Technical Report Archive & Image Library (TRAIL) - 1,386 Matching Results
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- 11,400 KW Nuclear Power Plant Employing an Organic Moderated Reactor: Preliminary Description
- Abstract: The preliminary design is described for a small electric-power-generating plant powered by an organic moderated reactor. System and component requirements are discussed and possible design configurations and equipment are described.
- 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.
- 20,000 KW Nuclear Power Plant Study for United States Atomic Energy Commission
- Introduction: In September of 156, Gilbert Associates, Inc., entered into a contract with the United States of America, acting through the United States Atomic Energy Commission, for the study and preliminary design of a nuclear power plant being considered for integration into a central station power system at an overseas site.
- Abnormal grain growth in M-252 and S-816 alloys
- Report discussing an experimental investigation was carried out on air- and vacuum-melted M-252 and S-816 alloys to find conditions of heating and hot-working which resulted in abnormal grain growth. The experiments were mainly limited to normal conditions of heating for hot-working and heat treatment and normal temperatures of solution treatment were used to allow grain growth after susceptibility to abnormal grain growth was developed by various experimental conditions. Results indicated that small reductions of essentially strain-free metal were the basic cause of such grain growth.
- Abnormal grain growth in nickel-base heat-resistant alloys
- From Introduction: "The data included in this report for Nimonic 80A alloy, for instance, represent experiments carried out to help clarify a production problem of grain-size control in an alloy which has been extensively used. The general procedure of the investigation was to carry out controlled laboratory experiments on samples of bar stock to find conditions of heating and hot-working which resulted in abnormal grain growth."
- An Abrasive Cutoff Machine for Metallurgical Research on Radioactive Materials
- An abrasive cutoff machine design, based upon a previous model, (1) was undertaken to provide for the sampling of radioactive material. the design objective was; first, to provide samples for metallographic examination, second, to provide samples for physical and mechanical property testing, and, third, to meet the following design requirements: 1. Remote operation. 2. Airborne contamination control. 3. Radioactive waste collection. 4. Remote maintenance.
- Accelerations in fighter-airplane crashes
- From Introduction: "This report describes some measurements of these quantities obtained by crashing fighter aircraft under circumstances approximating those observed in service."
- Accident in Continuous-Dissolver Pilot Plant of Fluoride Volatility Project on May 15, 1957
- The so-called Fluoride Volatility Processes refer to several proposed non-aqueous methods of processing irradiated fuel elements. In each of these methods, the uranium is fluorinated to UF6 and then decontaminated by distillation. One of those methods, involving the direct fluorination of the uranium by bromine trifluoride (BTF), has been under investigation at BNL since 1950. In 1952, it was demonstrated at BNL that uranium, as UF6, could be satisfactorily decontaminated by distillation in small-scale pilot plant equipment; end in 1953, BNL undertook the job of determining the technical feasibility of a continuous dissolver on a pilot-plant scale. The reason for the project was that the economic superiority of the process seemed to depend upon its amenability to continuous operation.
- Accidents from explosives at metal and nonmetallic mines
- Circular produced by the U.S. Bureau of Mines to promote safety through a series of reports on accident prevention in mines. According the the scope statement, "This is the fourth section of the revised series of circulars that cover various phases of accident prevention in metal and nonmetallic mines; it give information on accidents and injuries from storing, handling, and using explosive in metal and nonmetallic mines and discusses the precautions by which they can be prevented" (p. 2).
- 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.
- Additional Experiments With Flat-Top Wing- Body Combinations at High Supersonic Speeds
- Memorandum presenting an experimental study of the effects of several variations in configuration geometry on the aerodynamic characteristics of flat-top wing-body combinations. Generally, the configurations consist of one half of a body of revolution mounted beneath a wing of essentially arrow plan form. Results regarding the effect of trailing-edge sweep, effect of the addition of auxiliary bodies, effect of tip-flap deflection, effect of dihedral, effect of leading-edge sweep, effect of fuselage fineness ratio, effect of fuselage profile shape, and static longitudinal stability characteristics are provided.
