UNT Libraries Government Documents Department - 360 Matching Results

Search Results

Results: 1 - 50 next
1024 Channel Time-of-Flight Analyzer for MTR Fast Chopper - Operating Manual
Report on the principle of measuring the time-of-flight of neutrons, magnetic-core storage of detector pulses, how pulses are stored, current generator, storage cycle generator, and cathode ray oscillograph.
Advanced Designs and Special Applications for Fast Breeders
The purpose of this paper is to describe a few of the suggested advanced concepts for fast breeder reactors and to compare these with the standard approach as to their potential advantage. I have attempted to estimate the economic effect of full technical success with each of the proposed concepts. The proposed concepts include: (1) single sodium system, (2) steam-cooled core concept, (3) direct cycle reactor using potassium as reactor coolant and working fluid, (4) molten plutonium-fuel alloy circulated and cooled by a jet of sodium, (5) settled-bed core, (6) molten salt concept, and (7) paste-fuel system.
Aerial Radiometric and Magnetic Survey: Trona National Topographic Map, California. Volume 1
The results of analyses of the airborne gamma radiation and total magnetic field survey flown for the region identified as the Trona National Topographic Map NI-11-12 is presented in Volume I and II of this report. This volume gives the description of the program and the results.
Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Transonic Speeds
"Tests have been conducted in the Langley 8-foot transonic tunnel on a 0.04956-scale model of the Convair F-102A airplane which employed an indented and extended fuselage, cambered wing leading edges, and deflected wing tips. Force and moment characteristics were obtained for Mach numbers from 0.60 to 1.135 at angles of attack up to 20 degrees. In addition, tests were made over a limited angle-of-attack range to determine the effects of the cambered leading edges, deflected tips, and a nose section with a smooth area distribution" (p. 1).
Aerodynamic Characteristics of a Circular Cylinder at Mach Number 6.86 and Angles of Attack Up to 90 Degrees
"Pressure-distribution and force tests of a circular cylinder have been made in the Langley 11-inch hypersonic tunnel at a Mach number of 6.86, a Reynolds number of 129,000 based on diameter, and angles of attack up to 90 degrees. The results are compared with the hypersonic approximation of Grimminger, Williams, and Young and with a simple modification of the Newtonian flow theory. The comparison of experimental results shows that either theory gives adequate general aerodynamic characteristics but that the modified Newtonian theory gives a more accurate prediction of the pressure distribution" (p. 1).
Aerodynamic characteristics of a flying-boat hull having a length-beam ratio of 15 and a warped forebody
From Introduction: "The results of two phases of this investigation, presented in references 1 and 2, have indicated possible ways of reducing hull drag without causing large changes in aerodynamic stability and hydrodynamic performance."
The aerodynamic characteristics of a supersonic aircraft configuration with a 40 degree sweptback wing through a Mach number range from 0 to 2.4 obtained from various sources
"A summary and analysis have been made of the results of various investigations to determine the aerodynamic characteristics of a supersonic aircraft configuration. The configuration has a wing with 40 degree sweepback at the quarter-chord line, aspect ratio 4, taper ratio 0.5, and 10-percent-thick circular-arc sections normal to the quarter-chord line. Experimental data were available for a Mach number range from 0.16 to 2.32. Results obtained from wing-flow, rocket-model, transonic-bump, and tunnel tests are presented and, where possible, are supplemented by empirical and theoretical calculations" (p. 1).
Aerodynamic Design of Axial-flow Compressors 6 - Experimental Flow in Two-Dimensional Cascades
"Available experimental two-dimensional cascade data for conventional compressor blade sections are correlated at a reference incidence angle in the region of minimum loss. Variations of reference incidence angle, total-pressure loss, and deviation angle with cascade geometry, inlet Mach number, and Reynolds number are investigated. From the analysis and the correlations of the available data, rules and relations are evolved for the prediction of blade-profile performance" (p. 1).
Aerodynamic heating of a wing as determined from a free-flight rocket-model test to Mach number 3.64
From Introduction: "The primary purpose of the wing instrumentation was to obtain data for use in design of NACA research missiles; however, it is believed that the wing is representative of typical supersonic designs and that the data will be of general use and interest. Only the wing data are reported herein."
Aerodynamic Heating of Blunt Nose Shapes at Mach Numbers Up to 14
From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on this problem."
Aerodynamic heating of blunt nose shapes at Mach numbers up to 14
From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on the problem."
Aerodynamic Measurements Made During Navy Investigation of Human Tolerance to Wind Blasts
From Summary: "This report presents the aerodynamic measurements made during a Navy investigation conducted in the Langley 8-foot high speed tunnel to determine the actual human tolerance to wind blasts."
