Technical Report Archive & Image Library (TRAIL) - 380 Matching Results

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Correction of Downwash in Wind Tunnels of Circular and Elliptic Sections

Description: The downwash velocity distribution behind the wing was determined for the free jet and for the closed tunnel of both circular and elliptic cross sections. The wing was placed at the center of the tunnel. The theory makes it possible to determine the downwash at any point in the jet. The computations were performed for points in the plane determined by the jet axis and the center-of-pressure line of the wing.
Date: July 1936
Creator: Lotz, Irmgard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Counter-Propeller

Description: A counter-propeller is a fixed propeller smaller than the main propeller, mounted either fore or aft of the latter and performing the function of changing the direction of motion of the fluid filaments, which naturally tend to adopt a helicoidal form. This paper presents a consideration of the real advantage of counter-propellers on aircraft and the best shape of the blades. First, the author determines the possible energy absorption by the tangential increments. This process will be facilitate… more
Date: October 1930
Creator: de Caria, Ugo
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Critical Shear Load of Rectangular Plates

Description: This report gives formulas for analyzing the critical shear load of a simply supported square, isotropic (simple flat plate), or orthogonal anisotropic plate (a plate in which the rigidity in two directions perpendicular to each other is different, i.e. plywood or corrugated sheet), these formulas, although arrived at by approximation method, seem to agree fairly well with experimental results.
Date: April 1933
Creator: Seydel, Edgar
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The critical velocity of a body towed by a cable from an airplane

Description: It is sufficient to consider only the equations of motion of the towed body whereas those of the cable may be left out of consideration. The result obtained makes it possible to determine which factors affect the critical velocity and what modifications of the instrument are necessary for extending the upper limit of that velocity.
Date: July 1937
Creator: Koning, C. & DeHaas, T. P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The D.V.L. Gliding-Angle Control (W. Hübner Design)

Description: This report describes a device for arbitrary enlargement of the gliding angle of airplanes, especially of such with flat gliding angle and difficult landing characteristics. The D.V.L. gliding angle control (design, Hubner) permits a local interruption of the lift distribution along the span and consequently an increased induced drag. The mechanism comprises two wing rudders operated by lever from the pilot's cockpit. Said rudders are fitted on the top side of the wing near the leading edge. Th… more
Date: January 1933
Creator: Hübner, Walter & Pleines, Wilhelm
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Dangerous Flat Spin and the Factors Affecting It

Description: This report deals first with the fundamental data required for the investigation. These are chiefly the aerodynamic forces and moments acting on an airplane in a flat spin. It is shown that these forces and moments depend principally on the angle of attack and on the rotation about the path axis, and can therefore either be measured in a wind tunnel or calculated from wind-tunnel measurements of lift, drag and moment about the leading edge of the wing of an airplane model at rest.
Date: July 1931
Creator: Fuchs, Richard & Schmidt, Wilhelm
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Dangerous Sideslip of a Stalled Airplane and Its Prevention

Description: This investigation covers only that phase of airplane accidents which are the result of sideslip. We examine the circumstances under which this occurs, study the behavior of present-day airplane types (monoplane, conventional and staggered biplane) therein and endeavor to find a solution whereby this danger may be avoided.
Date: September 1931
Creator: Fuchs, Richard & Schmidt, Wilhelm
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Denis-Gruson Six-Component Wind-Tunnel Balance

Description: The 6.C.1 balance is the first fully automatic balance assuring a continuous and simultaneous record of the aerodynamic characteristics of an airfoil in a wind tunnel. Because of the rapidity of the measurements a complete polar (six components) requires only about three minutes of wind, that is to say, of motive power, which is of interest for wind tunnels with high efficiency factors and may lead to the economical design of large size wind tunnels.
Date: July 1935
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Design of Airplane-Engine Superchargers

Description: Report studying the "underlying principles for the computation and design of airplane engine superchargers" (p. 1). With the forms of superchargers and underlying principles of computation, delivery heads per stage of 7,000 to 8,500 meters (air column) at an effective efficiency, based on the adiabatic process, of 0.7 may be attained, the space and weight requirements being kept within reasonable limits.
Date: October 1937
Creator: von der Nüll, Werner
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Design of Centrifugal Impeller Blades

Description: This paper restricts itself to radial impellers with cylindrical blades since, as Prasil has shown, the flow about an arbitrarily curved surface of revolution may be reduced to this normal form we have chosen by a relatively simple conformal transformation. This method starts from the simple hypotheses of the older centrifugal impeller theory by first assuming an impeller with an infinite number of blades. How the flow is then modified is then investigated.
Date: July 1939
Creator: Betz, A. & Flügge-Lotz, I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The design of floats

