Technical Report Archive & Image Library (TRAIL) - 13,786 Matching Results

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The 5- by 7-meter wind tunnel of the DVL

Description: The report contains a description of the DVL wind tunnel. According to the cones fixed, an elliptical stream with axes 5 by 7 meters and length 9 meters, or a stream 6 by 8 meters in cross section and 11 meters in length is available. The top speed with the smaller cone is 65 meters per second. The testing equipment consists of an automatic six-component balance and a test rig for propellers and engines up to 650 horsepower.
Date: March 1936
Creator: Kramer, M.
Partner: UNT Libraries Government Documents Department
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The 6-Foot-4-Inch Wind Tunnel at the Washington Navy Yard

Description: Report discussing the 6-foot-4-inch wind tunnel and its auxiliary equipment has proven itself capable of continuous and reliable output of data. The real value of the tunnel will increase as experience is gained in checking the observed tunnel performance against full-scale performance. Such has been the case of the 8- by 8-foot tunnel, and for that reason the comparison in the calibration tests have been presented.
Date: August 1935
Creator: Desmond, G. L. & McCrary, J. A.
Partner: UNT Libraries Government Documents Department
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The 7 by 10 Foot Wind Tunnel of the National Advisory Committee for Aeronautics

Description: This report presents a description of the 7 by 10 foot wind tunnel and associated apparatus of the National Advisory Committee for Aeronautics. Included also are calibration test results and characteristic test data of both static force tests and autorotation tests made in the tunnel.
Date: October 22, 1931
Creator: Harris, Thomas A.
Partner: UNT Libraries Government Documents Department
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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

Description: 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."
Date: February 23, 1950
Creator: Ritchie, Virgil S.; Wright, Ray H. & Tulin, Marshall P.
Partner: UNT Libraries Government Documents Department
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The 300 H.P. Benz Aircraft Engine

Description: This report provides a description of the Benz 300 H.P. aircraft engine containing 12 cylinders placed at a 60° angle. It includes a detailed description of the development of the constructional points, particularly the cylinders, pistons, and connecting rods, as well as the engine fitting, lubrication, oil pumps, bearings, oil tank, fuel pump, carburetors, and cooling system. There are seven pages of illustrative figures at the end of the report.
Date: January 1921
Creator: Heller, A.
Partner: UNT Libraries Government Documents Department
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The 1350 F stress-rupture properties of two wrought alloys and three cast alloys

Description: From Summary: "These properties compare favorably with those of the strongest similar alloys previously investigated. However, compared with a 60Cr-25Fe-15Mo alloy, the three cobalt-chronium-nickel cast alloys are inferior. A correlation of NACA and OSRD (Project NRC-8) data is presented, showing the variation of rupture strengths with temperature in the range of 1350^o to 2000^o for alloys."
Date: November 1947
Creator: Reynolds, E. E.; Freeman, J. W. & White, A. E.
Partner: UNT Libraries Government Documents Department
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The 1926 German Seaplane Contest

Description: The report discusses the problem of rating the various seaplane designs from the 1926 seaplane contest. The whole process of rating consists in measuring the climbing speed, flying weight and carrying capacity of a seaplane and then using these data as the basis of a construction problem.
Date: March 1928
Creator: Seewald, F.; Blenk, H. & Liebers, F.
Partner: UNT Libraries Government Documents Department
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The 1929 Rhon soaring-flight contest

Description: The limitation of the 1929 contest to performance gliders necessitated the establishment of a formula which would make it possible to distinguish between performance gliders and school and training gliders. The sinking speed was therefore adopted as the basis for such a distinction, and the requirement was made that the sinking speed of a performance glider should not exceed 0.8 m/s. The rest of the report details the different entries with regard to design and performance.
Date: April 1930
Creator: Lippisch, Alexander
Partner: UNT Libraries Government Documents Department
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The A. B. Flygindustri "K 37" (Swedish Junkers): A Low-Wing All-Metal Military Airplane

Description: Report discusses the characteristics of the K 37 all-metal long-wing monoplane and its use for long-distance scouting, as a day bomber, and as a heavy fighting airplane. Its engines, climbing capacity, action radius, bombing installation, fuselage, controls, and landing gear are explored in depth.
Date: October 1929
Creator: United States. National Advisory Committee for Aeronautics.
Partner: UNT Libraries Government Documents Department
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N.A.C.A. control position recorder

