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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Technical aspects of the 1934 International Touring Competition (Rundflug)
The rules and regulations for the International Touring Competition are presented as well as the technical characteristics that proved advantageous for the successful competitors.
Technical Concept-Operation Bren
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Technical Concept-Operation Henre
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Technical details in the structural development of Rohrbach seaplanes
The recent trial flights and acceptance tests of the Rohrbach "Romar," the largest seaplane in the world, have yielded results fully confirming the principles followed in its development. Its take-off weight of 19,000 kg, its beating the world record for raising the greatest useful load to 2000 m by almost 2500 kg and its remarkable showing in the seaworthiness tests are the results of intelligent researches, the guiding principles of which are briefly set forth in this article.
The technical development of the transport airplane.Report of the Aero-Technical Conference of the Scientific Association for Aeronautics, March 5, 1919
The abolition of military qualifications gives free scope to new technical possibilities in the development of transport airplanes. This report notes the various considerations that must be made when designing aircraft to meet the needs of commercial passengers. Comfort and safety must be emphasized.
Technical preparation of the airplane "Spirit of St. Louis."
Given here is a brief history of the design and construction of the "Spirit of St. Lewis", the airplane that Charles Lindbergh flew solo across the Atlantic. Although the plan was to modify a standard model Ryan M-2, it was quickly determined that modification was less practical than redesign. Colonel Lindbergh's active participation in the design of the aircraft is noted. Given here are the general dimensions, specifications, weight characteristics, and man hours required to build the aircraft.
Technical problems of commercial flying
The technical requirements for commercial aircraft are listed, which include: safety, economy and comfort. The author lists various methods to increase these requirements in commercial aircraft.
Technical progress shown in the 1927 Rhon soaring-flight contest
Since 1922 the further development of the glider has consisted of a very gradual and arduous improvement in regards to air resistance, weight, strength and maneuverability. This report provides an in-depth examination of these improvements.
Technical report of the 1928 Rhon soaring-flight contest
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Technical Section of Aeronautics
The duties of the Technical Section are listed along with facilities for testing. Different categories of tests are discussed and some sample results included.
A technique applicable to the aerodynamic design of inducer-type multistage axial-flow compressors
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A technique utilizing rocket-propelled test vehicles for the measurement of the damping in roll of sting-mounted models and some initial results for delta and unswept tapered wings
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Techniques for calculating parameters of nonlinear dynamic systems from response data
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Techniques for determining thrust in flight for airplanes equipped with afterburners
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Technology and Uses of Silica and Sand
Report discussing the technology for mining silica and the various uses of silica in industry and the arts.
Technology and Uses of Silica and Sand
Report issued by the Bureau of Mines over studies conducted on the production and uses of silica. Forms and different uses for silica are discussed. This report includes tables, illustrations, and photographs.
Technology of Liquid Helium
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The Technology of Marble Quarrying
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Technology of Salt Making in the United States
Report discussing technology for the production of salt in the United States and also the more important sources of salt in the United States.
The Technology of Slate
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Television System Study for Accident Recovery : Phase I
From abstract: "A previous study of equipment necessary for clean-up following a nuclear accident indicated a need for a portable television system capable of operating in hazardous environments during recovery operations. A system to accomplish this is described and justified in this study."
Temperature and pressure distributions in dual parallel jets impinging on the ground from a turbojet engine
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Temperature and thermal-stress distributions in some structural elements heated at a constant rate
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Temperature coefficient of the modulus of rigidity of aircraft instrument diaphragm and spring materials
Experimental data are presented on the variation of the modulus of rigidity in the temperature range -20 to +50 degrees C. of a number of metals which are of possible use for elastic elements for aircraft and other instruments. The methods of the torsional pendulum was used to determine the modulus of rigidity and its temperature coefficient for aluminum, duralumin, monel metal, brass, phosphor bronze, coin silver, nickel silver, three high carbon steels, and three alloy steels. It was observed that tensile stress affected the values of the modulus by amounts of 1 per cent or less.
