Technical Report Archive and Image Library (TRAIL) - 21,345 Matching Results

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Effect of fluid-system parameters on starting flow
No Description Available.
Effectiveness of Bleeder Entries in Ventilating Pillared Areas of Bituminous-Coal Mines
Report issued by the Bureau of Mines over studies conducted on bleeder application in bituminous coal mines. The methods and results of the studies are presented. This report includes illustrations.
Effects of airplane flexibility on wing strains in rough air at 5,000 feet as determined by flight tests of a large swept-wing airplane
No Description Available.
Equations, tables, and figures for use in the analysis of helium flow at supersonic and hypersonic speeds
No Description Available.
Exploratory investigation of transpiration cooling of a 40 degree double wedge using nitrogen and helium as coolants at stagnation temperatures of 1,295 to 2,910 F
No Description Available.
Impact-loads investigation of a chine-immersed model having a longitudinally curved bow and a v-bottom with a dead-rise angle of 30 degrees
No Description Available.
Impact-loads investigation of chine-immersed model having a circular-arc transverse shape
No Description Available.
Impingement of Cloud Droplets on 36.5-Percent-Thick Joukowski Airfoil at Zero Angle of Attack and Discussion of Use as Cloud Measuring Instrument in Dye-Tracer Technique
The trajectories of droplets i n the air flowing past a 36.5-percent-thick Joukowski airfoil at zero angle of attack were determined. The amount of water i n droplet form impinging on the airfoil, the area of droplet impingement, and the rate of droplet impingement per unit area on the airfoil surface were calculated from the trajectories and cover a large range of flight and atmospheric conditions. With the detailed impingement information available, the 36.5-percent-thick Joukowski airfoil can serve the dual purpose of use as the principal element in instruments for making measurements in clouds and of a basic shape for estimating impingement on a thick streamlined body. Methods and examples are presented for illustrating some limitations when the airfoil is used as the principal element in the dye-tracer technique.
Investigation of the effects of profile shape on the aerodynamic and structural characteristics of thin, two-dimensional airfoils at supersonic speeds
No Description Available.
The mechanism of thermal-gradient mass transfer in the sodium hydroxide-nickel system
No Description Available.
Mining Methods and Costs: La Sal Mining & Development Co., La Sal Uranium Mine, San Juan County, Utah
Report issued by the U.S. Bureau of Mines discussing the costs and methods of uranium mining in San Juan County, Utah. History, geology, and production of the uranium mines are presented. This report includes tables, maps, illustrations, and photographs.
Nuclear Powered Ships for American Ship Operators: a Symposium Held at Washington, D.C., July 30, 1957
It is the intent of this paper to discuss briefly the characteristics and significant naval architectural features of the nuclear powered passenger-cargo ship.
Practical solution of plastic deformation problems in elastic-plastic range
A practical method for solving plastic deformation problems in the elastic-plastic range is presented. The method is one of successive approximations and is illustrated by four examples which include a flat plate with temperature distribution across the width, a thin shell with axial temperature distribution, a solid cylinder with radial temperature distribution, and a rotating disk with radial temperature distribution.
The Principles of Turbulent Heat Transfer
The literature on turbulent heat transfer has in the course of years attained a considerable volume. Since this very complicated problem has not as yet found a complete solution, further studies in this field may be expected. The heat engineer must therefore accomodate himself to a constantly increasing number of theories and formulas. Since the theories generally start from hypothetical assumptions, and since they contain true and false assertions, verified knowledge and pure suppositions often being intermingled in a manner difficult to tell them apart, the specialist had difficulty in forming a correct evaluation of the individual studies. The need therefore arises for a presentation of the problem of turbulent heat transfer which is not initially bound by hypothetical assumptions and in which uninvestigated can be clearly distinguished form each other. Such a presentation will be given in the present treatment. Brief remarks with regard to the development of the theory of local heat transfer are included.
Reduction of oxidized Nichrome V powders and sintering of Nichrome V bodies
No Description Available.
Startup Operation of a Production Facility for Separating Barium-140 from MTR Fuel
Report describing "the startup operation of a batch production facility for separating and purifying barium-140 from short-cooled MTR fuel" (p. 3).
