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The 1934 Contest for the Deutsch De La Meurthe Trophy

Description: This report presents a description of the rules, history and new technical innovations in the Deutsch de la Meurthe Cup race of 1934.
Date: February 1935
Creator: L├ęglise, Pierre
Partner: UNT Libraries Government Documents Department

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 discuss stalling characteristics, it is desired to point out that in general the danger of inadvertent stalling is greatest with those airplanes that behave worse when the stalling occurs; that is, with airplanes in which the stall starts at the wing tips. A warning of the impending stall is desirable in any case, but is particularly desirable with airplanes of the latter type.
Date: February 1938
Creator: Thompson, F. L.
Partner: UNT Libraries Government Documents Department

Accelerations in Landing with a Tricycle-Type Landing Gear

Description: "In connection with the application of stable tricycle-type landing gears to transport airplanes, the question arises as to whether certain passengers may not experience relatively great accelerations in an emergency landing. Since the main landing wheels are behind the center of gravity in this type of gear, a hard-braked landing will cause immediate nosing down of the airplane and, when this motion is stopped due to the front wheel striking the ground, there will be some tendency for the rearmost passengers to be thrown out of their seats, The provided rough calculations are designed to show the magnitudes of the various reactions experienced in a severe landing under these circumstances" (p. 1).
Date: February 1937
Creator: Jones, Robert T.
Partner: UNT Libraries Government Documents Department

The Aerodynamic Aspect of Wing-Fuselage Fillets

Description: Report discussing model tests prove the feasibility of enhancing the aerodynamic qualities of wing-fuselage fillets by appropriate design of fuselage and wing roots. Abrupt changes from maximum fuselage height to wing chord must be avoided and every longitudinal section of fuselage and wing roots must be so faired and arranged as to preserve the original lift distribution of the continuous wing. Adapting the fuselage to the curvilinear circulation of the wing affords further improvement. The polars of such arrangements are almost the same as those of the "wing alone," thus voiding the superiority of the high-wing type airplane known with conventional design.
Date: February 1935
Creator: Muttray, H.
Partner: UNT Libraries Government Documents Department

The Aerodynamic Characteristics of Airfoils at Negative Angles of Attack

Description: From Introduction: "The present report gives all the results, including those published in reference 1 and the results of previously un-published tests tests of the airfoils at positive angles of attack."
Date: February 26, 1932
Creator: Anderson, Raymond F.
Partner: UNT Libraries Government Documents Department

Aerodynamic Characteristics of Anemometer Cups

Description: From Introduction: "The investigation was intended to cover the characteristics of individual cups and of similar cups mounted on complete cup wheals. This report treats the static tests run on the individual cups."
Date: February 1934
Creator: Brevoort, M. J. & Joyner, U. T.
Partner: UNT Libraries Government Documents Department

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

The Aerodynamic Forces and Moments Exerted on a Spinning Model of the NY-1 Airplane as Measured by the Spinning Balance

Description: From Summary: "A preliminary investigation of the effects of changes in the elevator and rudder settings and of small changes in attitude upon the aerodynamic forces and moments exerted upon a spinning airplane was undertaken with the spinning balance in the 5-foot vertical tunnel of the National Advisory Committee for Aeronautics. The tests were made on a 1/12-scale model of the "NY-1" airplane. Data by which to fix the attitude, the radius of spin, and the rotational and air velocities were taken from recorded spins of the full-scale airplane."
Date: February 7, 1933
Creator: Bamber, M. J. & Zimmerman, C. H.
Partner: UNT Libraries Government Documents Department

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 center of gravity at the instant of equilibrium, now exert a moment M(sub G) not equal to 0.
Date: February 1931
Creator: Lapresle, A.
Partner: UNT Libraries Government Documents Department

Airplane Flight in the Stratosphere

Description: This brief survey of the problems encountered in high-altitude flight deals in particular with the need for high lift coefficient in the wings, large aspect ratios in the wings, and also the problem of hermetically sealing the cabin.
Date: February 1932
Creator: de Caria, Ugo
Partner: UNT Libraries Government Documents Department

Annual Report of the Explosives Division, Fiscal Year 1936

Description: Report issued by the U.S. Bureau of Mines on the U.S. Explosives Division, and the chemical and physical testing conducted. The properties of the studies conducted during 1936 are presented. This report includes tables, illustrations, and photographs.
Date: February 1937
Creator: Huff, Wilbert James
Partner: UNT Libraries Government Documents Department

The Avia 51 Commercial Airplane (Czechoslovakian): A Cantilever High-Wing Monoplane

Description: Circular describing the Avia 51 commercial airplane, which is a Czechoslovakian cantilever high-wing monoplane with a fairly orthodox design. Details of the performance, construction, wing, ailerons, fuselage, landing gear, engines, characteristics, drawings, and photographs are provided.
Date: February 1934
Partner: UNT Libraries Government Documents Department

