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Notes on Longitudinal Stability and Balance
Report detailing studies of longitudinal stability and balance on five airplanes: the JN4H, DH4, VE7, USAC-11, and Martin Transport. The methods of measurement, methods of correcting instability, and potential modifications for the elevator of the planes is described.
Date:
April 1920
Creator:
Warner, E. P.
System:
The UNT Digital Library
Abstracts from the German Technical Press: Rates for Flights Organized by the State
Report presenting tariffs that are written for all aircraft manufacturing companies to follow regarding aircraft orders.
Date:
April 1921
Creator:
United States. National Advisory Committee for Aeronautics.
System:
The UNT Digital Library
The Coupling of Engines
This report examines the idea of coupling numerous engines together to turn a single propeller, which the author feels would free aircraft design from the problems of multi-engine and propeller design.
Date:
April 1921
Creator:
Boccaccio, Paul
System:
The UNT Digital Library
Extracts from the German Technical Process. Transport Airplanes.
Report presenting a description of the transition stage of airplanes and how it will change with new developments in aircraft design. The details of the debate between centralized or decentralized installation are also provided, including some of the pros and cons of each.
Date:
April 1921
Creator:
Rohrbach, A. K.
System:
The UNT Digital Library
Gordon Bennett Airplane Cup 1920
The characteristics of the airplanes built for the Gordon Bennett Airplane Cup race that took place on September 28, 1920 are described. The airplanes are discussed from a aerodynamical point of view, with a number of new details concerning the French machines. Also discussed is the regulation of future races. The author argues that there should be no limitations on the power of the aircraft engines. He reasons that in the present state of things, liberty with regard to engine power does not lead to a search for the most powerful engine, but for one which is reliable and light, thus leading to progress.
Date:
April 1921
Creator:
Margoulis, W.
System:
The UNT Digital Library
On the Definition of the Standard Atmosphere
"On April 15, 1920, the under Secretary of State for Aeronautics and Aerial Transport decided to adopt as Standard Atmosphere for official airplane tests in France, the atmosphere defined by the following law, known as the Law of the S.T.You.(Technical Section of Aeronautics): From 0 to 11,000 m. - 0=15-0.0065 Z and above 11,000 m. - 0= -56.5 degrees being the temperature in centigrade degrees at altitude Z expressed in meters. For altitude 0 the pressure is 760 mm of mercury. In the magazine "L'Aeronautique" Mr. A. Toussaint has already written at length on the first studies which led to the elaboration of this law. Since that time the results obtained have been confirmed by fuller and more abundant data which have justified the official adoption of the Law of the S.T.Ae" (p. 1).
Date:
April 1921
Creator:
Grimault, P.
System:
The UNT Digital Library
On the Resistance of the Air at High Speeds and on the Automatic Rotation of Projectiles
Here, the laws governing the flow of a compressible fluid through an opening in a thin wall are applied to the resistance of the air at high speeds, especially as applied to the automatic rotation of projectiles. The instability which we observe in projectiles shot into the air without being given a moment of rotation about their axis of symmetry, or without stabilizing planes, is a phenomenon of automatic rotation. It is noted that we can prevent this phenomenon of automatic rotation by bringing the center of gravity sufficiently near one end, or by fitting the projectile with stabilizing planes or a tail.
Date:
April 1921
Creator:
Riabouchinski, D.
System:
The UNT Digital Library
Recent European Developments in Helicopters
Descriptions are given of two captured helicopters, one driven by electric power, the other by a gasoline engine. An account is given of flight tests of the gasoline powered vehicle. After 15 successful flight tests, the gasoline powered vehicle crashed due to the insufficient thrust. Also discussed here are the applications of helicopters for military observations, for meteorological work, and for carrying radio antennas.