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Subsonic Mach and Reynolds number effects on the characteristics of the wing and on the effectiveness of an elevon
Report presenting a wind-tunnel investigation of a semispan model of a wing swept back 63 degrees with an aspect ratio of 3.5 and a taper ratio of 0.25. The tests were conducted to evaluate the effects of Reynolds and Mach number on the aerodynamic characteristics of the wing. Results regarding the characteristics of the wing with the elevon undeflected, effectiveness of the elevon, effects of roughness strips, and effect of model deflection under varying loads are provided.
Airfoil section characteristics as affected by protuberances
From Introduction: "The present report deals with another phase of the investigation; that is, the effects on airfoil section characteristics of protuberances extending along the entire span from the airfoil surface."
Alternating Current and Square-Wave Polarography
A exploratory study was made of a polarographic technique in which an alternating sine or square-wave potential is superimposed upon the applied d.c. potential of the polarographic scan. Recording of the a.c. component of the polarographic current results in derivative-type waves. It was shown that the technique yields greater sensitivity and greater selectivity than normal polarographic technique.
Altitude performance characteristics of tail-pipe burner with variable-area exhaust nozzle
From Introduction: "Data are presented to show the effects of tail-pipe fuel-air ratio, altitude, and flight Mach number on tail-pipe-burner performance at rated engine speed and approximately constant turbine-outlet temperature. Operational characteristics of the tail-pipe burner and variable-area exhaust nozzle are also reported."
Altitude-Wind-Tunnel Investigation of Oil-System Performance of XR-4360-8 Engine in XTB2D-1 Airplane
"An investigation was conducted in the Cleveland altitude wind tunnel to determine the aerodynamic characteristics and the oil delivery critical altitude of the oil-cooler installation of an XTB2D-1 airplane. The investigation was made with the propeller removed end with the engine operating at 1800 brake horsepower, an altitude of 15,000 feet (except for tests of oil-delivery critical altitude), oil-cooler flap deflections from -20 degrees to 20 degrees and inclinations of the thrust axis of 0 degrees, 1.5 degrees, and 6 degrees. At an inclination of the thrust axis of 0 degrees and with the propeller operating, the total-pressure recovery coefficient at the face of the oil cooler varied from 0.84 to 1.10 depending on the flap deflection" (p. 1).
Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loading, 1, Aeroproducts H20C-162-X11M2 Four-Blade Propeller
"An investigation was made in the Cleveland Altitude wind tunnel to determine the performance of an Aeroproducts H20C-162-X11M2 four-blade propeller on a YP-47M airplane at high blade loadings and high engine powers. The propeller characteristics were obtained for a range of power coefficients from 0.30 to 1.00 at free-stream Mach numbers of 0.40 and 0.50. The results of the force measurements are indicative only of trends in propeller efficiency with changes in power coefficient and advance-diameter ratio because unknown interference effects existed during the investigation" (p. 1).
Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine 3: performance with tail-pipe burning in standard-size tail pipe
From Introduction: "Evaluation of tail-pipe burning in this engine with a larger tail-pipe combustion chamber is discussed in reference 1. Results of investigations on tail-pipe burning in this engine at static sea-level conditions are presented in reference 2. An investigation of thrust augmentation by means of injecting water at the inlet of an axial-flow compressor engine is discussed in reference 3."
An analysis of available data on effects of wing-fuselage-tail and wing-nacelle interference on the distribution of the air load among components of airplanes
From Introduction: "The purpose of the present paper is to summarize the available data on the effects of wing-fuselage-tail and wing-nacelle interference on the distribution of the air load among aircraft components. Some discussion is also given of the effects of center-of-gravity position."
An analysis of base pressure at supersonic velocities and comparison with experiment
From Introduction: "The primary purpose of the investigation described in the present described in the present report is to formulate a method which is of value for qualitative calculations of base pressure both on airfoils and bodies."
Analysis of factors affecting selection and design of air-cooled single-stage turbines for turbojet engines 4: coolant-flow requirements and performance of engines using air-cooled corrugated-insert blades
Report presenting an investigation of the estimated minimum cooling requirements and related performance of turbojet engines equipped with high-performance single-stage turbines with air-cooled corrugated-insert blades over a range of turbine-inlet temperature, tip speed, and hub-tip radius ratio for Mach number 2 at 50,000 feet. The effects of stress-ratio factor, flight Mach number, altitude, turbine rotor impeller efficiency, and outside heat-transfer coefficient on cooling requirements were also investigated.
