Technical Report Archive & Image Library (TRAIL) - 105 Matching Results
Search Results
- Aerodynamic Characteristics of Missile Configurations With Wings of Low Aspect Ratio for Various Combinations of Forebodies, Afterbodies, and Nose Shapes for Combined Angles of Attack and Sideslip at a Mach Number of 2.01
- "An investigation has been made in the Langley 4-by-4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a series of missile configurations having low-aspect-ratio wings at a Mach number of 2.01. The effects of wing plan form and size, length-diameter ratio, forebody and afterbody length, boattailed and flared afterbodies, and component force and moment data are presented for combined angles of attack and sideslip to about 28 degrees. No analysis of the data was made in this report" (p. 1).
- Aerodynamic Heating and Boundary-Layer Transition on a 1/10-Power Nose Shape in Free Flight at Mach Numbers Up to 6.7 and Free-Stream Reynolds Numbers Up To 16 x 10(Exp 6)
- Report presenting testing of a modified 1/10-power nose shape in free flight at Mach numbers up to 6.7. Measured heating rates were presented and compared with calculated values. Results regarding transition and comparison with previous investigations are provided.
- Aerodynamics of Oscillating Control Surfaces at Transonic Speeds
- Memorandum presenting a discussion of oscillating flap-type and all-movable controls with particular emphasis on the aerodynamic forces and moments at transonic speeds. Hinge-moment results from recent wind-tunnel and rocket-powered-model tests are summarized for trailing-edge flap-type controls to illustrate the effects of control hinge-line position and profile shape on one-degree-of-freedom flutter of this type of control.
- Airborne Radiometric Reconnaissance in the Wind River Basin, Wyoming
- Abstract: A program of airborne radiometric reconnaissance for uranium was conducted in eastern Fremont and western Natrona Counties, in central Wyoming, during the summer and fall of 1954, by the U.S. Atomic Energy Commission.
- Altitude Starting Tests of a Small Solid Propellant Rocket
- From Summary: "Four solid-propellant rocket engines of nominal 500-pound thrust were tested for starting characteristics at pressure altitudes ranging from 89,000 to 111,000 feet and at a temperature of -75^o F. Chamber pressures were measured on two of the runs. Average chamber pressures in these two runs were lower than expected, although action times agreed with the expected values."
- Analyses for Turbojet Thrust Augmentation With Fuel-Rich Afterburning of Hydrogen, Diborane, and Hydrazine
- Turbojet thrust augmentation with fuel-rich afterburning of hydrogen, diborane, and hydrazine was computed. Results regarding takeoff thrust augmentation and flight thrust augmentation are provided.
- Analyses for turbojet thrust augmentation with fuel-rich afterburning of hydrogen, diborane, and hydrazine
- From Introduction: "This report presents net thrusts computed for hydrogen, diborance, and hydrazine with fuel-air ratios form stoichiometric values to 0.5. Net thrusts for fuel-rich afterburning are compared with those for stoichiometric combustion of the turbojet fuel and air augmented with a 220-second specific-impulse rocket."
- Analysis of Meteorological Tower Data, April 1950 - March 1952, Brookhaven National Laboratory
- Report issued by the Brookhaven National Laboratory discussing data collected from two BNL meteorological towers. As stated in the introduction, "results are presented in graphic form rather than tabular form" (p. 1). This report includes tables, maps, illustrations, and photographs.
- Analysis of two-spool turboprop-engine characteristics
- From Introduction: "The purpose of this report is to present the results of an analytical investigation of the engine characteristics of two-spool engines with high over-all compressor pressure ratio (12.0 at design). Some of the turbine design problems encountered in a single-spool engine with current compressor pressure ratio (7.32 at design) were investigated in reference 1. The investigation was extended in reference 2 to cover the effect of mode of engine operation on the turbine design requirements and engine performance for a single-spool engine with current compressor pressure ratio."
