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20,383 Matching Results
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Motor-Vehicle Headlighting
A report on the necessity of improved motor-vehicle lighting.
Date:
August 5, 1925
Creator:
Carlson, R. E.
System:
The UNT Digital Library
The Armstrong-Whitworth "Argosy": The Latest Three-Engined Commercial Airplane
Describes the utility of multi-engine aircraft with special regard to the Argosy, which will seat up to 20 passengers and who's engines turn out nearly 1200 HP. The Argosy had a top speed of 110 MPH, and a range of 400 miles.
Date:
August 1926
Creator:
unknown
System:
The UNT Digital Library
The characteristics of the N.A.C.A. M-12 airfoil section
The data obtained on the NACA M-12 airfoil, tested at twenty atmosphere density in the NACA variable density wind tunnel, have been extended by additional tests at one and at twenty atmospheres under improved conditions. The results of these tests are given. Considerable scale effect was found.
Date:
August 1926
Creator:
Higgins, George J.
System:
The UNT Digital Library
Designing Seaplane Hulls and Floats
Experimental data, such as the results of tank tests of models, render it possible to predict, at least in principle, as to how a hull or float of a given shape will comport itself. We will see further along, however, how uncertain these methods are and how they leave room for empiricism, which will reign for a long time yet in seaplane research bureaus.
Date:
August 1926
Creator:
Benoit
System:
The UNT Digital Library
Effect of Roughness on Properties of Airfoils
The first group of a large series of contemplated experiments on the effect of roughness was intended to show the effect of great roughness on airfoils of various sizes and attitudes.
Date:
August 1926
Creator:
Schrenk, O.
System:
The UNT Digital Library
Experiments With an Airfoil From Which the Boundary Layer Is Removed by Suction
"Our attempts to improve the properties of airfoils by removing the boundary layer by suction, go back to 1922. The object of the suction is chiefly to prevent the detachment of the boundary layer from the surface of the airfoil. At large angles of attack, such detachment prevents the attainment of the great lift promised by the theory, besides greatly increasing the drag, especially of thick airfoils. This report gives results of those experiments" (p. 1).
Date:
August 1926
Creator:
Ackeret, J.; Betz, A. & Schrenk, O.
System:
The UNT Digital Library
Farman Monoplane F.170: Commercial Airplane with One 500 HP. Farman Engine
The F.170's engine has won world endurance tests in 1924 and in 1925. It has a semi-thick wing, rigidly braced by oblique struts. This wing is embedded in the top of the fuselage and measures 16.1 by 3.6 meters. The F.170 has a passenger compartment seating eight.
Date:
August 1926
Creator:
Serryer, J.
System:
The UNT Digital Library
Heinkel Airplane H.D. 39 for Carrying Newspapers
Circular presenting a description of the Heinkel Airplane H.D. 39, which is a postal airplane that can be used to carry newspapers. Details regarding the design, controls, equipment arrangement, fuel, and flying characteristics are provided.
Date:
August 1926
Creator:
unknown
System:
The UNT Digital Library
Navy Propeller Section Characteristics as Used in Propeller Design
"This report contains artificial aerodynamic characteristics of a set of propeller sections to be used in designing propellers by means of the blade element theory. Characteristics computed from model propeller tests for a single section are extended to cover sections of Navy propeller sections at high Reynolds Number in the variable density tunnel of the NACA" (p. 1).
Date:
August 1926
Creator:
Weick, Fred E.
System:
The UNT Digital Library
Report on Tests of Metal Model Propellers in Combination With a Model VE-7 Airplane
This report, prepared at the request of the NACA, describes tests of three metal model propellers, in a free air stream and in front of a model of a VE-7 airplane. The effect of introducing the model airplane is shown to be an increase in thrust and power coefficients and efficiency at small slip, and a decrease in the same at large slip.
Date:
August 1926
Creator:
Lesley, E. P.
System:
The UNT Digital Library
Tail Planes
This report presents methods by which the cells of large commercial airplanes may be reduced. The tail of large airplanes represent an area where considerable improvement in weight and size reduction can be attained.
Date:
August 1926
Creator:
Constantin, L.
System:
The UNT Digital Library
The Boeing Mail Airplane
The Boeing Mail Airplane is a biplane with cloth covered wings of wood and wire construction, a top speed of 130 MPH, and a fuel capacity of 100 gallons in two tanks.
Date:
August 1927
Creator:
unknown
System:
The UNT Digital Library
Caproni Airplane Ca 73 (Commercial) and Ca 73 ter (Military)
The Caproni 73 is a biplane with medium thick wings, a rigid central section, and with each lateral extension forming a single cell and is powered by two 500 Isotta Fraschini "Asso" Engines.
