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 Collection: National Advisory Committee for Aeronautics Collection
Results 13311 - 13334 of 13,806
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Standardization and aerodynamics

Standardization and aerodynamics

Date: March 1, 1923
Creator: Knight, William; Prandtl, L; VON KARMAN; Costanzi, G; Margoulis, W; Verduzio, R et al.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Variation in the number of revolutions of air propellers

Variation in the number of revolutions of air propellers

Date: March 1, 1923
Creator: Achenbach, W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The air propeller, its strength and correct shape

The air propeller, its strength and correct shape

Date: February 1923
Creator: Dietsius, H
Description: It is possible to give a propeller such a shape that, under given conditions, viz., a definite speed of revolution and flying speed, the bending stresses in the blades will assume quite an insignificant magnitude.
Contributing Partner: UNT Libraries Government Documents Department
"AM" flexible metal joint

"AM" flexible metal joint

Date: February 1923
Creator: unknown
Description: A flexible metal joint used for connecting fuel lines is investigated and methods for assembly are included.
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"AM" gasoline cock.

"AM" gasoline cock.

Date: February 1923
Creator: unknown
Description: The "AM" cock was designed specially for gasoline pipes on vehicles using internal combustion engines (airplanes, airships, automobiles, tractors, battle "tanks", boats, etc.).
Contributing Partner: UNT Libraries Government Documents Department
Determination of climbing ability

Determination of climbing ability

Date: February 1, 1923
Creator: Blasius, H
Description: The vertical distribution of the pressure, temperature, and density of the atmosphere varies from day to day. Thus, rates of climb on different days cannot be compared directly, but must be corrected with reference to a standard rate of diminution of air density with increasing altitude. The following problem, therefore, has to be solved. An airplane has climbed on a certain day under prevailing atmospheric conditions as shown by the barograph. How would the same airplane climb in a standard atmosphere? This problem has already been dealt with by Everling, using the monthly and yearly mean of the vertical temperature distribution. Von Mises solved the problem by arithmetical methods. Here, conditions are examined which shorten or lengthen the climbing time. In establishing the corrected barogram, computation seems more practical than graphical treatment. The basis of the answer to the question answered here is summed up in the remark that lift, drag, propeller thrust, and torque and engine power depend only on the density of the air and do not change with the pressure and temperature, provided that the density remains constant.
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Fixed air-cooled engines

Fixed air-cooled engines

Date: February 1923
Creator: Fedden, A H
Description: It is proposed to analyze the advantages and disadvantages of large fixed air-cooled radial engines and to explain how the problems have been solved by the Bristol Aeroplane Company.
Contributing Partner: UNT Libraries Government Documents Department
Graetzin special carburetor

Graetzin special carburetor

Date: February 1923
Creator: unknown
Description: Corresponding to practical requirements, this carburetor (especially the smaller sizes) may be regarded as the smallest form of a float carburetor and is adapted for use with all small engines, including auxiliary bicycle and similar engines.
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The laboratories of the Technical Section of Aeronautics (Service Technique de L'Aeronautique or S.T.Ae.)

The laboratories of the Technical Section of Aeronautics (Service Technique de L'Aeronautique or S.T.Ae.)

Date: February 1923
Creator: Robert,
Description: An historical sketch of the laboratories of the Technical Section is provided. A breakdown of the different departments and their specialties is also listed.
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Lessons of the 1922 Rhon soaring flights

Lessons of the 1922 Rhon soaring flights

Date: February 1, 1923
Creator: Prandtl, L
Description: Innovations in design and technique from the Rhon soaring contest are presented in this report.
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Longitudinal balancing of airplanes

Longitudinal balancing of airplanes

Date: February 1, 1923
Creator: Eteve, Albert
Description: The object of the present communication is to determine the best method for locating the center of lift of an airplane and to provide a method for making corrections. The method employed is very simple, being based on the positions given the elevator during flights at different speeds.
Contributing Partner: UNT Libraries Government Documents Department
Model supports and their effects on the results of wind tunnel tests