- Analytical Investigation of Fuel-Cooled Turbine Blades With Return-Flow Type of Finned Coolant Passages
- Memorandum presenting an investigation of coolant-flow rates for a turbine rotor blade with return-flow type of coolant-passage configuration formed by fins within a capped blade shell with both hydrogen and methane fuels as coolants. Results regarding spanwise blade and coolant temperature distributions, effects of coolant inlet temperature on hydrogen-coolant-flow requirements, comparison of return-flow-blade coolant requirements, effect of fin thickness and fin height, comparison of hydrogen and methane as coolants, and feasibility of fuel-cooled turbines are provided.
- Analytical investigation of fuel-cooled turbine blades with return-flow type of finned coolant passages
- From Introduction: "The purpose of this report was to investigate the possible use of engine fuels (hydrogen and methane) as coolants for turbine rotor blades and to determine the pressure-drop characteristics of these coolants for a turbine blade with a more effective coolant-passage configuration than that considered in reference 5 but for the same engine and flight conditions."
- Analytical Study of the Comparative Pitch-Up Behavior of Several Airplanes and Correlation With Pilot Opinion
- From Introduction: "An extension of the work presented in reference 2, the method was applied to six swept-wing airplanes for which the pilot opinion was well documented. The analytical results obtained are used herein to illustrate how wind-tunnel data may be used to predict the pitching motions and the comparative pitch-up behavior of new airplane designs or to assess the effects of modifications on existing airplanes."
- Booby Traps
- The following report provides data taken of problematic situations that have led to accidental prompt-critical radiation bursts in critical assemblies laboratories, as well as a few risky instances. The purpose of this report is to prevent these mistakes from happening in the future.
- Calculated and Measured Stresses in Simple Panels Subject to Intense Random Acoustic Loading Including the Near Noise Field of a Turbojet Engine
- "Flat 2024-T3 aluminum panels measuring 11 inches by 13 inches were tested in the near noise fields of a 4-inch air jet and turbojet engine. The stresses which were developed in the panels are compared with those calculated by generalized harmonic analysis. The calculated and measured stresses were found to be in good agreement. In order to make the stress calculations, supplementary data relating to the transfer characteristics, damping, and static response of flat and curved panels under periodic loading are necessary and were determined experimentally. In addition, an appendix containing detailed data on the near pressure field of the turbojet engine is included" (p. 703).
- Cascade investigation of cooling characteristics of a cast-finned air-cooled turbine blade for use in a turboprop engine
- Report presenting an experimental investigation of the cooling characteristics of a small air-cooled turbine blade for use in a turboprop engine in a static cascade facility. Three test blades of the same size and chord were tested at several different combustion-gas temperatures. Results regarding the gas-flow conditions in cascade test section, correlation of temperature data and application of correlated data to typical engine are provided.
- Cascade Investigation of Cooling Characteristics of a Castfinned Air-Cooled Turbine Blade for Use in a Turboprop Engine
- Memorandum presenting an experimental investigation of the cooling characteristics of a small air-cooled turbine blade for use in a turboprop engine in a static cascade facility. Three test blades were studiued at three combustion-gas temperatures. Results regarding gas-flow conditions in cascade test section, correlation of temperature data, and application of correlated data to the typical engine are provided.
- Charts for estimating the effects of short-period stability characteristics on airplane vertical-acceleration and pitch-angle response in continuous atmospheric turbulence
- Report presenting charts for estimating the effects of variations in short-period stability characteristics of a rigid airplane on its root-mean-square vertical-acceleration and pitch-angle response to continuous atmospheric turbulence. A comparison of the root-mean-square vertical-acceleration response of an airplane free to be disturbed in vertical and pitching motion with that of an airplane free to be disturbed only in vertical motion indicates that the responses are similar for a nearly critically damped airplane.
- Chattanooga Shale and Related Rocks of Central Tennessee and Nearby Areas : An Abstract
- The following report covers the study of the Chattanooga shale and Maury formation found between the Nashville Basin and the surrounding Highland Rim.
- 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.
- 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.
- 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.