Date:
August 1927
Creator:
unknown
System:
The UNT Digital Library
Discussion of the results of the boundary-layer tests of an airfoil fitted with a rotary cylinder
The results of the velocity measurements in the boundary layer described in NACA-TM 411 are here discussed in greater detail. The measurements made were of the velocity distribution in the vicinity of an airfoil model fitted with a rotary cylinder and were undertaken for the purpose of obtaining a closer insight into the phenomena observed in experimenting with this model.
Date:
August 1927
Creator:
Wolff, E. B. & Koning, C.
System:
The UNT Digital Library
The Installation and Correction of Compasses in Airplanes
"The saving of time that results from flying across country on compass headings is beginning to be widely recognized. At the same time the general use of steel tube fuselages has made a knowledge of compass correction much more necessary than was the case when wooden fuselages were the rule. This paper has been prepared primarily for the benefit of the pilot who has never studied navigation and who does not desire to go into the subject more deeply than to be able to fly compass courses with confidence" (p. 1).
Date:
August 1927
Creator:
Schoeffel, M. F.
System:
The UNT Digital Library
Junkers Commercial Airplane G 31
The three engine Junkers commercial Airplane, type G 31 is a further development of the earlier G 24. It is an all metal low wing monoplane with a total engine output of 1100-1200 HP.
Date:
August 1927
Creator:
unknown
System:
The UNT Digital Library
"A L C L A D": A New Corrosion Resistant Aluminum Product
Described here is a new corrosion resistant aluminum product which is markedly superior to the present strong alloys. Alclad is a heat-treated aluminum, copper, manganese, magnesium alloy that has the corrosion resistance of pure metal at the surface and the strength of the strong alloy underneath. Of particular importance is the thorough character of the union between the alloy and the pure aluminum.
Date:
August 1927
Creator:
Dix, E. H., Jr.
System:
The UNT Digital Library
"Levasseur 8" Transatlantic Airplane
Circular describing the Levasseur 8, which is an adaptation of a naval airplane adopted by the French Navy. Details of the wings, fuselage, landing gear, fuel, engine, and flying qualities are provided.
Date:
August 1927
Creator:
unknown
System:
The UNT Digital Library
Lindbergh's Flight
Memorandum describing the flights of Charles Lindbergh and some of the calculations that go into the determination of the amount of fuel required, drag, and weight for his trip.
Date:
August 1927
Creator:
Von Parseval, August
System:
The UNT Digital Library
A load factor formula
The ultimate test of a load factor formula is experience. The chief advantages of a semi rational formula over arbitrary factors are that it fairs in between points of experience and it differentiates according to variables within a type. Structural failure of an airplane apparently safe according to the formula would call for a specific change in the formula. The best class of airplanes with which to check a load factor formula seems to be those which have experienced structural failure. Table I comprises a list of the airplanes which have experienced failure in flight traceable to the wing structure. The load factor by formula is observed to be greater than the designed strength in each case, without a single exception. Table II comprises the load factor by formula with the designed strength of a number of well-known service types. The formula indicates that by far the majority of these have ample structural strength. One case considered here in deriving a suitable formula is that of a heavy load carrier of large size and practically no reserve power.
Date:
August 1927
Creator:
Miller, Roy G.
System:
The UNT Digital Library
Recent Suggestions in Diesel-Engine Construction
Different methods for increasing the efficiency of diesel engines are presented and some new designs are given.
Date:
August 1927
Creator:
Bielefeld, F. Ernst
System:
The UNT Digital Library
Seaplanes floats and hulls. Part 1
This part of the report presents characteristics and graphic representations of water resistance. The laws of similarity are discussed as well as the theory of model tests. The test procedures and model tests of other countries are also discussed.
Date:
August 1927
Creator:
Herrmann, H.
System:
The UNT Digital Library
Study of Open Jet Wind Tunnel Cones
"Tests have been made by the National Advisory Committee for Aeronautics on the air flow in an open jet wind tunnel with various sizes, shapes, and spacings of cones, and the flow studied by means of velocity and direction surveys in conjunction with flow pictures. It was found that for all combinations of cones tested the flow is essentially the same, consisting of an inner core of decreasing diameter having uniform velocity and direction, and a boundary layer of more or less turbulent air increasing in thickness with length of jet. The energy ratio of the tunnel was obtained for the different combinations of cones, and the spilling around the exit cone causing undesirable air currents in the experiment chamber was noted" (p. 1).
Date:
August 1927
Creator:
Weick, Fred E.
System:
The UNT Digital Library
Tension experiments on diaphragm metals
Strips of german silver, steel, copper, duralumin, nickel and brass were tested in tension in an apparatus in which the change in deflection with time was measured by means of an interferometer. This change in deflection with time caused by the application and removal of a load is defined as "drift" and "recovery," respectively. It was measured in the time interval from approximately 5 seconds to 5 hours after loading. The data are given in a series of graphs in which the drift and recovery are plotted against time. The proportional drift and recovery in five hours are given for a number of the tests, and in addition are shown graphically for nickel and steel.
Date:
August 1927
Creator:
Henrickson, H. B.
System:
The UNT Digital Library