Analysis of Fully Developed Turbulent Heat Transfer at Low Peclet Numbers in Smooth Tubes With Application to Liquid Metals
From Introduction: "Analyses of heat transfer for liquid metals flowing turbulently in smooth tubes (low Pradtl numbers) are given in reference 1 and 2. The predicted heat-transfer coefficients from these analyses are considerably higher than those determined in the experimental heat-transfer investigations for mercury and lead bismuth given in references 2 to 4. If the analytical and experimental results for flow of gases are compared at low Peclet numbers, they are also found to be in disagreement (references 5 and 6)."
Analysis of Meteorological Data Obtained During Flight in a Supercooled Stratiform Cloud of High Liquid-Water Content
"Flight icing-rate data obtained in a dense and abnormally deep supercooled stratiform cloud system indicated the existence of liquid-water contents generally exceeding values in amount and extent previously reported over the midwestern sections of the United States. Additional information obtained during descent through a part of the cloud system indicated liquid-water contents that significantly exceeded theoretical values, especially near the middle of the cloud layer. The growth of cloud droplets to sizes that resulted in sedimentation from the upper portions of the cloud is considered to be a possible cause of the high water contents near the center of the cloud layer" (p. 1).
Analysis of Rocket, Ramjet, Turbojet Engines for Supersonic Propulsion of Long-Range Missiles 2: Rocket Missile Performance
Memorandum presenting an investigation of the theoretical performance of a two-stage ballistic rocket missile with a centerbody and two parallel boosters for JP4-oxygen and ammonia-fluorine propellants. The missile using the ammonia-fluorine propellant weighs about one-half as much as a missile using JP4-oxygen. Results regarding the optimum missile and effect of variation of design parameters are provided.
Analytical and experimental studies of a divided-flow ram-jet combustor
From Introduction: "The investigation reported herein is a continuation of a ram-jet-combustor design program being conducted at the NACA Lewis laboratory. The purpose of this broad program is to establish basic design criteria for combustors operating over wide range of fuel-air ratio with low pressure losses and high combustion efficiency, and to utilize these design criteria in the development of practical ram-jet combustors."
Analytical determination of local surface heat-transfer coefficients for cooled turbine blades from measured metal temperatures
Analytical methods are presented for the determination of local values of outside and inside heat-transfer coefficients and effective gas temperatures by use of turbine-blade-temperature measurements. The methods are derived for a number of configurations that can be applied to typical cooled-turbine-blade shapes as well as to other types of heat-transfer apparatus.
Application of Ascorbic Acid Method to Uranium in Salvage Solutions
Abstract: The erroneously high values for uranium content of salvage solutions as determined by the ether extraction-ascorbic acid procedure have been demonstrated to be due to the presence of colored organic materials in these solutions. Evaporation of such solutions to fumes of HC104 before extraction has been shown to be completely successful in preventing such interference while pretreatment with activated carbon is sufficiently successful for application in Control laboratories. Complete procedures for application of either protreatment and results of such application to composite salvage solutions received over a six-month period are included.
Automatic control systems satisfying certain general criterions on transient behavior
"An analytic method for the design of automatic controls is developed that starts from certain arbitrary criterions on the behavior of the controlled system and gives those physically realizable equations that the control system can follow in order to realize this behavior. The criterions used are developed in the form of certain time integrals. General results are shown for systems of second order and of any number of degrees of freedom. Detailed examples for several cases in the control of a turbojet engine are presented" (p. 207).
Average Physical Properties of Tuff in the Vicinity of Ground Zero, U12g.01 Tunnel, Nevada Test Site, Nye County, Nevada
This report presents the physical properties of tuff in the vicinity of the U12g.01 tunnel at the Nevada Test Site based off of two previous Technical Letters on the tunnel: Technical Letter: Area 12-1, and Technical Letter 12-1, Supplement 1.
Backmixing in Pulse Columns II, Experimental Values and Effect of Several Variables
Seven runs were made with the system Penn. Ref. Co. "Supersol" (dispersed) water (continuous) to investigate the effects of pulse frequency, amplitude plate spacing, volume flow ratio, and throughput on backmixing, using the technique of continuous injection of a tracer solution into the packed section. Backmixing was found to be surprisingly insensitive to all the above variables over the range studied with the exception of pulse amplitude and continuous phase flow rate, showing greatest dependence on the later. Backmixing increased with decreasing continuous phase flow rate and increased with pulse amplitude.
Behavior of Transistors in a Magnetic Field
Experiments are described which show that magnetic fields can exert a controlling influence on the operating characteristics of point contact transistors. The effect is especially evident when the transistor is operated in its negative resistance region. The frequency of an oscillator can be varied, or a switch made to trigger by applying a magnetic field to the transistor. Some applications of the principle are suggested; many more are evident.
