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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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Advantages of Oxide Films as Bases for Aluminum Pigmented Surface Coatings for Aluminum Alloys

Description: Report discussing both laboratory and weather-exposure corrosion tests showed conclusively that the protection afforded by aluminum pigmented spar varnish coatings applied to previously anodized aluminum surfaces was greatly superior to that afforded by the same coatings applied to surfaces which had simply been cleaned free from grease and not anodized.
Date: November 1931
Creator: Buzzard, R. W. & Mutchler, W. H.
Partner: UNT Libraries Government Documents Department
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The aerodynamic characteristics of six commonly used Airfoils over a large range of positive and negative angles of attack

Description: From Summary: "This paper presents the results of tests of six commonly used airfoils: the CYH, the N-22, the C-72, the Boeing 106, and the Gottingen 398. The lifts, drags, and pitching moments of the airfoils were measured through a large range of positive and negative angles of attack. The tests were made in the variable density wind tunnel of the National Advisory Committee for Aeronautics at a large Boeing 106, and the Gottingen 398 airfoils, the negative maximum lift coefficients were foun… more
Date: November 1931
Creator: Anderson, Raymond F.
Partner: UNT Libraries Government Documents Department
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The aerodynamic characteristics of three tapered airfoils tested in the variable density wind tunnel

Description: From Summary: "This report contains the lift, drag, and moment characteristics of tapered Clark Y, Gottingen 393, and USA 45 airfoils as obtained from tests made in the Variable Density Wind Tunnel of the NACA. The results are given at both low and high Reynolds Numbers to show scale effect and to provide data for use in airplane design."
Date: February 1931
Creator: Anderson, Raymond F.
Partner: UNT Libraries Government Documents Department
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The Aerodynamic Wind Vane and the Inherent Stability of Airplanes

Description: Report discussing the design of the wind vane described rests on the following line of reasoning: An airplane, originally in equilibrium about its C.G. is assumed to be deflected from this position through an angle (delta)i, the variation (delta)i being so sudden that the path of the C.G. and the airplane speed do not change while it is taking place. The aerodynamic forces acting on the wings, tail surfaces, fuselage, etc., which, as a whole, exerted a zero moment (M(sub G) = 0) about the cente… more
Date: February 1931
Creator: Lapresle, A.
Partner: UNT Libraries Government Documents Department
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Aeronautical education and research at the Swiss Institute of Technology in Zurich

Description: Progress in the scientific and practical fields of aviation has caused the Swiss Institute of Technology to organize lectures and practical training courses in all three branches of aeronautics and to found centers of scientific research, laboratories, etc., in order to supply the government and industries with scientifically and technically trained engineers.
Date: April 1931
Creator: Karner, L. & Ackeret, J.
Partner: UNT Libraries Government Documents Department
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Airplane Landing Gear

Description: This report presents an investigation of the design and construction of various types of landing gears. Some of the items discussed include: chassises, wheels, shock absorbers (rubber disk and rubber cord), as well as oleopneumatic shock absorbers. Various types of landing gears are also discussed such as the Messier, Bendix, Vickers, and Bleriot.
Date: July 1931
Creator: Maiorca, Salvatore
Partner: UNT Libraries Government Documents Department
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Airship Model Tests in the Variable Density Wind Tunnel

Description: This report presents the results of wind tunnel tests conducted to determine the aerodynamic characteristics of airship models. Eight Goodyear-Zeppelin airship models were tested in the original closed-throat tunnel. After the tunnel was rebuilt with an open throat a new model was tested, and one of the Goodyear-Zeppelin models was retested. The results indicate that much may be done to determine the drag of airships from evaluations of the pressure and skin-frictional drags on models tested at… more
Date: January 27, 1931
Creator: Abbott, Ira H.
Partner: UNT Libraries Government Documents Department
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Annual Report of the National Advisory Committee for Aeronautics (16th). Administrative Report Including Technical Reports Nos. 337 to 364

Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Date: 1931
Partner: UNT Libraries Government Documents Department
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Basic Requirements of Fuel-Injection Nozzles for Quiescent Combustion Chambers

Description: This report presents test results obtained during an investigation of the performance of a single-cylinder, high-speed, compression-ignition test engine when using multiple-orifice fuel-injection valve nozzles in which the number and the direction of the orifices were varied independently.
Date: June 1931
Creator: Spanogle, J. A. & Foster, H. H.
Partner: UNT Libraries Government Documents Department
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The Behavior of Conventional Airplanes in Situations Thought to Lead to Most Crashes