Model supports and their effects on the results of wind tunnel tests

Date: February 1, 1923
Creator: Bacon, David L
Description: The airflow about a model while being tested is often sufficiently affected by the model support to lead to erroneous conclusions unless appropriate corrections are used. In this paper some new material on the subject is presented, together with a review of the airfoil support corrections used in several other laboratories.
Contributing Partner: UNT Libraries Government Documents Department
Rules and regulations of the 1922 Rhoen Soaring Flight Contest

Rules and regulations of the 1922 Rhoen Soaring Flight Contest

Date: February 1923
Creator: unknown
Description: Rules, regulations, announcements and lists of personnel are presented.
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Rules and regulations of the 1922 Rhon Soaring Flight Contest

Rules and regulations of the 1922 Rhon Soaring Flight Contest

Date: February 1, 1923
Creator: unknown
Description: Rules, regulations, announcements and lists of personnel are presented.
Contributing Partner: UNT Libraries Government Documents Department
Soaring without rising currents

Soaring without rising currents

Date: February 1, 1923
Creator: Warner, Edward P
Description: Methods for soaring with fluctuating wind speeds are examined.
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Technical Section of Aeronautics

Technical Section of Aeronautics

Date: February 1923
Creator: Lesage, Andre
Description: The duties of the Technical Section are listed along with facilities for testing. Different categories of tests are discussed and some sample results included.
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Tests on an airplane model, AEG D I of the Allgemeine Elektricitats Gesellschft, A-G, airplane construction section conducted at the Gottingen Model Testing Laboratory for Aerodynamics

Tests on an airplane model, AEG D I of the Allgemeine Elektricitats Gesellschft, A-G, airplane construction section conducted at the Gottingen Model Testing Laboratory for Aerodynamics

Date: February 1, 1923
Creator: Munk, Max & Molthan, Wilhelm
Description: Tests were carried out in the small wind tunnel of the Gottingen establishment on a complete model of the AEG D I airplane. The agreement between the model and the complete airplane applies particularly to the wings, which have ribs cut out of sheet metal and built up in exactly the same manner as in the actual airplane. Various series of tests were carried out with this model in which one or the other of the control surfaces were adjusted to various angles, while the others remained in their neutral positions. During the first three series of tests, the stabilizer was set at a positive angle of 3 degrees, 45' relative to the axis of the engine crankshaft, after which further tests at a 6 degree 30' we made. Finally, the model was tested with the tail group removed. With the elevators set in the prescribed positions, the lift, the drag, and the moments about an axis passing through the center of gravity and perpendicular to the plane of symmetry were measured. All three sets of readings are given as absolute coefficients. Where one of the other control surfaces was deflected from its normal position, the moment produced by that ...
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Absolute dimensions of Karman vortex motion

Absolute dimensions of Karman vortex motion

Date: January 1923
Creator: Heisenberg, Werner
Description: None
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Aerodynamic characteristics of aerofoils II : continuation of report no. 93

Aerodynamic characteristics of aerofoils II : continuation of report no. 93

Date: 1923~
Creator: unknown
Description: This collection of data on aerofoils has been made from the published reports of a number of the leading aerodynamic laboratories of this country and Europe. The information which was originally expressed according to the different customs of the several laboratories is here presented in a uniform series of charts and tables suitable for the use of designing engineers and for purposes of general reference. The absolute system of coefficients has been used, since it is thought by the National Advisory Committee for Aeronautics that this system is the one most suited for international use, and yet is one for which a desired transformation can be easily made. For this purpose a set of transformation constants is included in this report. The authority for the results here presented is given as the name of the laboratory at which the experiments were conducted, with the size of the model, wind velocity, and date of test.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic properties of thick airfoils  II

