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Performance of B. M. W. 185-horsepower airplane engine

Description: Report discusses the results of testing on a B.M.W. engine in an altitude chamber where temperature and pressure can be controlled to simulate flight at various altitudes. Results for various engine speeds, altitudes, and propeller speeds are provided.
Date: April 13, 1922
Creator: Sparrow, Stanwood Willston
Partner: UNT Libraries Government Documents Department
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Recovery of Gasoline From Uncondensed Still Vapors

Description: Report issued by the U.S. Bureau of Mines on the possibilities of increasing fuel production from crude oil. Methods of recovering oil that is lost by remaining uncondensed are presented. This report includes tables, graphs, and illustrations.
Date: April 1922
Creator: Dow, Donald B.
Partner: UNT Libraries Government Documents Department
open access

Metal Construction

Description: The future development of aerial navigation is closely connected with the condition of obtaining airplanes of great stability and sufficient strength. Different construction materials such as wood, aluminum, iron, and alloys are examined to determine which materials or combination of materials provides a greater coefficient of safety.
Date: April 1922
Creator: Verduzio, Rodolfo
Partner: UNT Libraries Government Documents Department
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Commercial Airplanes and Seaplanes

Description: This report considers as the dominating characteristic, either the load carried, the speed, the radius of action, the fuel consumption, the activity of transport, or, lastly, the qualities of comfort and safety. The first four factors determine the theoretical efficiency, while the others determine its practical efficiency.
Date: April 1922
Creator: Royer, Etienne
Partner: UNT Libraries Government Documents Department
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Testing Airplanes in Flight: Determining Position of Resultant of Action of Air and Longitudinal Stability of an Airplane at Different Angles of Attack

Description: "Measurements made during flight with the triple recording device which gives the horizontal and vertical speeds of an airplane and the angle it makes with the horizon, render it possible to calculate its lift, its drag, and R the resultant of the action of the air both in magnitude and direction, but with these data alone, it is impossible to determine the position of this resultant in the plane of symmetry of the airplane. We will also see how we may determine the position of R during flight … more
Date: April 1922
Creator: Senouque, A.
Partner: UNT Libraries Government Documents Department
open access

Irresponsibility Clause in Air Traffic Contracts

Description: This report examines the question of the responsibility of the carrier in air traffic. The French were concerned about the competitive advantage the English companies enjoyed because of differences in their respective laws.
Date: April 1922
Creator: Porquet
Partner: UNT Libraries Government Documents Department
open access

Wing Resistance Near the Ground

Description: In the present treatise, a convenient method will be indicated, which makes it possible to determine the polar curve of an airplane at short distances from the ground by a simple short calculation, when the polar curve is known for flight in unlimited space.
Date: April 1922
Creator: Wieselsberger, C.
Partner: UNT Libraries Government Documents Department
open access

Joukowski Wings

Description: To sum up, Professor Joukowski's theory of supporting wings renders it possible to calculate the coefficient of lift in terms of the angle of attack, and Prandtl's coefficient of induced drag and the correction of the angle of attack in terms of the disposition and aspect ratio of the wings.
Date: April 1922
Creator: Margoulis, W.
Partner: UNT Libraries Government Documents Department
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Propeller Theory of Professor Joukowski and His Pupils

Description: This report gives a summary of the work done in Russia from 1911 to 1914, by Professor Joukowski and his pupils. This summary will show that these men were the true originators of the theory, which combines the theory of the wing element and of the slipstream.
Date: April 1922
Creator: Margoulis, W.
Partner: UNT Libraries Government Documents Department
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Influence of Elliptical Distribution of Lift on Strength of Airplane Wings

Description: "Hitherto it has been generally assumed, in calculating the fall of an airplane, that the forces withstood by the latter were distributed uniformly throughout the whole length of the wing. In reality this is not the case and German engineers in particular are now assuming an elliptical distribution of the forces. The latter hypothesis has made it possible to carry out a certain number of calculations which have been verified by experiment" (p. 1).
Date: April 1922
Creator: Dorand
Partner: UNT Libraries Government Documents Department
open access

Distribution of Pressure on Fuselage of Airplane Model: Communication From Rijks-Studiedienst Voor De Luchtvaart of Amsterdam

Description: In order to study the distribution of the pressure on the surfaces of a fuselage and the influence of the wing on the air flow along these surfaces, we have made tests pertaining to the bottom and one side. In this particular case, the wing causes an increase in pressure along the sides of the fuselage.
Date: April 1922
Partner: UNT Libraries Government Documents Department
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Applying the results of experiments on small models in the wind tunnel to the calculation of full-sized aircraft

Description: This report presents the attempt to develop a law which will permit the use of results obtained on small models in a tunnel for the calculation of full-sized airplanes, or if it exists, a law of similitude relating air forces on a full-sized plane to those on a reduced scale model.
Date: April 1922
Creator: Robert
Partner: UNT Libraries Government Documents Department
open access

Center of pressure coefficients for airfoils at high speeds

Description: "It has been customary to calculate the strength of the rear wing beam for the 'high speed' condition on the assumption that the center of pressure was at 0.50 of the wing chord. It can be shown that this assumption is not justified, regardless of the utility of a 'high speed' condition in strength calculations" (p. 1).
Date: April 1922
Creator: Diehl, W. S.
Partner: UNT Libraries Government Documents Department
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Full Scale Determination of the Lift and Drag of a Seaplane

Description: The speed, barometric pressure, and number of revolutions of the engine of a seaplane were measured, including tests with stopped engine. The mean data obtained are given in the following note; the results of the gliding tests are used for the computation of the lift and drag coefficients, and by making use of them the results of the engine flights are used for the computation of the propeller efficiency.
Date: April 1922
Creator: Munk, Max M.
Partner: UNT Libraries Government Documents Department
open access

The Background of Detonation

Description: Note presenting a determination of the relative merits of various fuels for use in high compress engines. The main purpose is to discuss a phase that has not been given much attention in previous studies; specifically, the standpoint of the influence of charge temperatures and pressures on the temperatures and pressures after combustion.
Date: April 1922
Creator: Sparrow, Stanwood W.
Partner: UNT Libraries Government Documents Department
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