Calculated Performance of Nuclear Turbojet Powered Airplane at Flight Mach Number of 0.9
"An analysis was made at flight Mach number of 0.9 to estimate performance of nuclear-energy-powered turbojet engine and optimum engine operating conditions and to determine gross weight and load-carrying capacity of airplane powered by such an engine. The size of airplane required to carry disposable load of 20,000 pounds was found to vary from approximately 300,000 to 900,000 pounds depending on assumptions. For a reactor tube-wall mean temperature of 2500 degrees R, turbine-inlet temperature of 2000 degrees R, reactor-free-flow-area ratio of 0.33, reactor-shielding-material specific gravity of 6.0, shielding thickness of 3.0 feet, and altitude of 30,000 feet, the airplane gross weight required to carry a 20,000 payload is 545,000 pounds" (p. 1).
Calculation of Shield Induced Gamma Radiation Escaping Through Openings in a Biological Shield -- Application to the HRT
A method was developed for calculating shield induced gamma radiation escaping through openings in a biological shield. The method was applied to the HRT and the results indicated that the contribution to the dose from induced activity in the HRT shield was around 0.1 r/hr and was insignificant in comparison to to other mechanisms contributing to the escape of gamma rays through shield openings.
Calculation of Wing Bending Moments and Tail Loads Resulting from the Jettison of Wing Tips During a Symmetrical Pull-Up
"A preliminary analytical investigation was made to determine the feasibility of the basic idea of controlled failure points as safety valves for the primary airplane structure. The present analysis considers the possibilities of the breakable wing tip which, in failing as a weak link, would relieve the bending moments on the wing structure. The analysis was carried out by computing the time histories of the wing and stabilizer angle of attack in a 10g pull-up for an XF8F airplane with tips fixed and comparing the results with those for the same maneuver, that is, elevator motion but with tips jettisoned at 8g" (p. 1).
Calibration of instruments for measuring wind velocity and direction
From Summary: "Signal Corps wind equipment AN/GMQ-1 consisting of a 3-cup anemometer and wind vane was calibrated for wind velocities from 1 to 200 miles per hour. Cup-shaft failure prevented calibration at higher wind velocities. The action of the wind vane was checked and found to have very poor directional accuracy below a velocity of 8 miles per hour. After shaft failure was reported to the Signal Corps, the cup rotors were redesigned by strengthening the shafts for better operation at high velocities. The anemometer with the redesigned cup rotors was recalibrated, but cup-shaft failure occurred again at a wind velocity of approximately 220 miles per hour."
Ceramic-Based Materials for High Temperature Service
The following report provides data that was discovered from a preliminary literature survey that was made to define the utility of the newer refractory ceramics or ceramic-based materials.
Characterization of Inclusion in Dingot Uranium
Abstract: The nonmetallic inclusions in both as-reduced and fabricated dingot uranium have been studied for comparison with those in ingot uranium. Special attention was paid to the hydride for the purpose of determining the amount and distribution in the various types of uranium. The types and distribution of other inclusions were also studied. It was found that the dingot uranium was of a higher quality than ingot uranium and was comparable to as-reduced derby uranium on the basis of over-all inclusion count. The hydrogen content in dingot uranium, however, was found to be appreciably higher than in either ingot or derby uranium.
Chemistry Division, Section C-1, Quarterly Report July, August, and September 1952
Report describing the research and development activities related to nuclear chemistry and radiochemistry and basic chemistry conducted by the Argonne National Laboratory Chemistry Division, Section C-1.
Coefficients of discharge of fuel-injection nozzles for compression-ignition engines
"This report presents the results of an investigation to determine the coefficients of discharge of nozzles with small, round orifices of the size used with high-speed compression-ignition engines. The injection pressures and chamber back pressures employed were comparable to those existing in compression-ignition engines during injection. The construction of the nozzles was varied to determine the effect of the nozzle design on the coefficient. Tests were also made with nozzles assembled in an automatic injection valve, both with a plain and with a helically grooved stem" (p. 193).
Cofit - A 709 Program for Determining Extrapolation Length from Horizontal Traverse Data
A program has been prepared for the 709 computer which will determine extrapolation length from horizontal traverses measurements taken in an exponential pile. The flux across the pile is assured to fit a cosine function of the form y = A cos B (X-C)
Column Adsorption Methods in Analytical Chemistry
Technical report. Numerous application of various column adsorption techniques to inorganic analytical chemistry have appear in the literature. The comparatively recent introduction of ion exchange resins has resulted in the development of efficient, simple, and rapid column adsorption methods. the principal service of column adsorption methods to analytical chemistry is that of providing a relatively simple means of separating an element in a sufficiently pure state so that a direct precipitation, ignition, and weighting, for example, will suffice to complete the quantitative analysis. Systems involving uranyl nitrate will naturally be emphasized in this report but information will be included concerning the separation of the individual members of a series from one another, such as in the alkaline earths and the rare earths.