Temperature-composition limits of spontaneous explosion for nine alkylsilanes with air at atmospheric pressure
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Temperature-control study of turbine region of turbojet engine, including turbine-blade time constants and starting characteristics
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Temperature distribution in internally heated walls of heat exchangers composed of nonnuclear flow passages
In the walls of heat exchangers composed of noncircular passages, the temperature varies in the circumferential direction because of local variations of the heat-transfer coefficients. A prediction of the magnitude of this variation is necessary in order to determine the region of highest temperature and in order to determine the admissible operating temperatures. A method for the determination of these temperature distributions and of the heat-transfer characteristics of a special type of heat exchanger is developed. The heat exchanger is composed of polygonal flow passages and the passage walls are uniformly heated by internal heat sources. The coolant flow within the passages is assumed to be turbulent. The circumferential variation of the local heat-transfer coefficients is estimated from flow measurements made by Nikuradse, postulating similarity between velocity and temperature fields. Calculations of temperature distributions based on these heat-transfer coefficients are carried out and results for heat exchangers with triangular and rectangular passages are presented.
Temperature distribution in internally heated walls of heat exchangers with noncircular flow passages using coolants with very low Prandtl number
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Temperature Distribution in the Crystallization of Undercooled Liquids in Cylindrical Tubes
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Temperature drops through liquid-cooled turbine blades with various cooling-passage geometries
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Temperature Entropy Chart of Thermodynamic Properties of Nitrogen
Report issued by the U.S. Bureau of Mines on the complete revision of the temperature entropy chart developed 25 years prior. The revised chart presented shows the thermodynamic properties of nitrogen.
Temperature-Entropy Diagram for Parahydrogen Triple-Point Region
Graphical presentation of he three-phase region at and near the triple point of parahydrogen.
Temperature gradients in the wing of a high-speed airplane during dives from high altitudes
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Temperature in a J47-25 Turbojet-Engine Combustor and Turbine Sections During Steady-State and Transient Operation in a Sea-Level Test Stand
In order to determine the conditions of engine operation causing the most severe thermal stresses in the hot parts of a turbojet engine, a J47-25 engine was instrumented with thermocouples and operated to obtain engine material temperatures under steady-state and transient conditions. Temperatures measured during rated take-off conditions of nozzle guide vanes downstream of a single combustor differed on the order of 400 degrees F depending on the relation of the blades position to the highest temperature zone of the burner. Under the same operation conditions, measured midspan temperatures in a nozzle guide vane in the highest temperature zone of a combustor wake ranged from approximately 1670 degrees F at leading and trailing edges to 1340 degrees F at midchord on the convex side of the blade. The maximum measured nozzle-guide-vane temperature of 1920degrees at the trailing edge occurred during a rapid acceleration from idle to rated take-off speed following which the tail-pipe gas temperature exceeded maximum allowable temperature by 125 degrees F.
Temperature-indicating paints
This report is an attempt at a new method of coating the surface of the cylinder with materials that undergo chemical change at definite temperatures as indicated by a change in color. In this way it was hoped that the substance itself would indicate directly the position of its isotherms, which in measurements with thermocouples requires a tedious amount of labor.
Temperature-Induced Stresses in Solids of Elementary Shape
Report discussing how solids subjected to non-uniform temperature change develop internal stresses determined by, (1) the temperature distribution within the solid, and (2) certain physical constants of the material. For two varieties of heating, the equations determining stress have been put in convenient form for practical use, and tables of certain temperature functions show how to determine stresses in a slab, in a cylinder, or in a sphere subjected to either of two modes of heating. The temperature-distribution tables independently provide a useful means for the ready estimation of temperature gradients.
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)
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Temperature Measurements in Bessemer and Open-Hearth Practice
Technical paper issued by the Bureau of Standards over studies conducted on different types of furnaces, specifically the Bessemer and the open-hearth furnace. The results of the studies are presented and discussed. This paper includes tables, and illustrations.
