakota.
- Comparison of the Combustion Performance of Shell UMF, Grade C, MIL-F-5624C, Grade JP-5, Fuels in a Heavy-Duty XRJ47-W-9 Ram-Jet Engine
- Comparable combustion performance data for Shell UMF, grade C, and MIL-F-5624C, grade JP-5, fuels were obtained using a heavy-duty version of the XRJ47-W-9 ram-jet engine operated in a 2.75 Mach number free-jet facility. Data were obtained for the two fuels over a range of fuel-air ratios, engine airflows, and engine-inlet temperatures. The test conditions were selected to provide combustor-inlet temperatures. The test conditions were selected to provide combustor-inlet conditions approximately representative of those which would be encountered over a range of altitudes and flight Mach numbers. The variation of combustion efficiency with fuel-air ratio for the two fuels is compared at the several inlet conditions. The pilot-burner ignition and operating limits with both fuels are also included. In general, the combustion efficiency with Shell UMF, grade C, fuel was 1 to 4 points lower than with MIL-F-5624C, grade JP-5, fuel.
- A comparison of typical National Gas Turbine Establishment and NACA axial-flow compressor blade sections in cascade at low speed
- Report presenting comparative low-speed cascade tests of the National Gas Turbine Establishment of Great Britain axial-flow compressor blade sections at a range of air-inlet angles and a solidity of 1.0 using the porous wall technique. Results regarding a comparison of performance characteristics of the NGTE and NACA axial-flow compressor blade sections and a comparison of NGTE and NACA low-speed cascade tests of the NGTE 10C4/30C50 section are provided.
- Compatibility Tests of Various Materials in Molten Sodium
- Several compatibility test of various materials in contact in sodium under 500 psi pressure were conducted for 716 hr at 1500 F. Of the diffusion couples studies, the Inconel-beryllium system showed the largest amount al alloying. The reaction between molybdenum and beryllium resulted in the formation of two compounds, both of which were severely cracked in several areas. The molybdenum-INOR #8, and the INOR #8p type 316 stainless steel interfaces showed little if any alloying.
- 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 7: effect of first-stator adjustment; over-all performance of J71 turbine with 87-percent-design stator area
- The performance results, as well as a compressor-turbine match point study based on a particular mode of engine operation, are compared with those previously obtained with the same turbine having first-stator areas 70, 95.6, and 132 percent of design. Maximum efficiencies for all turbine configurations were high, on the order of 87 to 89 percent. The efficiencies obtained at the match points for the 87-, 95.6-, and 132-percent turbines were slightly lower. No match point for the 70-percent turbine was obtained because, with first-stator areas less than 75.5 percent of design, the turbine would develop insufficient work to drive the compressor at the match point.
- Component performance investigation of J71 experimental turbine 8: effect of first-stator adjustment; internal flow conditions of J71-97 turbine with 70-percent-design stator area
- Results of a survey investigation of the J71-97 experimental three-stage turbine equipped with a first-stator area 70 percent pf design are presented and compared with the turbine with a first-stator area 97 percent of design.
- 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).
- Compressibility Effects on a Hovering Helicopter Rotor Having an NACA 0018 Root Airfoil Tapering to an NACA 0012 Tip Airfoil
- Report presenting an investigation to determine the effects of compressibility on the hovering performance and the blade pitching moments of a helicopter rotor with a tip airfoil, a root airfoil, and twist. Results regarding hovering performance, rotor-blade pitching moments, rotor profile-drag torque, and a comparison with two-dimensional drag-divergence data are provided.
- Compressible Laminar Boundary Layer Over a Yawed Infinite Cylinder With Heat Transfer and Arbitrary Prandtl Number
- Note presenting the equations for development of the compressible laminar boundary layer over a yawed infinite cylinder. The results indicate that the effect of yaw on the heat-transfer coefficient at the stagnation line depends markedly on the free-stream Mach number.
- 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).
- Compressive Stress-Strain Properties of 17-7 PH and AM 350 Stainless-Steel Sheet at Elevated Temperatures
- 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.
- Conceptual Design of an Advanced Engineering Test Reactor
- From abstract: This report describes a conceptual design for an Advanced Engineering Test Reactor. The reactor is a large graphite assembly penetrated by parallel Zircaloy tubes through which flow as heavy water solution of uranyl sulfate. Reactor power is 220 megawatts.