Description: Simple flight tests were made on ten conventional airplanes for the purpose of determining their action in two situations, which are generally thought to precede and lead to a large proportion of airplane crashes. These situations are when in an attempt to stretch the glide in a forced landing, the airplane is stalled, and when while taking off, particularly if taking off steeply, the engine fails at a low altitude.
Date: February 1931
Creator: Weick, Fred E.
Partner: UNT Libraries Government Documents Department
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Breguet 390 T Commercial Airplane (French): A Ten-Seat All-Steel Sesquiplane

Description: Circular presenting a description of the Breguet 390 T, which is a three-engine all-metal transport sesquiplane with the same structural principles as the Breguet military airplane. This aircraft design replaces a girder fuselage with an orthodox rectangular fuselage with accommodations for ten passengers and baggage. Details of the design, components, flying qualities, drawings, and photographs are provided.
Date: August 1931
Partner: UNT Libraries Government Documents Department
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Breguet Military Airplane, Type 33: A Two-Place Long-Distance Sesquiplane for Observation and Bombing

Description: Circular presenting a description of the Breguet military airplane, Type 33, which is a two-place long-distance sesquiplane made for observation and bombing. Details of the components, bomb dropping, flying qualities, design, flying qualities and performances, drawings, and photographs are provided.
Date: September 1931
Partner: UNT Libraries Government Documents Department
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Clerget 100 Hp Heavy-Oil Engine

Description: A complete technical description of the Clerget heavy-oil engine is presented along with the general characteristics. The general characteristics are: 9 cylinders, bore 120 mm, stroke 130 mm, four-stroke cycle engine, rated power limited to 100 hp at 1800 rpm; weight 228 kg; propeller with direct drive and air cooling. Moving parts, engine block, and lubrication are all presented.
Date: January 1931
Creator: Léglise, Pierre
Partner: UNT Libraries Government Documents Department
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Combined Pitching and Yawing Motion of Airplanes

Description: This report treats the following problems: The beginning of the investigated motions is always a setting of the lateral controls, i.e., the rudder or the ailerons. Now, the first interesting question is how the motion would proceed if these settings were kept unchanged for some time; and particularly, what upward motion would set in, how soon, and for how long, since therein lie the dangers of yawing. Two different motions ensue with a high rate of turn and a steep down slope of flight path in … more
Date: May 1931
Creator: v. Baranoff, A. & Hopf, L.
Partner: UNT Libraries Government Documents Department
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Combustion in a High-Speed Compression-Ignition Engine

Description: "An investigation conducted to determine the factors which control the combustion in a high-speed compression-ignition engine is presented. Indicator cards were taken with the Farnboro indicator and analyzed according to the tangent method devised by Schweitzer. The analysis show that in a quiescent combustion chamber increasing the time lag of auto-ignition increases the maximum rate of combustion. Increasing the maximum rate of combustion increases the tendency for detonation to occur" (p. 63… more
Date: May 21, 1931
Creator: Rothrock, A. M.
Partner: UNT Libraries Government Documents Department
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The Comparative Performance of Superchargers

Description: "This report presents a comparison of superchargers on the basis of the power required to compress the air at a definite rate, and on the basis of the net engine power developed at altitudes from 0 to 40,000 feet. The investigation included geared centrifugal, turbine-driven centrifugal, roots, and vane-type superchargers. It also includes a brief discussion of the mechanical limitations of each supercharger and explains how the method of control affects the power requirements" (p. 425).
Date: January 13, 1931
Creator: Schey, Oscar W.
Partner: UNT Libraries Government Documents Department
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A comparison of the aerodynamic characteristics of the normal and three reflexed airfoils in the variable density wind tunnel

Description: "An investigation was made of the aerodynamic effects of reflexing the trailing edge of three commonly used airfoils. Six airfoils were used in the investigation: three having the normal profiles of the Navy 60, the Boeing 106, and the Gottingen 398, and three having these profiles modified to obtain a reflexed trailing edge with the mean camber line changed to give Cmc/4=0. The tests were conducted at a value of the Reynolds Number of approximately 3,100,000 in the variable density wind tunnel… more
Date: August 1931
Creator: DeFoe, George L.
Partner: UNT Libraries Government Documents Department
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