The temperature of unheated bodies in a high-speed gas stream
The present report deals with temperature measurements on cylinders of 0.2 to 3 millimeters diameter in longitudinal and transverse air flow at speeds of 100 to 300 meters per second. Within the explored test range, that is, the probable laminar boundary layer region, the temperature of the cylinders in axial flow is practically independent of the speed and in good agreement with Pohlhausen's theoretical values; Whereas, in transverse flow, cylinders of certain diameter manifest a close relationship with speed, the ratio of the temperature above the air of the body to the adiabatic stagnation temperature decreases with rising speed and then rises again from a Mach number of 0.6. The importance of this "specific temperature" of the body for heat-transfer studies at high speed is discussed.
Temperature-pressure-time relations in a closed cryogenic container
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Temperature recording in high-speed gases
The development of suitable thermometer shapes giving the amount of temperature rise if possible without calibration and affording ready repetition is predicated upon a fundamental elucidation of this heating on a number of elementary body forms. This report provides results of tests at subsonic and supersonic velocities.
Temperature recovery factors on a slender 12 degree cone-cylinder at Mach numbers from 3.0 to 6.3 and angles of attack up to 45 degrees
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Temperature response of turbine-blade metal covered with oxide coatings supplied by fuel additives
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Temperature survey of the wake of two closely located parallel jets
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Temperature-Viscosity Relations in the Ternary System CaO-Al₂O₃-SiO₂
Technical paper issued by the Bureau of Mines over studies on the relations of temperature-viscosity. The "observations on the temperature-viscosity relations of silicates" (p. 5) are presented and discussed. This report includes tables, and illustrations.
Temperatures and Stresses on Hollow Blades For Gas Turbines
The present treatise reports on theoretical investigations and test-stand measurements which were carried out in the BMW Flugmotoren GMbH in developing the hollow blade for exhaust gas turbines. As an introduction the temperature variation and the stress on a turbine blade for a gas temperature of 900 degrees and circumferential velocities of 600 meters per second are discussed. The assumptions onthe heat transfer coefficients at the blade profile are supported by tests on an electrically heated blade model. The temperature distribution in the cross section of a blade Is thoroughly investigated and the temperature field determined for a special case. A method for calculation of the thermal stresses in turbine blades for a given temperature distribution is indicated. The effect of the heat radiation on the blade temperature also is dealt with. Test-stand experiments on turbine blades are evaluated, particularly with respect to temperature distribution in the cross section; maximum and minimum temperature in the cross section are ascertained. Finally, the application of the hollow blade for a stationary gas turbine is investigated. Starting from a setup for 550 C gas temperature the improvement of the thermal efficiency and the fuel consumption are considered as well as the increase of the useful power by use of high temperatures. The power required for blade cooling is taken into account.
Temperatures in a J47-25 turbojet-engine turbine section during steady-state and transient operation in an altitude test stand
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Temperatures in Cabs of Freight Locomotives Passing Through Tunnels of the Chesapeake & Ohio Railroad
Report issued by the U.S. Bureau of Mines on experiments conducted to improve the cab conditions of freight engines. The temperature, gas content, and other properties are presented. This report includes tables, graphs, and illustrations.
Temperatures in Spark Plugs Having Steel and Brass Shells
This investigation was conducted at the Bureau of Standards for the National Advisory Committee for Aeronautics. Brass has often been assumed superior to steel for spark plug shells because of its greater heat conductivity. The measurements described in this report prove the contrary, showing that the interior of a spark plug having a brass shell is from 50 degrees to 150 degrees c. (90 degrees to 270 degrees f.) hotter than that of a similar steel plug. Consistent results were obtained in both an aviation and a truck engine, and under conditions which eliminated all other sources of difference between the plugs. It is to be concluded that steel is to be preferred to brass for spark plug shells. This report embodies the results of measurements taken of electrodes and a comparison of brass and steel insulators of spark plugs while they were in actual operation. The data throw considerable light upon the problem of the proper control of temperatures in these parts.
Temperatures, thermal stress, and shock in heat-generating plates of constant conductivity and of conductivity that varies linearly with temperature
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