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  Partner: UNT Libraries Government Documents Department
 Decade: 1920-1929
Airplane drag

Airplane drag

Date: December 1, 1929
Creator: Topfer, Carl
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.
Contributing Partner: UNT Libraries Government Documents Department
The balance of moments and the static longitudinal stability of airplanes

The balance of moments and the static longitudinal stability of airplanes

Date: December 1, 1929
Creator: Muller, Horst
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.
Contributing Partner: UNT Libraries Government Documents Department
Calculation of the pressures on aircraft engine bearings

Calculation of the pressures on aircraft engine bearings

Date: December 1, 1929
Creator: Steigenberger, O
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.
Contributing Partner: UNT Libraries Government Documents Department
Contribution to the aileron theory

Contribution to the aileron theory

Date: December 1, 1929
Creator: Betz, A & Petersohn, E
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.
Contributing Partner: UNT Libraries Government Documents Department
The Morane Sauliner 222 airplane (French) : a single-seat pursuit monoplane

The Morane Sauliner 222 airplane (French) : a single-seat pursuit monoplane

Date: December 1, 1929
Creator: Frachet, Andre
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some effects of air flow on the penetration and distribution of oil sprays

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

Date: December 1, 1929
Creator: Rothrock, A M & Beardsley, E G
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.
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel pressure distribution tests on a series of biplane wing models Part III : effects of charges in various combinations of stagger, gap, sweepback, and decalage

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

Date: December 1, 1929
Creator: Knight, Montgomery & Noyes, Richard W
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.
Contributing 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

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

Date: November 1, 1929
Creator: Stieger, H J
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.
Contributing Partner: UNT Libraries Government Documents Department
The effect of fuel consumption on cylinder temperatures and performance of a cowled Wright J-5 engine

The effect of fuel consumption on cylinder temperatures and performance of a cowled Wright J-5 engine

Date: November 1, 1929
Creator: Schey, Oscar W
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. A free flow of air past the cylinders is essential for satisfactory operation on a lean mixture. The results of these tests show that the Wright J-5 engine can withstand severe temperatures for short periods of operation. The test results also show to what extent destructive temperatures may be avoided by enriching the mixture.
Contributing Partner: UNT Libraries Government Documents Department
Game laws for the season 1929-1930 : a summary of federal, state and provincial statutes.

Game laws for the season 1929-1930 : a summary of federal, state and provincial statutes.

Date: November 1929
Creator: Earnshaw, Frank L. & Grimes, Frank G.
Description: Describes the laws and regulations regarding hunting and fishing in North America.
Contributing Partner: UNT Libraries Government Documents Department
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