Technical Report Archive & Image Library (TRAIL) - 383 Matching Results
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- An 8-Foot Axisymmetrical Fixed Nozzle for Subsonic Mach Numbers Up to 0.99 and for a Supersonic Mach Number of 1.2
- From Introduction: "This paper, which should be of interest to those concerned with transonic wind tunnels, covers the design and operating characteristics of the nozzle."
- 1706-KER Coolant Test Facility Operations Manual
- This procedure is intended to be used as: 1. An instruction and guide for operation of the KER loops. 2. To aid in familiarization and understanding of the general operation of the loops. 3. To prevent lost time due to errors in loop operation. The procedure is not meant to be completely comprehensive in all details of loop operation.
- Absolute Cross Sections of the Reaction P + P - w+ + d
- Absolute differential cross sections for the reaction p + p - w+ + d were obtained by detecting meson-deuteron coincidences produced by passing the 340-Mev external proton beam of the Berkeley synchro-cyclotron through a liquid hydrogen target.
- Additional Results in a Free-Flight Investigation of Control Effectiveness of Full-Span, 0.2-Chord Plain Ailerons at High Subsonic, Transonic, and Supersonic Speeds to Determine Some Effects of Wing Sweepback, Aspect Ratio, Taper, and Section Thickness Ratio
- Report discussing an aerodynamic control effectiveness study using free-flight, rocket-propelled test vehicles. Information about the effects of wing sweepback, aspect ratio, taper ratio, and section thickness ratio on the rolling effectiveness of full-span, sealed ailerons is provided.
- Advanced Indirect Cycle Water Reactor Studies for Maritime Applications: Part 3. Analog Simulation of Reactor Plant Transients
- Third part of the "final report of a study directed toward the evolution, design, and demonstration of the principle design features of interim indirect cycle water cooled and moderated nuclear power plants which will be useful in early cooperative programs between the Atomic Energy Commission and the United States maritime industry" (p. i).
- Advanced Indirect Cycle Water Reactor Studies for Maritime Applications: Part 4. Steam Driven Coolant Pumps
- Fourth part of the "final report of a study directed toward the evolution, design, and demonstration of the principle design features of interim indirect cycle water cooled and moderated nuclear power plants which will be useful in early cooperative programs between the Atomic Energy Commission and the United States maritime industry" (p. i).
- Advanced Indirect Cycle Water Reactor Studies for Maritime Applications: Part 5. Spiked Core Concept
- Fifth part of the "final report of a study directed toward the evolution, design, and demonstration of the principle design features of interim indirect cycle water cooled and moderated nuclear power plants which will be useful in early cooperative programs between the Atomic Energy Commission and the United States maritime industry" (p. i).
- Aerial Radiometric and Magnetic Survey: Crystal City National Topographic Map, Texas Gulf Coast, Volume 1
- Final report documenting a high-sensitivity airborne gamma radiation and magnetic field survey of the Texas portions of the Crystal City (NH 14-11 quadrangle) National Topographic Map segment including a description of the program and results.
- 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 High and Low Subsonic Mach Numbers of the NACA 0012, 64₂-015, and 64₃-018 Airfoil Sections at Angles of Attack from -2 Degrees to 30 Degrees
- An investigation has been made in the Langley low-turbulence pressure tunnel of the aerodynamic characteristics of the NACA 0012, 64(sub 2)-015, and 64(sub 3)-018 airfoil sections. Data were obtained at Mach numbers from 0.3 to that for tunnel choke, at angles of attack from -2deg to 30deg, and with the surface. of each airfoil smooth-and with roughness applied at the leading edge.The Reynolds numbers of the tests ranged from 0.8 x 10(exp 6) to 4.4 x 10(exp 6). The results are presented as variations of lift, drag, and quarter-chord pitching-moment coefficients with Mach number.