- Concluding Report of Free-Spinning, Tumbling, and Recovery Characteristics of a 1/18-Scale Model of the Ryan X-13 Airplane, Coord. No. AF-199
- "An investigation has been completed in the Langley 20-foot free-spinning tunnel on a l/18-scale model of the Ryan X-13 airplane to determine its spin, recovery, and tumbling characteristics, and to determine the minimum altitude from which a belly landing could be made in case of power failure in hovering flight. Model spin tests were conducted with and without simulated engine rotation. Tests without simulated engine rotation indicated two types of spins: one, a slightly oscillatory flat spin; and the other, a violently oscillatory spin" (p. 1).
- 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.
- Control System for HRT Cooling Water
- The circuits described herein and shown functionally in Fig. 1 are to be added to the HRT control circuit to provide control and protection for the revised HRT cooling water system. The circuitry will provide protection against excess pressure in the demineralized cooling water loop and cooling water activity, will initiate action to insure containment of activity in event of an explosion and will provide emergency cooling water from the tower basin when required.
- 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.
- Cooling performance and structural reliability of a modified corrugated-insert air-cooled turbine blade with an integrally cast shell and base
- A modified corrugated-insert blade with integrally cast shell and base was developed. This blade was as light as a conventional fabricated corrugated-insert blade. Of four test blades operated in a full-scale turbojet engine, one failed after about 15 hours operation at an inlet gas temperature of 1670 degrees F, a coolant-flow ratio of 0.0064, and a 1/3-span centrifugal stress of approximately 28,000 psi. Three other test blades ran for approximately 16, 31, and 36 hours without failure at similar conditions.
- 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.
- A correlation of low-speed, airfoil-section stalling characteristics with Reynolds number and airfoil geometry
- From Summary: "The low-speed stalling characteristics of a large number of airfoil sections have been correlated with Reynolds number and a single airfoil ordinate near the leading edge as the correlation parameters. The correlation is appropriate only to airfoils without high-lift devices in flows of very low turbulence and with aerodynamically smooth surfaces."
- A Correlation of Results of a Flight Investigation With Results of an Analytical Study of Effects of Wing Flexibility on Wing Strains Due to Gusts
- Report presenting a study of the effects of wing flexibility on wing strains due to gusts for four spanwise stations of a four-engine bomber airplane and a correlation with previous testing results. Results regarding the power spectre, peak counts, amplification factors, statistical reliability, input disturbance, frequency-response functions, output response, and amplification factors are provided.
- Corrosion of 2-S Aluminum in Potassium Tetraborate Solution
- From summary: "A laboratory test was conducted to determine the feasibility of using an uninhibited solution of potassium tetraborate in steam condensate as a material for a pile ink facility. The evaluation was made from the standpoints of 2-5 aluminum corrosion, the rate and composition of film build-up on aluminum flow surfaces, and the change of solution composition."
- Corrosion Studies
- The following report focuses on the first run in a series of corrosion reports testing a solution of .5 M UO3 in 85% H3PO4.
- Cracks in HRT Flange Bolts and Ferrules
- When it was discovered that two HRT flange bolts of a lot of 16 spares contained serious cracks, a program was launched to (1) determine the cause for the cracking, and (2) find methods for non-destructive testing the remainder of the 672 bolts shipment, a large portion of which had been installed in the HRT. Concurrently, inspection of 8 ferrules removed from an HRT flange revealed hairline cracking in 4 of them. Magnaglo, a magnetic particle inspection method using a fluorescent dye, proved to be the only definitive method for inspecting the bolts. The evidence gathered on the bolts pointed to quench cracking as the cause for the defects. Nothing abnormal was disclosed in regard to the bolt material. The alloy and heat treatment at present prescribed for the HRT bolts and ferrules are considered suitable. However, recommendations are made for plating with zinc, instead of formerly prescribed cadmium, to a thickness of 0.0002 inch, followed by a hydrogen relief treatment and a final bichromate chemical dip.
- Creep Behavior of Structural Joints of Aircraft Materials Under Constant Loads and Temperatures
- "The results of 55 creep and creep-rupture tests on structural joints are presented. Methods are described by which the time to rupture, the mode of rupture, and the deformation of joints in creep may be predicted. These methods utilize creep data on the materials of the joint in tension, bearing, and shear" (p. 1).
- Creep Deformation Patterns of Joints Under Bearing and Tensile Loads
- Note presenting an investigation to study the interaction of bearing and tensile loads on the creep behavior of joints. A simplified model was employed which contained many of the features found in riveted connections. Results regarding creep-rupture tests, plate subjected to tension, plate subjected to bearing loads, plate subjected to tensile and bearing loads, and index of joint behavior are provided.
- Critical-Assembly Studies on an Intermediate Reactor for Aircraft Propulsion
- The following report studies an intermediate solid-fuel reactor system for aircraft propulsion.
- 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."