The comparative performance of an aviation engine at normal and high inlet air temperatures
"This report presents some results obtained during an investigation to determine the effect of high inlet air temperature on the performance of a Liberty 12 aviation engine. The purpose of this investigation was to ascertain, for normal service carburetor adjustments and a fixed ignition advance, the relation between power and temperature for the range of carburetor air temperatures that may be encountered when supercharging to sea level pressure at altitudes of over 20,000 feet and without intercooling when using plain aviation gasoline and mixtures of benzol and gasoline" (p. 409).
A Comparison of Elementary Criticality Calculations with Experimental Results
Several experiments have been performed at ORNL with light water solutions of uranyl nitrate (highly enriched in either U^233 or U^235) in an essentially bare sphere 27 inches in diameter. This report presents the results of several calculations with elementary bare reactor theory and a discussion of the observed discrepancies between the calculated and experimental results. If the observed critical concentration is used in the calculations, the calculated effective multiplication constant is less than unity' thus a higher critical concentration would be predicted than is actually observed.
Comparison of Hovering Performance of Helicopters Powered by Jet-Propulsion and Reciprocating Engines
Report presenting an investigation of the maximum hovering time, or the time that a helicopter can sustain itself without motion, for helicopters using a reciprocating engine, by ramjet engines at the tips of rotor blades, and by pulse-jet engines at the tips of rotor blades. Testing showed that the reciprocating engine permitted much longer hovering time than the jet-propulsion engines, but the jet-propulsion engines were much lighter and could lift greater disposable loads.
Comparison of measured and predicted indicated angles of attack near the fuselages of a triangular-wing wind-tunnel model and a swept-wing fighter airplane in flight
Report presenting measurements of the local flow angles near the fuselages of a triangular-wing wind-tunnel model and an F-86A-5 airplane in flight using airflow detectors on the fuselages. A comparison of the measured and predicted flow angles is provided. Results indicated that the accuracy of the predicted indicated angles of attack was not sufficient to eliminate the necessity of a flight calibration of a detector mounted on a fuselage.
Comparison of the Thermal Conductivity, Electrical Resistivity, and Seebeck Coefficient of a Hight-Purity Iron and Armco Iron to 1000 [degrees] C
The thermophysical properties of Armco iron such as thermal conductivity, electrical resistivity, and Seebeck coefficient have been extensively investigated and reviewed up to 1000 degrees C. Few investigations of such properties have been made on high purity iron. If such a study is made using the same apparatus to determine the properties of two purity levels of iron, then several significant intercomparisons can be made which add meaning to data on a single material. The systemic errors for a single apparatus are the same, therefore comparison of a property of two similar materials is more significant. A comparison of the property changes with temperature and purity can show the effects of impurities on the mechanisms contributing to a property and allows prediction of the properties of iron as a function of purity. For these reasons a study was initiated on the high-purity iron for comparison to Armco iron.
Comparison of two methods of modulating the throat area of convergent plug nozzles
Report presenting an investigation to determine the effect on performance of two methods of throat-area modulation of two convergent plug nozzles. Data were obtained over a range of pressure ratios. Results regarding the performance of the translatable outer-shell-type plug nozzle, performance of the iris-outer-shell-type plug nozzles, sensitivity to throat-area variation, and air-flow parameter are provided.
Comparison of wind-tunnel and flight measurements of stability and control characteristics of a Douglas A-26 airplane
From Summary: "Stability and control characteristics determined from tests in the Langley 19-foot pressure tunnel of a 0.2375-scale model of the Douglas XA-26 airplane are compared with those measured in flight tests of a Douglas A-26 airplane. Agreement regarding static longitudinal stability as indicated by the elevator-fixed neutral points and by the variation of elevator deflection in both straight and turning flight was found to be good except at speeds approaching the stall. At these low speeds the airplane possessed noticeably improved stability, which was attributed to pronounced stalling at the root of the production wing."
A comparison with flight data of vertical-tail loads in various maneuvers estimated from sideslip angles and rudder deflections
Report presenting a comparison of the vertical-tail loads determined from pressure-distribution measurements in flight in various maneuvers with the corresponding vertical-tail loads. Some of the maneuvers investigated included slow rolls, steady sideslips, fishtails, and rolling pull-outs.
Back to Top of Screen