Static longitudinal and lateral stability characteristics at low speed of 45 degree sweptback-midwing models having wings with an aspect ratio of 2, 4, or 6
Results are presented of tests conducted in the Langley stability tunnel to determine the effects of various components and combinations of components on the static longitudinal and lateral stability characteristics at low speed of a series of 45 degree sweptback-midwing-airplane configurations having wings with an aspect ratio of 2, 4, or 6. The tests were made at a dynamic pressure of 24.9 pounds per square foot which corresponds to a Mach number of 0.13 and Reynolds numbers of 1.00 x 10(exp 6), 0.71 x 10 (exp 6), and 0.58 x 10 (exp 6) based on the respective wing mean aerodynamic chords. The angle-of-attack range covered was from -4 degrees to 32 degrees and the sideslip angles used for the lateral-derivative tests were 5 degrees and -5 degrees. An increasing loss in tail contribution to directional stability both with increasing wing aspect ratio and increasing angle of attack was found to be a principal cause of all the complete models becoming directionally unstable in the high angle-of-attack range.
Survey of Fire-Fighting Facilities at Coal Mines
Report issued by the Bureau of Mines over surveys conducted to determine the best fire-fighting technology for coal mines. The equipment, procedures, and cost of the technology were assessed. This report includes tables, maps, and illustrations.
Tensile stress-strain properties of 17-7 PH and AM 350 stainless-steel sheet at elevated temperatures
No Description Available.
Theory of aircraft structural models subject to aerodynamic heating and external loads
No Description Available.
A thermal system for continuous monitoring of laminar and turbulent boundary-layer flows during routine flight
No Description Available.
A thermal system for continuous monitoring of laminar and turbulent boundary-layer flows during routine flight
No Description Available.
Wind-tunnel investigation at low speeds to determine flow-field characteristics and ground influence on a model with jet-augmented flaps
No Description Available.
Wind-tunnel investigation of effects of ground proximity and of split flaps on the lateral stability derivatives of a 60 degree delta-wing model oscillating in yaw
No Description Available.
Wind-tunnel investigation of external-flow jet-augmented double slotted flaps on a rectangular wing at an angle of attack of 0 degree to high momentum coefficients
A wind-tunnel investigation has been made to determine the characteristics of external-flow jet-augmented double slotted flaps which appear suitable for application to airplanes with pod-mounted engines. The investigation included tests of the rectangular wing with an aspect ratio of 6 over a momentum-coefficient range from 0 to 28. Lift coefficients larger than the jet reaction in the lift direction were obtained with the external-flow jet-augmented double slotted flaps.
Homogeneous Reactor Project Quarterly Progress Report: February-April 1957
Report issued by the Oak Ridge National Laboratory discussing quarterly progress of the Homogeneous Reactor Project. Progress of operations, design, development, and analysis is presented. This report includes tables, illustrations, and photographs.
Effect of conical and flat sting-mounted windshields on the zero-lift drag of a flare-stabilized bluff body at Mach numbers from 0.6 to 1.15
No Description Available.
Effect of frequency of sideslipping motion on the lateral stability derivatives of a typical delta wing airplane
No Description Available.
Effect of ground proximity on aerodynamic characteristics of two horizontal-attitude jet vertical-take-off-and-landing airplane models
No Description Available.
Investigation at Mach numbers to 1.04 of blade-loading characteristics of two full-scale three-blade supersonic propellers differing in blade-section camber
No Description Available.
Temperature measurements from a flight test of two wing-body combinations at 7 degree angle of attack for Mach numbers to 4.86 and Reynolds numbers to 19.2 X 10(exp 6)
No Description Available.
Altitude Starting Tests of a 1000-Pound-Thrust Solid-Propellant Rocket
Four solid-propellant rocket engines of nominal 1000-pound-thrust were tested for starting characteristics at pressure altitudes ranging from 112,500 to 123,000 feet and at a temperature of -75 F. All engines ignited and operated successfully. Average chamber pressures ranged from 1060 to ll90 pounds per square inch absolute with action times from 1.51 to 1.64 seconds and ignition delays from 0.070 t o approximately 0.088 second. The chamber pressures and action times were near the specifications, but the ignition delay was almost twice the specified value of 0.040 second.
Standard Practices for Design of MTR and ETR Safety Circuits
Report containing notes for designing safety circuits for the Materials Testing Reactor (MTR) and Engineering Test Reactor (ETR).