- Adsorption of Zirconium-Niobium on Silica Gel
- From abstract: "Adsorption of radioactive zirconium-niobium from uranyl nitrate solutions by silica gel was increased by increasing the temperature and time the solution contacts silica gel, and decreased by "aging" the solutions before contacting the silica gel."
- Amplitude and Phase Functions for the Revised Parameters of the Cambridge Electron Accelerator
- "The phase and amplitude functions describing the betatron oscillations in the synchrotron are calculated using the revised parameters of the Cambridge Electron Accelerator. The results are given numerically and plotted in a graph for one machine period."
- Aerodynamic and hydrodynamic characteristics of a proposed supersonic multijet water-based hydro-ski aircraft with a variable-incidence wing
- From Introduction: "The configuration described in this paper represents one approach to such an airplane and the results of the wind-tunnel and tank evaluations are presented. In the present investigation, the aerodynamic longitudinal characteristics over a Mach number range from 0.6 to 1.97 were obtained."
- Aerodynamic characteristics at Mach number of 4.06 of a typical supersonic airplane model using body and vertical-tail wedges to improve directional stability
- Report presenting an investigation at Mach number 4.06 on a typical supersonic airplane model with a 40 degree sweptback wing. The purpose of the investigation was to determine the effectiveness of using wedges on the body and on the vertical tail to increase the static directional stability. Results regarding the longitudinal characteristics and lateral characteristics are provided.
- Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair TF-102A Airplane at Transonic Speeds, Coord. No. AF-120
- "The basic aerodynamic characteristics of a 0.04956-scale model of the Convair TF-102A airplane with controls undeflected have been determined at Mach numbers from 0.60 to 1.135 for angles of attack up to approximately 22 deg in the Langley 8-foot transonic tunnel. In addition, comparisons have been made with data obtained from a previous investigation of a 0.04956-scale model of the Convair F-102A airplane. The results indicated the TF-102A airplane was longitudinally stable for all conditions tested" (p. 1).
- The aerodynamic characteristics of a body in the two-dimensional flow field of a circular-arc wing at a Mach number of 2.01
- From Introduction: "The present report is concerned with the characteristics of a body in the two-dimensional flow field of a circular-arc wing of rectangular plan form."
- 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 6.88, a Reynolds number of 129,000, and angles of attack up to 90 degrees. The results are compared with the hypersonic approximation of Grimminger, Williams, and Young and a simple modification of the Newtonian flow theory. An evaluation of the crossflow theory is made through comparison of present results with available crossflow Mach number drag coefficients" (p. 1).
- Aerodynamic Characteristics of a Model of an Escape Capsule for a Supersonic Bomber-Type Airplane at a Mach Number of 2.49
- Report discussing an investigation of the aerodynamic characteristics of a model of an escape capsule with and without stabilizing fins for a supersonic bomber-type airplane. Lift, drag, longitudinal and lateral stability characteristics, and photographs of the capsule model are presented.
- 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 Forces and Moments on a Large Ogive-Cylinder Store at Various Locations Below the Fuselage Center Line of a Swept-Wing Bomber Configuration at a Mach Number of 1.61
- "A supersonic wind-tunnel investigation on store interference has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.61. Forces and moments were measured on a large ogive-cylinder store in the presence of a 45 degree swept-wing-fuselage bomber configuration for a number of store locations below the fuselage center line. Results of the investigation show that large variations of store lift, drag, and pitch occur with changes in store or airplane angle of attack, store vertical location, and store horizontal location" (p. 1).
- Aerodynamic Forces on a Vibrating Unstaggered Cascade
- "The unsteady aerodynamic forces, [based on two-dimensional incompressible flow considerations], are determined for an unstaggered cascade, the blades of which are vibrating in phase in an approach flow parallel to the blades" (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.