- The Crystal Structures of Three New Vanadium Oxide Minerals
- This report analyzes the characteristics of three vanadium-uranium ores of the Colorado Plateau by prevalence of a number of low-valence vanadium oxide minerals, usually occurring as fine-grained mixtures. The ores being analyzed are haggite, doloresite, and duttonite.
- Design and Engine Evaluation of a Semistrut Corrugated Air-Cooled Turbine Blade for Operation at a Tip Speed of 1300 Feet Per Second
- Report presenting an improved air-cooled turbine blade that was described, stress-analyzed, and evaluated in a full-scale turbojet engine. The blade consists of a sheet-metal outer shell and an internal strut of partial blade length. The effect on blade rupture life of varying outer-shell thickness, strut length, blade temperature distribution, and corrugation pitch and amplitude are provided.
- Design and experimental evaluation of a light-weight turbine-wheel assembly
- Report presenting lightweight design concepts, which were developed and tested in a full-scale turbine wheel with a tip diameter of 34.3 inches and a tip speed of 1190 feet per second. It consisted of a rotor of two thin alloy disks attached with spacers and bolts and hollow turbine blades. Testing indicated that it would be particularly applicable to an expendable missile engine.
- The Development of Botanical Methods of Prospecting for Uranium on the Colorado Plateau
- The following report covers detailed investigations on botanical methods of prospecting for uranium that have been developed on the Colorado Plateau by the U.S. Geological Survey.
- Dissociation of H₂⁺ by Photons
- Abstract: "A measurement was made of the dissociation of vibrationally-excited H2+ ions by photons having quantum energy in the vicinity of 4 e.v. The calculated cross section from theory is 3 x 10-(-18) cm-2. The experimental result is 10-(-17) cm-2; a factor of 10 uncertainty is present because the photon intensity was unknown by that factor."
- Drilling in the Monument Valley Area, San Juan County, Utah and Navajo County, Arizona
- Abstract: Napier Drilling Company of Dallas, Texas drilled 53,998.0 feet for exploration purposes, under Contract No. AT(05-1)-256. This footage was drilled in 508 holes during the period from June 21, 1954 through May 13, 1955.
- Effect of fuel properties on liner temperatures in a single tubular turbojet combustor
- Report presenting the effect of fuel properties on combustion-liner temperatures in a single tubular combustor at combustor-inlet conditions representative of those encountered in turbojet-powered high-flight-speed aircraft. Testing was conducted with three liquid jet-type fuels that varied in voltaility and aromatic content. The variations in fuel properties were found to produce only moderate and not always consistent changes in average liner temperature.
- Effect of Hinge-Line Position on the Oscillating Hinge Moments and Flutter Characteristics of a Flap-Type Control at Transonic Speeds
- Free oscillation test to determine hinge moment of trailing-edge, flap control surface with various hinge-line positions at transonic speed. Results show that oscillating amplitude has a large effect on the control aerodynamic damping derivative and that the damping is unstable in the test Mach number range above about 0.90 for the hinge positions tested.
- Effect of hinge-line position on the oscillating hinge moments and flutter characteristics of a flap-type control at transonic speeds
- Report presenting free-oscillation tests to determine the dynamic hinge-moment characteristics of a trailing-edge, flap-type control surface with various hinge-like positions. Oscillating amplitude was found to have a large effect on the control aerodynamic damping derivative and the damping was found to be unstable in the test Mach number range above 0.90 for the hinge positions tested. Results regarding damping moments and flutter characteristics, spring moments, and effect of hinge-line position and comparison with theory are provided.