- The Aerodynamic Characteristics in Pitch of a 1/15-Scale Model of the Grumman F11F-1 Airplane at Mach Numbers of 1.41, 1.61, and 2.01, TED No. NACA DE 390
- "Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 to determine the static longitudinal stability and control characteristics of various arrangements of the Grumman F11F-1 airplane. Tests were made of the complete model and various combinations of its component parts and, in addition, the effects of various body modifications, a revised vertical tail, and wing fences on the longitudinal characteristics were determined" (p. 1).
- Aerodynamic Characteristics of a 42 Degree Swept-Back Wing With Aspect Ratio 4 and NACA 64(Sub 1)-112 Airfoil Sections at Reynolds Numbers From 1,700,000 to 9,500,000
- Report discussing testing on a 42 degree swept-back wing to determine its low-speed aerodynamic characteristics in pitch and yaw at high Reynolds numbers. The main effect of increasing the Reynolds number was delayed wing stalling to higher angles of attack. Roughness on the wing leading edge also had a large adverse effect on lift, drag, and pitching-moment characteristics at higher Reynolds numbers.
- Aerodynamic Characteristics of a Flying-Boat Hull Having a Length-Beam Ratio of 15, TED No. NACA 2206
- "An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of a flying-boat hull of a length-beam ratio of 15 in the presence of a wing. The investigation was an extension of previous tests made on hulls of length-beam ratios of 6, 9, and 12; these hulls were designed to have approximately the same hydrodynamic performance with respect to spray and resistance characteristics. Comparison with the previous investigation at lower length-beam ratios indicated a reduction in minimum drag coefficients of 0.0006 (10 percent) with fixed transition when the length-beam ratio was extended from 12 to 15" (p. 1).
- Aerodynamic Characteristics of Two Delta Wings at Mach Number 4.04 and Correlations of Lift and Minimum-Drag Data for Delta Wings at Mach Numbers From 1.62 to 6.9
- Report presenting tests of the aerodynamic characteristics of two delta wings of the same aspect ratio and airfoil sections at Mach number 4.04. The results indicated that the ratio of the experimental lift-curve slope to the theoretical two-dimensional lift-curve slope from previous testing is valid at this Mach number.
- The Aerodynamic Effects of Rockets and Fuel Tanks Mounted Under the Swept-Back Wing of an Airplane Model
- From Summary: "The effects of externally mounted rockets and fuel tanks on the aerodynamic characteristics of an airplane model with a swept-back wing are presented in this report."
- Aerodynamic Load Measurements Over a Leading-Edge Slat on a 40 Degree Sweptback Wing at Mach Numbers From 0.10 to 0.91
- Report presenting an investigation of the aerodynamic loads on a leading-edge slat on a 40 degree sweptback wing with NACA 64(sub 1)-112 airfoil sections in the low-turbulence pressure tunnel. Results regarding wing force data, slat force data, and slat pressure distributions are provided.
- 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).
- An Airborne Simulator Investigation of the Accuracy of an Optical Track Command Missile Guidance System
- Memorandum presenting an airborne missile simulator used to represent visually the predicted flight behavior of the Navy XASM-N-7 Bullpup air-to-surface missile, which is guided along the line of sight to the target by bang-bang radio signals controlled by the pilot of the launch airplane. Quantitative response measurements showed that the simulator gave a good representation of the trajectory and control characteristics predicted for the Bullpup missile, and the simulation appeared plausible to the pilots.
- Aircraft Nuclear Propulsion Project Quarterly Progress Report for Period Ending June 10, 1952
- This quarterly progress details ongoing research at the Oak Ridge National Laboratory as a part of the Aircraft Nuclear Propulsion Project. Topics discussed include reactor theory and design, [part two is not included], materials research, and appendixes with information on analytical chemical studies.
- 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.
