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Color in Movement

Description: No Description Available.
Access: This item is restricted to UNT Community Members. Login required if off-campus.
Date: ca. 1920
Creator: Matyushin, Mikhail
Partner: UNT College of Visual Arts + Design

Composition

Description: No Description Available.
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Date: ca. 1920
Creator: Popova, Lyubov'
Partner: UNT College of Visual Arts + Design

Construction of USSR

Description: A collage of photographs from the Soviet Union.
Access: This item is restricted to UNT Community Members. Login required if off-campus.
Date: ca. 1920
Creator: Rodchenko, Alexander
Partner: UNT College of Visual Arts + Design

Cote d'Azur

Description: A landscape painting of the French Riviera.
Access: This item is restricted to UNT Community Members. Login required if off-campus.
Date: ca. 1923
Creator: Bonnard, Pierre
Partner: UNT College of Visual Arts + Design

Creole Dance

Description: No Description Available.
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Date: [c.1925]
Creator: Figari, Pedro
Partner: UNT College of Visual Arts + Design

Dead Fowl

Description: No Description Available.
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Date: ca. 1924
Creator: Soutine, Chäim
Partner: UNT College of Visual Arts + Design

Full-scale wind-tunnel tests of a propeller with the diameter changed by cutting off the blade tips

Description: Tests were conducted in order to determine how the characteristics of a propeller are affected by cutting off the tips. The diameter of a standard 10-foot metal propeller was changed successively to 9 feet 6 inches, 9 feet 0 inches, 8 feet 6 inches, and 8 feet 0 inches. Each propeller thus formed was tested at four pitch settings using an open cockpit fuselage and a D-12 engine. A small loss in propulsive efficiency is indicated. Examples are given showing the application of the results to practical problems.
Date: December 10, 1929
Creator: Wood, Donald H.
Partner: UNT Libraries Government Documents Department

Water pressure distribution on a flying boat hull

Description: This is the third in a series of investigations of the water pressures on seaplane floats and hulls, and completes the present program. It consisted of determining the water pressures and accelerations on a Curtiss H-16 flying boat during landing and taxiing maneuvers in smooth and rough water.
Date: December 4, 1929
Creator: Thompson, F. L.
Partner: UNT Libraries Government Documents Department

Airplane Drag

Description: It has been less well understood that the induced drag (or, better said, the undesired increase in the induced drag as compared with the theoretical minimum calculated by Prandtl) plays a decisive role in the process of taking off and therefore in the requisite engine power. This paper seeks to clarify the induced drag.
Date: December 1929
Creator: Töpfer, Carl
Partner: UNT Libraries Government Documents Department

The Balance of Moments and the Static Longitudinal Stability of Airplanes

Description: A nomogram is developed which renders it possible by drawing a few lines, to determine: the location of the center of gravity for zero wing and tail moments; the longitudinal dihedral angle; the tail coefficient F(sub h) iota/F(sub t). Moreover there is no difficulty in determining the magnitude of the restoring moment or of the unstable moment.
Date: December 1929
Creator: Müller, Horst
Partner: UNT Libraries Government Documents Department

Calculation of the Pressures on Aircraft Engine Bearings

Description: For aircraft engines the three principal operating conditions are idling speed, cruising speed, and diving with the engine stopped. In what follows, we will discuss a method which affords a good idea of the course of pressure for the above mentioned operating conditions. The pressures produced in the driving gear are of three kinds; namely, the pressure due to gases, the pressure due to the inertia of the rotating masses, and the pressure due to the inertia of the reciprocating masses.
Date: December 1929
Creator: Steigenberger, O.
Partner: UNT Libraries Government Documents Department

Contribution to the aileron theory

Description: In an attempt to treat theoretically the effect of ailerons, difficulty arises because an aileron may begin at any point of the wing. Hence the question arises as to how the transition of the lift distribution proceeds at such a point, since the effect of the aileron (i.e., the moment generated about the longitudinal axis) depends largely on this distribution. In order to answer this question regarding the lift distribution during irregular variations in the angle of attack at first independently of other influences, especially those of the wing tips, we have taken as the basis of the following theoretical discussion a wing of infinite span and constant chord which exhibits at one point an irregular variation in the angle of attack. As regards the mathematical treatment, we will first consider a wing with periodically recurring angle of attack.
Date: December 1929
Creator: Betz, A. & Petersohn, E.
Partner: UNT Libraries Government Documents Department