- Effect of Quadrupole Lenses
- "The effect of correcting quadrupole lenses on the betatron oscillation characteristics of an AG synchrotron was studied, and general formulas are given for the fractional changes of the amplitude and phase functions. Calculations performed for different setups of different numbers of lenses for the CEA synchrotron structure point out that one may correct for sizable errors in the n- value by means of 8 pairs of quadrupole lenses in two consecutive straight sections with the focusing lens between defocusing sectors and vice versa. An increase of BETA /sub max/ of about 5% is obtained for DELTA n/n approximately 0.04. It was found that the necessary corrections can probably be obtained satisfactorily with lenses of 6 in. length. "
- Effect of Some External Crosswise Stiffeners on the Heat Transfer and Pressure Distribution on a Flat Plate at Mach Numbers of 0.77, 1.39, and 1.98
- The heat transfer and pressures on the surfaces of several flat-plate models with various external crosswise stiffener arrangements are presented. The tests were made in a free jet at Mach numbers of 0.77, 1.39, and 1.98 for Reynolds numbers of 3 x 10(exp 6), 7 x 10(exp 6), and 14 x 10(exp 6), respectively, based on a length of 1 foot. The addition of external crosswise stiffeners to the flat-plate models caused large pressure and heat-transfer variations on the surfaces of the models.
- Effect of Transient Heating on Vibration Frequencies of Some Simple Wing Structures
- "Thermal stresses, which may result from transient heating, can cause changes in the effective stiffness of wing structures. Some effects of this change in stiffness were investigated experimentally by radiantly heating three types of simple wing structures: a uniform plate, a solid double-wedge section, and a circular-arc multiweb-wing section. Changes in stiffness were determined by measuring the changes in natural frequency of vibration during transient heating. Some comparisons are made between theoretical calculations and the measured data" (p. 1).
- Effects of Horizontal-Tail Position and a Wing Leading-Edge Modification Consisting of a Full-Span Flap and a Partial-Span Chord-Extension on the Aerodynamic Characteristics in Pitch at High Subsonic Speeds of a Model With a 45 Degree Sweptback Wing
- Note presenting an investigation conducted in the high-speed 7- by 10-foot tunnel to determine the effects of varying the horizontal-tail position relative to the wing chord plane on the aerodynamic characteristics in pitch of a general research model having a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.30, and NACA 65A006 airfoil sections. The investigation also included the effects of a wing modification consisting of a full-span leading-edge flap deflected 6 degrees and an outboard partial-span chord-extension.
- Effects of Rapid Heating on Strength of Airframe Components
- Note presenting results of several experimental investigations which indicate the effects of rapid heating on the bending strength of multiweb beams and ring-stiffened cylinders. Thermal stresses are shown to reduce the bending load carried at buckling by both beams and cylinders.
- Effects of Some Configuration Changes on Afterburner Combustion Performance
- Report presenting an experimental investigation in a simulated afterburner test rig to determine the effects of some configuration variations on afterburner combustion performance. Results regarding the reduced-diameter flameholder, inclined radial-gutter flameholder, tapered-shell afterburner, and turbulence generators are provided.
- Effects of Some Configuration Changes on Afterburner Combustion Performance
- Memorandum presenting an experimental investigation conducted in a 25.75-inch-diameter simulated-afterburner test rig to determine the effects of some configuration variations on afterburner combustion performance. The variations included a V-gutter flameholder with the maximum gutter-ring diameter reduced from 20 to 17 inches, but with equal projected blockage; an inclined radial-gutter flameholder; a tapered-shell afterburner; and a V-gutter flameholder with turbulence generators added.
- Estimation of Compressible Boundary-Layer Growth Over Insulated Surfaces With Pressure Gradient
- Note presenting the incompressible boundary-layer theory of Truckenbrodt extended using a modified Stewartson-type transformation to include compressible boundary-layer development over insulated surfaces. The method is applicable to two-dimensional and axisymmetric, laminar and turbulent boundary layer, and accounts for the pressure gradient along the wall for both compressible and incompressible flow. Some experimental measurements of the boundary layer on small axisymmetric bodies on the wall of a supersonic wind tunnel compared with theoretical predictions.
- Experimental Investigation of Effects of Combustion-chamber Length and Inlet Total Temperature, Total Pressure, and Velocity on Afterburner Performance
- Report presenting an investigation of the effects of afterburner-inlet total temperature, total pressure, velocity, fuel-air ratio, and afterburner combustion-chamber length on afterburner performance and stability limits using a cylindrical afterburner installed in a duct test rig. The afterburner was investigated over a range of total temperature, total pressure, velocity, and afterburner fuel-air ratios.