Aerodynamic properties of thick airfoils II

Date: 1923?~
Creator: Norton, F H & Bacon, D L
Description: This investigation is an extension of NACA report no. 75 for the purpose of studying the effect of various modifications in a given wing section, including changes in thickness, height of lower camber, taper in thickness, and taper in plan form with special reference to the development of thick, efficient airfoils. The method consisted in testing the wings in the NACA 5-foot wind tunnel at speeds up to 50 meters (164 feet) per second while they were being supported on a new type of wire balance. Some of the airfoils developed showed results of great promise. For example, one wing (no. 81) with a thickness in the center of 4.5 times that of the U. S. A. 16 showed both uniformly high efficiency and a higher maximum lift than this excellent section. These thick sections will be especially useful on airplanes with cantilever construction. (author).
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Aeronautic instruments. Section II : altitude instruments

Aeronautic instruments. Section II : altitude instruments

Date: 1923?
Creator: Mears, A. H.; Henrickson, H. B. & Brombacher, W. G.
Description: This report is Section two of a series of reports on aeronautic instruments (Technical Report nos. 125 to 132, inclusive). This section discusses briefly barometric altitude determinations, and describes in detail the principal types of altimeters and barographs used in aeronautics during the recent war. This is followed by a discussion of performance requirements for such instruments and an account of the methods of testing developed by the Bureau of Standards. The report concludes with a brief account of the results of recent investigations. For accurate measurements of altitude, reference must also be made to thermometer readings of atmospheric temperature, since the altitude is not fixed by atmospheric pressure alone. This matter is discussed in connection with barometric altitude determination.
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Aeronautic instruments. Section III : aircraft speed instruments

Aeronautic instruments. Section III : aircraft speed instruments

Date: 1923?
Creator: Hunt, Franklin L. & Stearns, H. O.
Description: Part 1 contains a discussion and description of the various types of air speed measuring instruments. The authors then give general specifications and performance requirements with the results of tests on air speed indicators at the Bureau of Standards. Part 2 reports methods and laboratory apparatus used at the Bureau of Standards to make static tests. Methods are also given of combining wind tunnel tests with static tests. Consideration is also given to free flight tests. Part 3 discusses the problem of finding suitable methods for the purpose of measuring the speed of aircraft relative to the ground.
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Aeronautic instruments. Section IV : direction instruments

Aeronautic instruments. Section IV : direction instruments

Date: 1923?~
Creator: Franklin, W. S.; Stillman, M. H.; Sanford, R. L.; Warner, John A. C.; Sylvander, R. C. & Rounds, E. W.
Description: Part one points out the adequacy of a consideration of the steady state gyroscopic motion as a basis for the discussion of displacements of the gyroscope mounted on an airplane, and develops a simple theory on this basis. Principal types of gyroscopic inclinometers are described and requirements stated. Part two describes a new type of stabilizing gyro mounted on top of a spindle by means of a universal joint, the spindle being kept in a vertical position by supporting it as a pendulum of which the bob is the driving motor. Methods of tests and the difficulties in designing a satisfactory and reliable compass for aircraft use in considered in part three. Part four contains a brief general treatment of the important features of construction of aircraft compasses and description of the principal types used.
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Aeronautic instruments. Section V : power plant instruments

Aeronautic instruments. Section V : power plant instruments

Date: 1923
Creator: Washburn, G. E.; Sylvander, R. C.; Mueller, E. F.; Wilhelm, R. M.; Eaton, H. N. & Warner, John A. C.
Description: Part 1 gives a general discussion of the uses, principles, construction, and operation of airplane tachometers. Detailed description of all available instruments, both foreign and domestic, are given. Part 2 describes methods of tests and effect of various conditions encountered in airplane flight such as change of temperature, vibration, tilting, and reduced air pressure. Part 3 describes the principal types of distance reading thermometers for aircraft engines, including an explanation of the physical principles involved in the functioning of the instruments and proper filling of the bulbs. Performance requirements and testing methods are given and a discussion of the source of error and results of tests. Part 4 gives methods of tests and calibration, also requirements of gauges of this type for the pressure measurement of the air pressure in gasoline tanks and the engine oil pressure on airplanes. Part 5 describes two types of gasoline gauges, the float type and the pressure type. Methods of testing and calibrating gasoline depth gauges are given. The Schroeder, R. A. E., and the Mark II flowmeters are described.
Contributing Partner: UNT Libraries Government Documents Department