Some effects of air flow on the penetration and distribution of oil sprays

Description: Tests were made to determine the effects of air flow on the characteristics of fuel sprays from fuel injection valves. Curves and photographs are presented showing the airflow throughout the chamber and the effects of the air flow on the fuel spray characteristics. It was found that the moving air had little effect on the spray penetration except with the 0.006 inch orifice. The moving air did, however, affect the oil particles on the outside of the spray cone. After spray cut-off, the air flow rapidly distributed the atomized fuel throughout the spray chamber.
Date: December 1929
Creator: Rothrock, A. M. & Beardsley, E. G.
Partner: UNT Libraries Government Documents Department

Wind tunnel pressure distribution tests on a series of biplane wing models Part 3: effects of charges in various combinations of stagger, gap, sweepback, and decalage

Description: A concept for the calculation of the vortex lift of sharp-edge delta wings is presented and compared with experimental data. The concept is based on an analogy between the vortex lift and the leading-edge suction associated with the potential flow about the leading edge. This concept, when combined with potential-flow theory modified to include the nonlinearities associated with the exact boundary condition and the loss of the lift component of the leading-edge suction, provides excellent prediction of the total lift for a wide range of delta wings up to angles of attack of 20 degrees or greater.
Date: December 1929
Creator: Knight, Montgomery & Noyes, Richard W.
Partner: UNT Libraries Government Documents Department

The Design of Plywood Webs for Airplane Wing Beams

Description: This report deals with the design of plywood webs for wooden box beams to obtain maximum strength per unit weight. A method of arriving at the most efficient and economical web thickness, and hence the most suitable unit shear stress, is presented and working stresses in shear for various types of webs and species of plywood are given. The questions of diaphragm spacing and required glue area between the webs and flange are also discussed.
Date: November 27, 1929
Creator: Trayer, George W.
Partner: UNT Libraries Government Documents Department

Cantilever Wings for Modern Aircraft: Some Aspects of Cantilever Wing Construction with Special Reference to Weight and Torsional Stiffness

Description: In the foregoing remarks I have made an attempt to touch on some of the structural problems met with in cantilever wings, and dealt rather fully with a certain type of single-spar construction. The experimental test wing was a first attempt to demonstrate the principles of this departure from orthodox methods. The result was a wing both torsionally stiff and of light weight - lighter than a corresponding biplane construction.
Date: November 1929
Creator: Stieger, H. J.
Partner: UNT Libraries Government Documents Department

The Effect of Fuel Consumption on Cylinder Temperatures and Performance of a Cowled Wright J-5 Engine

Description: Given here are the results of tests made to determine the effect of fuel consumption on the cylinder temperatures and the performance of a cowled Wright J-5 engine. The results of these tests indicate that enriching the mixture by increasing the carburetor size results in a reduction in cylinder head and barrel temperatures. The cylinders shielded by the magnetos or the points on the cylinder that do not receive a free flow of cooling air increase most rapidly in temperature as the mixture is leaned.
Date: November 1929
Creator: Schey, Oscar W.
Partner: UNT Libraries Government Documents Department

Mathematical and Experimental Investigation of Heat Control and Power Increase in Air-Cooled Aircraft Engines

Description: In order to understand the numerical relations between the air velocity, temperature of the cylinder walls, heat dissipation, cylinder dimensions and type of construction an experimental plant was installed in the Siemens and Halske laboratory. The experimental cylinder was exposed to the air stream of a wind tunnel. The compression chamber was heated by an electrically heated oil bath kept constantly in motion by a stirrer. The wall temperatures were measured by thermocouples.
Date: November 1929
Creator: Gosslau, F.
Partner: UNT Libraries Government Documents Department