- Alternate Acid Addition Facility for 100-K
- Document HW-33176, "A Proposed Scope of the 100-K Sulfuric Acid Addition Facilities", presented the justification and bases for a sulfuric acid addition facility at the 183-K headhouses and included a system for adding the acid to the raw water. Since the issue of this document several factors to consider in such a system have been brought to light by experience gained both at K and at other areas. The alternate system presented here eliminates several of the troublesome points in the previously proposed system.
- Altitude-chamber performance of British Rolls-Royce Nene II engine 1: standard 18.75-inch-diameter jet nozzle
- Report presenting an altitude-chamber investigation to determine the altitude performance characteristics of the British Rolls-Royce Nene II turbojet engine with a standard 18.75-inch-diameter jet nozzle. Results regarding the simulated flight performance and generalized performance across other altitude and pressure characteristics are provided.
- Altitude evaluation of several afterburner design variables on a J47-GE-17 turbojet engine
- From Introduction: "The investigation reported herein presents information on design factors and modifications of the production afterburner for the J47-GE-17 turbojet engine designed for medium temperature operation. The present report is concerned only with the afterburner performance and operating characteristics.Altitude-starting characteristics of two of the configurations in this report are discussed in reference 1."
- Altitude-ignition limit of a turbojet engine using a condenser-discharge ignition system
- The altitude-ignition limits of a condenser-discharge ignition system installed on a turbojet engine were determined at a flight Mach number of 0.6 using 1.1-pound Reid vapor pressure fuel. Ignition was possible up to an altitude of 55,000 feet with 4.8 joules per spark and 6 sparks per second.
- Altitude-Test-Chamber Investigation of Performance of a 28-Inch Ram-Jet Engine 1: Combustion and Operational Performance of Four Combustion-Chamber Configurations
- An altitude-test-chamber investigation of a 28-inch-diameter ram-jet engine at a simulated flight Mach number of approximately 2.0 for altitudes of 40,000 to 50,000 feet was conducted at the NACA Lewis laboratory. Three different flame holders, varying in the number and size of the annular gutters, in conjunction with several fuel-injection systems were investigated. The combustion efficiency for the flame-holder fuel-injection system that provided the best over-all operational fuel-air-ratio range (0.03 to 0.075) was over 0.9 at a fuel-air ratio of about 0.065 for the altitude range investigated.
- Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine 1 - Analysis of Turbine Performance
- A wind tunnel investigation was conducted to determine the performance of a turbine operating as an integral part of a turbojet engine. Data was obtained while the engine was running over full operable range of speeds at various altitudes and flight mach numbers, and with four nozzles of different outlet areas.A maximum turbine efficiency of 0.875 was obtained at altitude of 15 thousand feet, Mach number 0.53, and corrected turbine speed of 5900 rpm.
- Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine 2 - Analysis of Compressor Performance
- Compressor performance properties for two 11-stage compressors of 3000-pound-thrust axial-flow turbojet engines were determined. Data are presented for a range of simulated altitudes and a range of Mach numbers for various modifications of the engine.
- Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine 3 - Analysis of Combustion-Chamber Performance
- Combustion chamber performance properties of a 3000-pound-thrust axial-flow turbojet engine were determined. Data are presented for a range of simulated altitudes from 15,000 to 45,0000 feet and a range of Mach numbers from 0.23 to 1.05 for various modifications of the engine.
- Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, 4, Operational Characteristics
- An investigation was conducted to evaluate the operational characteristics of a 3000 pound thrust axial flow turbojet engine over a range of simulated altitudes from 2000 to 50,000 feet and simulated flight Mach numbers from 0 to 1.04 throughout the operable range of engine speeds. Engine operating range, acceleration, deceleration, starting, altitude, and flight Mach number compensation of the fuel control system, and operation of the lubrication system at high and low ambient air temperatures were evaluated.
- Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, Part 5, Performance and Windmilling Drag Characteristics
- "An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the performance and windmilling drag characteristics of an original and a modified turbojet engine of the same type. Data have been obtained at simulated altitudes from 5000 to 45,000 feet, simulated flight Mach numbers from 0.09 to 1.08, and engine speeds from 4000 to 12,500 rpm. Engine performance data are presented for both engines to show the effects of altitude at a flight Mach number of 0.25 and of flight Mach number at an altitude of 25,000 feet" (p. 1).
- Altitude-wind-tunnel investigation of operational characteristics of Westinghouse X24C-4B axial flow turbojet engine
- From Summary: "An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the operational characteristics of a 3000-pound-thrust axial-flow turbojet engine over a range of simulated altitudes from 2000 to 50,000 feet and simulated flight Mach numbers from 0 to 1.04 throughout the operable range of engine speeds. Operational characteristics investigated include engine operating range, acceleration, deceleration, starting, altitude and flight-Mach-number compensation of the fuel-control system, and operation of the lubrication system at high and low ambient-air temperatures."
- Aluminum borohydride - hydrocarbon mixtures as a source of ignition for a turbojet combustor
- From Introduction: "Data on the extent of decomposition of a sample of aluminum borohy-dride during long-term storage are presented."
- Analysis of efficiency characteristics of a single-stage turbine with downstream stators in terms of work and speed requirements
- One-dimensional mean-section flow and blade specific losses proportional to average specific kinetic energy are assumed in the analysis. Range of the work-speed parameter lambda considered includes low to moderate blade speeds with high specific work outputs, where critical turbojet, turbopump, and accessory-drive turbines are encountered. A diffusion factor of 0.5 limits the loading on the downstream stators. Turbine efficiences considered are total or aerodynamic, rating, and static. Efficiences of velocity-diagram types at impulse and that corresponding to values of maximum efficiency are presented and compared to indicate in what range of lambda downstream stators are beneficial as well as the attending improvements in efficiency.
- Analysis of Flight-Determined and Predicted Effects of Flexibility on the Steady-State Wing Loads of the B-52 Airplane
- Memorandum presenting an investigation of the steady-state wing loads conducted on a Boeing B-52 airplane over a range of Mach numbers and altitudes. Results regarding flight tests and air-load calculations are provided.
- Analysis of flight-determined and predicted effects of flexibility on the steady-state wing loads of the B-52 airplane
- From Introduction: "This paper presents the results obtained during the phase of the B-52 flight investigation concerned with the steady-state wing loads. Where possible, the effects of Mach number and flexibility on the measured load are analyzed and presented."
- The Analysis of Impurities in Various Stages of Recycled Carbon Tetrachloride and Correlation with Chlorination Properties
- The following report discusses findings resulting from experiments on recycled carbon tetrachloride at various stages of the proposed purification process.
- Analysis of Wing Loads on a Flexible Swept-Wing Jet Bomber During Push-Pull Maneuvers
- Report presenting measurements of the loads of the wing of a Boeing B-47A medium bomber using strain-gage instrumentation during 23 symmetrical push-pull maneuvers at a variety of altitudes, Mach numbers, and gross weights. Time histories of aerodynamic shear, bending moment, and torque at each of four spanwise stations on the left wing and one on the right wing were created. Based on the results, presently available methods seem to be capable of predicting additional and basic loads accurately within the range of flight conditions in the test.
- Apparatus for obtaining a supersonic flow of very short duration and some drag measurements obtained with its use
- From Introduction: "The auxiliary apparatus described in this paper was constructed to meet this need and has been developed to a point where satisfactory measurements of relative drag can be obtained. In this paper, the apparatus is described and some comparisons are made between the results obtained with this apparatus and the measurements of free-fall, rocket, and supersonic-tunnel techniques."
- Application of statistical theory to beam-rider guidance in the presence of noise 1: Wiener filter theory
- Report presenting a study of the application of Wiener filter theory to the design of a beam-rider guidance system operating in the presence of glint noise. The theory is then used to establish the theoretical lower limit of root-mean-square error and the corresponding desired transfer-function characteristics.