Description: Following a summary of the multiplicity of domestic and foreign floats and a brief enumeration of the requirements of floats, the essential form parameters and their effect on the qualities of floats are detailed. On this basis a standard float design is developed which in model families with varying length/beam ratio and angle of dead rise is analyzed by an experimental method which permits its best utilization on any airplane.
Date: April 1938
Creator: Sottorf, W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Details of the Construction and Production of Fuel Pumps and Fuel Nozzles for the Airplane Diesel Engine

Description: This report presents investigations into the design and construction of fuel pumps for diesel engines. The results of the pump tests on the engines showed that, with a good cut-off, accurate injection, assured by the proper adjustment of the pump elements, there is a decrease in the consumption of fuel and hence an increase in the rated power of the engine. Some of the aspects investigated include: cam profile, coefficient of discharge, and characteristics of the injection system.
Date: September 1936
Creator: Lubenetsky, W. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Determination of Inherent Stresses by Measuring Deformations of Drilled Holes

Description: "Various methods have been proposed for determining the inherent stresses in structural components by disturbing their stress equilibrium through a mechanical device and measuring the resulting deformations. The methods used have disadvantages because they can be used only with specially shaped pieces (those with round or rectangular cross sections), that every form of test piece requires another kind of injury and hence of calculation, and the tested parts are rendered useless. The new test me… more
Date: March 1933
Creator: Mathar, Josef
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Determination of Resistance and Trimming Moment of Planing Water Craft

Description: This report presents a new theory which makes it possible to interpret the resistance and the trimming moment for any loading of a planing aircraft when these values are given for one load. This application of the new theory forms the basis of the present paper. Derivations of various conversion formulas are given as well as numerous examples.
Date: May 1931
Creator: Schröder, P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Determination of Stresses and Deformations of Aircraft Propellers

Description: A method is described for testing the strength of propellers of any shape. It is shown that the shape of the propeller greatly affects the stresses, and that great caution must be exercised if the relieving effect of the centrifugal force, which exists in every propeller with a straight blade axis, is to be increased by curving the blade axis. In a numerical example, the calculation is made for a certain revolution speed at which the actual distortion is then measured. The results of the calcul… more
Date: May 1932
Creator: Seewald, Friedrich
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Determination of the Maximum Control Forces and Attainable Quickness in the Operation of Airplane Controls

Description: "This report is intended to furnish bases for load assumptions in the designing of airplane controls. The maximum control forces and quickness of operation are determined. The maximum forces for a strong pilot with normal arrangement of the controls is taken as 1.25 times the mean value obtained from tests with twelve persons. Tests with a number of persons were expected to show the maximum forces that a man of average strength can exert on the control stick in operating the elevator and ailero… more
Date: September 1930
Creator: Hertel, Heinrich
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The development, design and construction of gliders and sailplanes

Description: This report explains and details the history of glider design and construction through the impetus of the Rhon Sailplane contests. Some of the topics considered include: whether the longitudinal stability (dynamic and static) is sufficient in the tailless typo and a consideration that the structural weight of sweptback wings would be greater than that of a corresponding normal wing.
Date: September 1931
Creator: Lippisch, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Development of a Non-Autorotative Airplane Capable of Steep Landing

Description: In the following we develop a non-autorotating monoplane wing. The conditions imposed on such a wing, aside from its freedom from autorotation,with respect to its polars and its construction, are taken into account as far as possible. It is indicated that the autorotation characteristics of a wing are dependent upon the speed of air flow as well as on the angle of yaw. This report postulates the knowledge of the behavior of certain conventional wings of different chords and cambers with respect… more
Date: December 1931
Creator: Schmidt, Wilhelm
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Development of Air-Cooled Engines With Blower Cooling

Description: With the aid of a heating device, the heat transfer to cylinders with conical fins of various forms is determined both for shrouded and exposed cylinders. Simultaneously the pressure drop for overcoming the resistance to the motion of air between the fins of the enclosed cylinder is measured. Thus the relations between the heat transfer and the energy required for cooling are discovered.
Date: October 1933
Creator: Löhner, Kurt
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Development of Floats and Equipment for Research in Promoting It

Description: Providing information that will make possible a favorable compromise between landing impact and planing resistance is the immediate problem in experimental float development. A description of equipment to perform dropping tests are included as well as how to determine the landing impact.
Date: March 1934
Creator: Pabst, Wilhelm
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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