- Experimental Investigation of Modified Cast-Cored Blades Having Hollow Tip Sections
- Memorandum presenting the development of fabrication techniques to provide cast-cored turbine blades with hollow tip sections. Two types of modified cast-cored blades that provided an 11-percent weight reduction from a fully cast-cored blade and a 13-percent weight reduction from a standard uncooled blade were investigated in a turbojet engine modified for air-cooling. Results regarding the experimental heat-transfer, temperature comparison with other cooled-blade configurations, calculated and experimental blade temperatures, cooling-air pressure drop, and structural reliability are provided.
- Experimental Investigation of the Transonic and Supersonic Flutter Characteristics of the Upper and Lower Vertical Tails of an Air-to-Ground Missile
- "Flutter models of the upper and lower vertical tails of an air-to-ground missile have been tested in the Mach number range from 0.5 to 3.0. It was found that the upper surface exhibited more or less conventional flutter behavior throughout the Mach number range, whereas the lower surface experienced a sudden change in flutter mode at a Mach number of about 1.18. This change in flutter mode was accompanied by a decrease of about 50 percent in the density required for flutter to occur" (p. 1).
- Exploratory drilling on Frey Point Mesa, White Canyon area, San Juan County, Utah
- The principal objectives of the exploratory diamond drilling programs conducted by the U.S. Atomic Energy Commission on Frey Point Mesa were to determine the presence of minable uranium ore; to study the lithologic and structural characteristics of paleostream channels and their relation to ore occurrence; and to accumulate geologic information essential for an appraisal of the uranium resources of the area.
- Extraction of Uranium and Other Actinides From Nitric Acid by Di-N-Butyl N-Butylphosphonate
- From abstract: "Equilibrium data are presented for the distribution of uranium, other actinides, zirconium, and nitric acid between aqueous solutions and di-n-butyl n-butylphosphonate diluted with n-dodecane. Data for the physical properties and chemical stability of the phosphonate are also given."
- Factors Affecting Loads at Hypersonic Speeds
- Report presenting a brief summary of current loads information at hypersonic speeds and some ways of estimating the loads on aircraft components when designing an aircraft.
- Flight-determined induction-system and surge characteristics of the YF-102 airplane with a two-spool turbojet engine
- Report presenting a brief compressor-surge and pressure-recovery program for the Convair YF-102 with a two-spool turbojet engine. The study covered a range of altitudes and Mach numbers.
- Flutter and Divergence of Rectangular Wings of Very Low Aspect Ratio
- "Slender-body aerodynamic theory is used in conjunction with thin-plate theory in the flutter analysis of low-aspect-ratio rectangular wings of constant thickness when chordwise variations of deflections are considered. The spanwise variation of deflection is given by a parabola, and the chordwise variation is allowed complete freedom. The results show the variation of flutter speed and mode shape with aspect ratio" (p. 1).
- Frequency Response Measurements of the EBWR Automatic Steam by-Pass Valve Control System
- Report describing the steam by-pass system of the Economic Simplified Boiling Water (EBWR) Reactor. The control system and errors are described.
- A Further Evaluation of the Calder Hall Type of Nuclear Power Plant
- Abstract: This report presents the results of plant optimization studies and cost estimates of the reference design for a natural uranium, graphite moderated, gas-cooled reactor and power plant which was described in NAA-SR-1833.
- Geochemistry of Uranium in Phosphorites and Black Shales of the Phosphoria Formation
- Report discussing the geochemistry of uranium in phosphorites and black shales of the phosphoria formation, with the assumption that the immediate source of the uranium in the Phosphoria formation was the ocean.
- Geology of the Aluminum Phosphate Zone in the Lakeland Highlands Area and Clark James-South Ridgewood Tracts, Land-Pebble Phosphate District, Polk County, Florida
- The following report is based mainly on information obtained from lithologic and gamma-ray logs of drill holes in the Lakeland Highlands area and Clark James-South Ridgewood.