Description: Report discussing a new instrument is described which is capable of simultaneously recording the position of the three controls of an airplane. The records are taken photographically on a standard N.A.C.A. film drum and the instrument can be quickly installed in any airplane.
Date: May 1922
Creator: Norton, F. H.
Partner: UNT Libraries Government Documents Department
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N.A.C.A. Flight-Path Angle and Air-Speed Recorder

Description: "A new trailing bomb-type instrument for photographically recording the flight-path angle and air speed of aircraft in unaccelerated flight is described. The instrument consists essentially of an inclinometer, air-speed meter and a film-drum case. The inclinometer carries an oil-damped pendulum which records optically the flight-path angle upon a rotating motor-driven film drum. The air-speed meter consists of a taut metal diaphragm of high natural frequency which is acted upon by the pressure … more
Date: April 1926
Creator: Coleman, Donald G.
Partner: UNT Libraries Government Documents Department
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N.A.C.A. Langley field wind tunnel apparatus: The tilting manometer

Description: A description is given of a tilting manometer designed to meet the requirements of a manometer for use in the wind tunnel at the Langley Memorial Aeronautical Laboratory. This gauge was designed to meet the requirements of a manometer in use in connection with a static pressure plate to indicate the wind speed in the tunnel. The requirements are noted. The sensitivity of the gauge must be made inversely proportional to the pressure to be measured. The gauge must be accurately and quickly set fo… more
Date: January 1921
Creator: Norton, F. H. & Bacon, D. L.
Partner: UNT Libraries Government Documents Department
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N.A.C.A. Recording Air Speed Meter

Description: A new type of air speed meter is described which was designed by the technical staff of the National Advisory Committee for Aeronautics. The instrument consists essentially of a tight metal diaphragm of high natural period which is acted upon by the pressure difference of a pitot-static head. The resulting deflection of this diaphragm is recorded optically on a moving film.
Date: October 1921
Creator: Norton, F. H.
Partner: UNT Libraries Government Documents Department
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N.A.C.A. Stall-Warning Device

Description: With some airplanes the approach to the stall is accompanied by changes in the behavior, such as tail buffeting or changes in the control characteristics of the airplane so that the pilot obtains a warning of the impending stall. Vith other airplanes it is possible to approach the stall without any perceptible warning other than the reading of the air-speed meter, in which case the danger of inadvertent stalling is considerably greater. Although it is not within the scope of this paper to discu… more
Date: February 1938
Creator: Thompson, F. L.
Partner: UNT Libraries Government Documents Department
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N.A.C.A. Stall-Warning Indicator

Description: "The stall-warning indicator employs a total-head tube located close to the wing surface in a region wherein local stalling occurs before the main portion of the wing stalls. The artificial production of a localized stalled region is accomplished by means of a sharp leading edge extending a few inches along the span. An abrupt drop in the total pressure relative to a static reference taken at some convenient point occurs at the stall in this region" (p. 1).
Date: October 1938
Creator: Thompson, F. L.
Partner: UNT Libraries Government Documents Department
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The A.N.E.C. IV "Missel Thrush" light airplane

Description: A product of the Air Navigation Engineering Co., the Missel Thrush is a light airplane suitable for private ownership. It is a two seat tractor fuselage biplane with single I interplane struts designed by J. Bewsher.
Date: November 1926
Creator: United States. National Advisory Committee for Aeronautics.
Partner: UNT Libraries Government Documents Department
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Abacus Giving the Variation of the Mean Pressure of an Aviation Engine as a Function of its Speed of Rotation

Description: Comparing the results of the calculations for computing the mean pressure of an aviation engine for any number of revolutions, with those of experiment, the writer, by numerous examples, shows the perfect agreement between them. This report will show that, by means of a special abacus, an engineer can instantly plot the characteristics of an engine.
Date: March 1921
Creator: Margoulis, W.
Partner: UNT Libraries Government Documents Department
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Ability of Pilots to Control Simulated Short-Period Yawing Oscillations

Description: Report discussing an investigation into the ability of human pilots to control short-period yawing oscillations using a yaw simulating device. The ability to control the oscillations was determined to be a function of period, control effectiveness, and inherent damping. Pilot control effectiveness was found to improve with practice.
Date: November 13, 1950
Creator: Phillips, William H. & Cheatham, Donald C.
Partner: UNT Libraries Government Documents Department
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