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

The charging process in a high-speed, single-cylinder, four-stroke engine

Description: From Summary: "Experimental measurements and theoretical calculations were made on an aircraft-type, single cylinder engine, in order to determine the physical nature of the inlet process, especially at high piston speeds. The engine was run at speeds from 1,500 to 2,600 r.p.m. (mean piston speeds of 1,370 to 2,380 feet per minute). Measurements were made of the cylinder pressure during the inlet stroke and of the power output and volumetric efficiency. Measurements were also made, with the engine not running, to determine the resistance and mass of air in the inlet valve port at various crank angles. Results of analysis indicate that mass has an appreciable effect, but friction plays the major part in restricting flow. The observed fact that the volumetric efficiency is considerably less than 100 percent is attributed to thermal effects. An estimate was made of the magnitude of these effects in the present case, and their general nature is discussed."
Date: February 1939
Creator: Reynolds, Blake; Schecter, Harry & Taylor, E. S.
Partner: UNT Libraries Government Documents Department

Circular Motion of Bodies of Revolution

Description: The circular motion for airship-like bodies has thus far been calculated only for a prolate ellipsoid of revolution (reference 1, p.133 and reference 2). In this paper, however, the circular motion of elongated bodies of revolution more nearly resembling airships will be investigated. The results will give the effect of rotation on the pressure distribution and thus yield some information as to the stresses set up in an airship in circular flight.
Date: February 1936
Creator: Kaplan, Carl
Partner: UNT Libraries Government Documents Department

Circulation Measurements About the Tip of an Airfoil During Flight Through a Gust

Description: "Measurements were made of the circulation about the rectangular tip of a short-span airfoil passing through an artificial gust of known velocity gradient. A Clark Y airfoil of 30-centimeter chord was mounted on a whirling arm and moved at a velocity of 29 meters per second over a vertical gust with a velocity of nearly 7 meters per second. Flow angles were measured with a hot-wire apparatus" (p. 1).
Date: February 1939
Creator: Kuethe, Arnold M.
Partner: UNT Libraries Government Documents Department

Coal-Mine Fatalities in January, 1931

Description: Report issued by the U.S. Bureau of Mines on the coal mine related deaths during the month of January, 1931. The number of fatalities and their causes are presented. This report includes tables.
Date: February 1931
Creator: Adams, William Waugh & Chenoweth, L.
Partner: UNT Libraries Government Documents Department

Comparative flight performance with an NACA Roots supercharger and a turbocentrifugal supercharger

Description: This report presents the comparative flight results of a roots supercharger and a turbocentrifugal supercharger. The tests were conducted using a modified DH-4M2 airplane. The rate of climb and the high speed in level flight of the airplane were obtained for each supercharger from sea level to the ceiling. The unsupercharged performance with each supercharger mounted in place was also determined. The results of these tests show that the ceiling and rate of climb obtained were nearly the same for each supercharger, but that the high speed obtained with the turbocentrifugal was better than that obtained with the roots. The high-speed performance at 21,000 feet was 122 and 142 miles per hour for the roots and turbocentrifugal, respectively.
Date: February 25, 1930
Creator: Schey, Oscar W. & Young, Alfred W.
Partner: UNT Libraries Government Documents Department

Comparative Performance Obtained With XF7C-1 Airplane Using Several Different Engine Cowlings

Description: Discussed here are problems with the use of cowlings with radial air cooled engines. An XF7C-1 airplane, equipped with service cowling and with narrow ring, wide ring, and exhaust collector ring cowlings over the service cowling, was used. For these four cowling conditions, the rate of climb and high speed performance were determined, the cylinder conditions were measured, and pictures to show visibility were taken. The level flight performance obtained with an engine speed of 1900 r.p.m. for the service type, the narrow ring, the wide ring, and the exhaust collector ring was 144.4, 146.6, 152.8, and 155 mph, respectively.
Date: February 1930
Creator: Schey, Oscar W.; Johnson, Ernest & Gough, Melvin N.
Partner: UNT Libraries Government Documents Department

Comparative Performance of Engines Using a Carburetor, Manifold Injection, and Cylinder Injection

Description: "The comparative performance was determined of engines using three methods of mixing the fuel and the air: the use of a carburetor, manifold injection, and cylinder injection. The tests were made of a single-cylinder engine with a Wright 1820-G air-cooled cylinder. Each method of mixing the fuel and the air was investigated over a range of fuel-air ratios from 0.10 to the limit of stable operation and at engine speeds of 1,500 and 1,900 r.p.m." (p. 1).
Date: February 1939
Creator: Schey, Oscar W. & Clark, J. Denny
Partner: UNT Libraries Government Documents Department

Comparison of Theory With Experiment in the Phenomenon of Wing Flutter

Description: Direct measurements were undertaken at the Aeronautics Laboratory in Turin of the aerodynamic actions on an oscillating wing. The tests conducted had as their essential object the examination of the operation of apparatus designed for this measurement. The values experimentally obtained for the aerodynamic coefficients are in good agreement with the theory of oscillatory motion of the wing of finite span and show clear deviation from the values obtained by theory of plane motion.
Date: February 1939
Creator: Cicala, P.
Partner: UNT Libraries Government Documents Department

The Comper C(La)7 "Swift" Airplane (English): A High-Wing Single-Seat Monoplane

Description: Circular describing the Comper C(La)7 Swift airplane, which is a high-wing single-seat monoplane with performance equal to that of a modern two-seat light airplane. Details of the view, aerodynamic design, wing, landing gear, cockpit, fuel tanks, engine, characteristics, drawings, and photographs are provided.
Date: February 1930
Partner: UNT Libraries Government Documents Department