- Aerodynamic heating of a thin, unswept, untapered, multiweb, aluminum-alloy wing at Mach numbers up to 2.67 as determined from a free-flight investigation of a rocket-propelled model
- From Introduction: "The heat-transfer data calculated from measured temperatures are compared with values calculated by the theory of Van Driest for a flat plate with laminar and turbulent boundary layers. In addition, the heat-transfer data from the flight tests are compared with data obtained from the Langley Structures Research Division of ground tests of an identical wing at a Mach number approximately equal to 1.99 in the pre-flight jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va. The stream static pressure is maintained at about 1 atmosphere, the free-stream temperature at about 75^o F, and the stagnation temperature at approximately 500 ^o F (ref.1)."
- Aerodynamic interference of slender wing-tail combinations
- From Introduction: "In the present paper, the emphasis is placed on calculating the variations of total forces and moments with angles of attack and sideslip for a number of slender plane and cruciform wing-tail combinations and for some airplane-type arrangements of a plane wing and a horizontal and vertical tail."
- Aerodynamic load distribution over a 45 degree swept wing having a spoiler-slot-deflector aileron and other spoiler ailerons for Mach numbers from 0.60 to 1.03
- Report discussing an investigation of a 45 degree swept-back-wing-body combination with flap spoiler ailerons, deflector ailerons, and a spoiler-slot-deflector aileron. The pressures were measured from Mach numbers 0.60 to 1.03 and at various angles of attack.
- Aerodynamic Loads on Tails at High Angles of Attack and Sideslip
- "Results are presented for the loads and moments acting on the individual tail surfaces of a body-tail combination over a wide range of angles of attack and sideslip. The effects of forebody length and panel-panel interference on the characteristics are included. It is shown that large nonlinear variations in these loads and moments, which occur at some combinations of angle of attack and sideslip, cannot be predicted by low-angle theory" (p. 1).
- Aerodynamic Performance of Several Techniques for Spike-Position Control of a Blunt-Lip Nose Inlet Having Internal Contraction; Mach Numbers of 0.63 and 1.5 to 2.0
- Memorandum presenting a study to determine locations of pressure sensors for controlling the spike position of a blunt-lip, axisymmetric inlet with internal contraction. The inlet performance was determined at Mach numbers of 0.63 and 1.5 to 2.0 for airflow schedules corresponding to those of a given turbojet engine over a wide range of ambient temperatures. The use of the ratio of a throat static pressure to either a local total or the spike-tip total pressure provided a signal that could set nearly maximum pressure recoveries at Mach numbers of 1.7 to 2.0 and within 6 percent of maximum recovery at Mach 1.5.
- 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.
- Age Determinations of the Rocks of the Batholiths of Baja and Southern California, Sierra Nevada, Idaho, and the Coast Range of Washington, British Columbia, and Alaska
- A report about the ages of the four great batholiths in the western United States.
- Aging Characteristics of Hastelloy B
- Report issued by the Oak Ridge National Laboratory discussing the aging characteristics of the alloy Hastelloy B. Materials, equipment, experimental procedures, and results used to determine the characteristics of the alloy are presented. This report includes tables, illustrations, and photographs.
- An Air-Borne Target Simulator for Use With Scope-Presentation Type Fire-Control Systems
- Report describing the design and flight evaluation of an air-borne target simulator using precomputed relative kinematics for use in tracking studies of fighter aircraft equipped with scope-presentation type fire-control systems. Testing occurred in an F86D airplane equipped with a Hughes E-4 fire-control system. Results regarding relative kinematic programming considerations and restrictions to system evaluation are provided.
- 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.
- Airborne radiometric survey of upper Michigan and parts of Wisconsin
- A report regarding an airborne radiometric survey of upper Michigan and Parts of Wisconsin
- Airplane Measurements of Atmospheric Turbulence for Altitudes Between 20,000 and 55,000 Feet Over the Western Part of the United States
- Report presenting a sample of data on atmospheric turbulence on Lockheed U-2 airplanes during research flights. The intensity, amount, and extent of atmospheric turbulence observed in the United States is in good agreement with data from England and Western Europe. Results regarding overall gust distribution, intensity of turbulence, percent of rough air, and size of turbulent areas are provided.