Date:
April 1921
Creator:
unknown
System:
The UNT Digital Library
Resume of the Theory of Naval and Aerial Propulsive Propellers and of Airplanes in the Rectilinear Flight
Though dissimilar, these two subjects have been united because they have some points in common. The computation of the movement of an airplane can only be correctly established if we are in a position to know exactly the thrust and resisting torque of the propeller for the various values of slip, which may vary greatly according to circumstance. The first part of the work concerns propellers and introduces as a fundamental variable, the true slip (delta) with respect to the effective pitch, which is the advance per revolution of the propeller corresponding to no thrust. The second part deals with characteristic curves of an airplane.
Date:
April 1921
Creator:
Rateau, A.
System:
The UNT Digital Library
Similitude tests on wing sections
Report presenting an exploration of the application of model test results to full size construction, which assumes that either the resistance varies as the square of the speed within, the range of speeds in question or that the mechanical similarity law is fulfilled by the model test. The latter requires that the relation of airflow to the model be exactly like that for the large machine.
Date:
April 1921
Creator:
Kumbruch, H. & Bacon, D. L.
System:
The UNT Digital Library
Sixth Meeting of the Members of the German Scientific Association for Aeronautics
Report presenting a description of a meeting of the German Scientific Association for Aeronautics. The topics that were discussed are described.
Date:
April 1921
Creator:
unknown
System:
The UNT Digital Library
Some New Tests at the Gottingen Laboratory
The tests at the Gottingen laboratory included: friction tests on a surface treated with emaillite, verification tests on the M.V.A. 356 wing, and comparative tests of wing no. 36 at the Eiffel laboratory. The examination of all these experiments leads to the belief that, at large incidences, the speeds registered by the suction manometer of the testing chamber of the Eiffel laboratory wind tunnel are, owing to pressure drop, greater than the actual speeds. Therefore, the values of k(sub x) and k(sub y) measured at the Eiffel laboratory at large incidences are too low.
Date:
April 1921
Creator:
unknown
System:
The UNT Digital Library
Study of the Resistance Offered by Propellers Rotating on an Airstream
This report presents a series of tests conducted to verify the formula for thrust P = q(exp 2) D(exp 2) V(exp 2), where P represents thrust, V the velocity of the airstream, D the diameter of the propeller, and q the lifting quality of a comparative propeller which is called the conjugate propeller.
Date:
April 1921
Creator:
Lame, M.
System:
The UNT Digital Library
The Technical Development of the Transport airplane: Report of the Aero-Technical Conference of the Scientific Association for Aeronautics, March 5, 1919
The abolition of military qualifications gives free scope to new technical possibilities in the development of transport airplanes. This report notes the various considerations that must be made when designing aircraft to meet the needs of commercial passengers. Comfort and safety must be emphasized.
Date:
April 1921
Creator:
unknown
System:
The UNT Digital Library
Applying the results of experiments on small models in the wind tunnel to the calculation of full-sized aircraft
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
System:
The UNT Digital Library
The Background of Detonation
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.
System:
The UNT Digital Library
Center of pressure coefficients for airfoils at high speeds
"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.
System:
The UNT Digital Library
Commercial Airplanes and Seaplanes
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
System:
The UNT Digital Library
Distribution of Pressure on Fuselage of Airplane Model: Communication From Rijks-Studiedienst Voor De Luchtvaart of Amsterdam
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
Creator:
unknown
System:
The UNT Digital Library
Evolution of Modern Aviation and Experimental and Technical Researches in Aerodynamic Laboratories
The evolution of construction techniques and the use of metal in wings is presented. Drag is discussed along with the fuselage and tail. The interaction of these parts is also investigated.
Date:
April 1922
Creator:
Toussaint, A.
System:
The UNT Digital Library
Full Scale Determination of the Lift and Drag of a Seaplane
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.
System:
The UNT Digital Library
Influence of Elliptical Distribution of Lift on Strength of Airplane Wings
"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
System:
The UNT Digital Library
Irresponsibility Clause in Air Traffic Contracts
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
System:
The UNT Digital Library
Joukowski Wings
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.
System:
The UNT Digital Library