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
No Description Available.
Flight investigation of pentaborane fuel in rocket boosted 9.75-inch-diameter ramjet engine with convergent-divergent exhaust nozzle
No Description Available.
Investigation of a 0.6 hub-tip radius-ratio transonic turbine designed for secondary-flow study III : experimental performance with two stator configurations designed to eliminate blade wakes and secondary-flow effects and conclusions from entire sta
No Description Available.
Investigation of a 0.6 Hub-tip Radius-ratio Transonic Turbine Designed for Secondary-flow Study. Iii - Experimental Performance With Two Stator Configurations Designed to Eliminate Blade Wakes and Secondary-flow Effects and Conclusions From Entire Stator Investigation
Hub-tip radius ratio transonic turbine for secondary flow - stator configurations designed to eliminate blade wakes and secondary-flow effects.
Investigation of ejection releases of an MB-1 rocket from a 0.04956-scaled model of the Convair F-106A airplane at several Mach numbers and simulated attitudes : COORD. No. AF-AM-57
No Description Available.
A semiempirical correlation of afterburner combustion efficiency and lean-blowout fuel-air-ratio data with several afterburner-inlet variables and afterburner lengths
No Description Available.
Total-pressure Distortion and Recovery of Supersonic Nose Inlet With Conical Centerbody in Subsonic Icing Conditions
Total-pressure distortion & recovery of supersonic nose inlet with conical afterbody in subsonic icing conditions.
Chemical Processing Instrumentation and Control Research Program
Report regarding the chemical processing instrumentation designs and problems at the Idaho Chemical Processing Plant.
Effect of full-span trailing-edge elevons on the transonic longitudinal aerodynamic characteristics of a wing-body combination having a 3-percent-thick triangular wing with 60 degree leading-edge sweep
No Description Available.
Free-flight investigation of jet effect on the low-lift drag and longitudinal trim of a supersonic interceptor-type airplane configuration with an overhanging tail boom at Mach numbers from 1.09 to 1.34
No Description Available.
A Special Purpose Slide Rule for Computing Solid Angles
Abstract: The design and construction of a slide rule for calculating the solid angle subtended by a rectangle at a point located on a line perpendicular to the center of the rectangle are described.
Wind-tunnel investigation of static lateral and longitudinal stability characteristics of a 1/62-scale model of the X-1E airplane at combined angles of attack and sideslip at supersonic speeds
No Description Available.
Transonic Wind-Tunnel Investigation of Static Longitudinal Stability and Control Characteristics and Drag of a 0.05-Scale Model of the Chance Vought XF8U-3 Airplane : TED No. NACA AD 3133
A transonic wind-tunnel investigation was made in the Langley 8-foot transonic pressure tunnel at the request of the Bureau of Aeronautics, Department of the Navy, of the static longitudinal stability and control characteristics and drag of a 0.05-scale model of the Chance Vought XF8U-3 airplane at Mach numbers from 0.80 to 1.20 with an average Reynolds number of 2.6 x 10(exp 6). The investigation included effects of the addition of the ventral fins, extension and removal of the missiles, deflection of the speed brake, addition of a fuselage fairing near the wing leading edge, and longitudinal control effectiveness. The model was statically stable throughout most of the range of positive lift coefficients, but some loss in horizontal-tail effectiveness may be expected near zero lift and a Mach number of 1.0. Installation of the ventral fins Increased the longitudinal stability from 2 to percent at a small drag-coefficient penalty. The speed-brake drag increment decreased with increasing angle of attack, and trim changes of about 2deg at low angles of attack may be expected at supersonic speeds. The increase in subsonic drag coefficient caused by extension of the three missiles to firing position was more than three times as great as the increase in drag-coefficient rise at supersonic speeds.
Evaluation of hydrogen fuel in a full-scale afterburner
Combustion efficiency of hydrogen fuel for varying afterburner configurations.
Evaluation of hydrogen fuel in a full-scale afterburner
No Description Available.
Comparison of low-lift drag at Mach numbers from 0.74 to 1.37 of rocket-boosted models having externally braced wings and cantilever wings
No Description Available.
Compressibility effects on a hovering helicopter rotor having an NACA 0018 root airfoil tapering to an NACA 0012 tip airfoil
No Description Available.