- The Alkaline Method for Treatment of High Radiation Level Aluminum Wastes
- The method is based on caustic precipitation and centrifugation (which removes the Cs and small amounts of Sr, rare earths, Zr, Nb, and Ru). These are removed in the supernatant and run through a cation exchange column. This separates Zr-NB and Ru. The effluent is precipitated and the Zr-Nb is stored in an asphalt pit. The Ru then may be recovered from the precipitate. The precipitate from the original centrifugation is calcined, pressed and transported to a deep well.
- Altitude chamber evaluation of an aircraft liquid hydrogen fuel system used with a turbojet engine
- From Introduction: "The objective of this report are (1) to describe the complete fuel system, (2) to discuss the procedure used for transitions between JP-4 fuel and hydrogen, and (3) to present and discuss engine performance obtained with both fuels, and (4) to review the reliability of the fuel system."
- Altitude Free-Jet Investigation of Dynamics of a 28-Inch-Diameter Ram-Jet Engine
- From Introduction: "The feasibility of closed-loop control of ram-jet-engine thrust is demonstrated in references 1 and 2. The dynamic behavior of a 28-inch-diameter ram-jet engine designed to operate in Mach number range of 2.35 to 2.70 is evaluated herein."
- Altitude performance of a full-scale turbojet engine using pentaborane fuels
- From Introduction: "The data presented herein include the standard engine performance parameters of net thrust, specific fuel consumption, and engine total-pressure ratio that reflect the performance available from the use of pentaborane as a fuel. The influence of the boric oxide deposits from the high-concentration pentaborane fuels on engine component performance is presented."
- Altitude Performance of a Turbojet Engine Using Pentaborane Fuel
- Memorandum presenting a turbojet engine with a two-stage turbine operated with pentaborane fuel continuously for 11.5 minutes at a simulated altitude of 55,000 feet at a flight Mach number of 0.8. The engine incorporated an NACA combustor designed specifically for use with pentaborane fuel. Results regarding oxide formation and deposition, engine operating point, effect of oxide deposits on component performance, effect of oxide deposition on overall performance, and some operational comments are provided.
- Altitude performance of a turbojet engine using pentaborane fuel
- From Summary: "The primary objectives of the investigation reported herein were to determine the effect of this new combuster design on boric oxide deposition on engine parts and to determine the effect of boric oxide on the performance of multistage turbine. Pentaborance fuel (approx. 130 lb) was used in the engine performance evaluation reported herein. The data presented herein show the engine component and over-all performance deterioration with operation on pentaborane fuel".
- 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."
- 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."
- American Standard Recommended Practice for Drainage of Coal Mines (M6.1-1955, UDC 622.5)
- Report discussing standardizations when dealing with pumps for draining and storing water in coal mines.
- An analog computer study of several stability augmentation schemes designed to alleviate roll-induced instability
- From Introduction: "The purpose of the present study is to investigate these suggested methods for reducing the undesirable pitching and yawing motions of an airplane during roll maneuvers. The airplane characteristics used in this study were those of the F-100A airplane having the original small vertical tail as shown in figure 1."
- Analog computer study of some filtering, command-computer, and automatic-pilot problems connected with the attack phase of the automatically controlled supersonic interceptor
- From Summary: "Presented herein are the results of a study of some of the problems associated with the cross-roll filter, command computer, and g-limiter of an automatic interceptor system."
- 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."
- An Analysis of Carry Transmission in Computer Addition
- The following report analyzes carry transformation circuits and their value when approaching the general problem of carry transmission in computer addition.
- Analysis of coolant flow and pressure requirements for a return-flow turbine rotor blade design using hydrogen, helium, or air as coolant
- From Introduction: "This report presents the results of an analysis to determine the coolant flow and pressure requirements for a particular return-flow turbine rooter blade design utilizing hydrogen, helium, or air as the coolant."