- The Application of Tracer Techniques to the Determination of Uranium Extraction Coefficients
- Abstract: This report deals with the development of a method using tracer technique for determining uranium extraction coefficients on solutions of low uranium concentration. It was found that extraction coefficients could be determined on systems containing as low as one part per million uranium using 1900 level uranium as the tracer. Results of several extraction series are presented in which aluminum nitrate is used as the salting agent and dibutyl carbitol the organic extractant.
- An approximate method for calculating the effect of surface roughness on the drag of an airplane
- From Summary: "A method for computing the effect of surface roughness on the drag coefficient of an airplane is presented. Calculated results using this method are compared with experimental results from both flight and wind-tunnel tests. In general, the agreement is believed satisfactory."
- Assembly of Fifty Prototype Fuel Elements for the Experimental Gas-Cooled Reactor
- Report that describes the Oak Ridge National Laboratory Experimental Gas-Cooled Reactor, problems with the procurement and assembly of its components, and its economic feasibility.
- Automatic Mass Spectrometer for Monitoring Uranium Isotope Concentrations
- Abstract: An automatic recording mass spectrometer has been designed; two instruments have been constructed and have operated reliably for more than seven years as process monitors.
- Axial-Flow Compressor Rotating-Stall and Rotor-Blade Vibration Survey
- Report presenting a compressor-rotor-blade vibration survey on a production turbojet engine incorporating a 13-stage axial-flow compressor with a pressure ratio of approximately 7 and an air flow of 120 pounds per second. The investigation was conducted due to the major problem that fatigue failures of compressor rotor blades have caused in the development of the axial-flow compressor. Results regarding rotating stall characteristics, rotor-blade vibration, and fourth-stage rotor-blade failure are provided.
- A Biological Reconnaissance of the Base of the Alaska Peninsula
- General account with outline of route and life zones, and lists of mammals and birds.
- Boron Isotope Enrichment: Pilot Plant Proposal for the Anisole - BF₃ System
- From abstract: This proposal for a 6"D column plant is based on laboratory and pilot plant work done at Oak Ridge and at Model City.
- A Brief Course in Radiation Dosimetry and its Application to Personnel Protection
- By radiation dosimetry, we will mean the determination of the energy deposited per unit mass of irradiated material by ionizing radiation. Usually the material of interest in tissue and the results are to be applied to a radiobiological experiment, a radiotherapy treatment, or the protection of personnel from radiation hazards. The same methods, however, are applied to such engineering problems as the production of heat by reactor radiations, the use of radiation in chemical reactions or food processing, etc.
- The Brookhaven Chemonuclear in-Pile Test Loop
- Technical report outlining the plan to develop the Brookhaven chemonuclear in-pile test loop because the interest in utilizing reactor radiation energy (fission-fragment recoil and neutron-gamma) for production of chemicals has developed to the point where a loop to study chemonuclear system in a reactor under dynamic conditions is necessary.
- The calculation of drag for airfoil sections and bodies of revolution at subcritical speeds
- Report presenting a method for calculating the drag, in a real compressible fluid and at subcritical Mach numbers, of airfoil sections at arbitrary life coefficients and of bodies of revolution at zero angle of attack. The values of drag coefficient are compared with values obtained for the same configurations by other methods. The differences between the results are found to lie withint he limits of accuracy of current experimental techniques.
- Calculation of the Aerodynamic Characteristics of Tapered Wings With Partial-Span Flaps
- "Factors derived from wing theory are presented. By means of these factors, the angle of zero lift, the lift-curve slope, the pitching moment, the aerodynamic-center position, and the induced drag of tapered wings with partial-span flaps may be calculated. The factors are given for wings of aspect ratios 6 and 10 , of taper ratios from 0.25 to 1.00, and with flaps of various length. An example is presented of the method of application of the factors. Fair agreement with experimental results is shown for two wings of different taper ratio having plain flaps of various spacing" (p. 1).