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  Partner: UNT Libraries Government Documents Department
 Decade: 1920-1929
 Collection: National Advisory Committee for Aeronautics Collection
Abacus giving the variation of the mean pressure of an aviation engine as a function of its speed of rotation

Abacus giving the variation of the mean pressure of an aviation engine as a function of its speed of rotation

Date: March 1921
Creator: Margoulis, W
Description: Comparing the results of the calculations for computing the mean pressure of an aviation engine for any number of revolutions, with those of experiment, the writer, by numerous examples, shows the perfect agreement between them. This report will show that, by means of a special abacus, an engineer can instantly plot the characteristics of an engine.
Contributing Partner: UNT Libraries Government Documents Department
Absolute coefficients and the graphical representation of airfoil characteristics

Absolute coefficients and the graphical representation of airfoil characteristics

Date: June 1921
Creator: Munk, Max
Description: It is argued that there should be an agreement as to what conventions to use in determining absolute coefficients used in aeronautics and in how to plot those coefficients. Of particular importance are the absolute coefficients of lift and drag. The author argues for the use of the German method over the kind in common use in the United States and England, and for the Continental over the usual American and British method of graphically representing the characteristics of an airfoil. The author notes that, on the whole, it appears that the use of natural absolute coefficients in a polar diagram is the logical method for presentation of airfoil characteristics, and that serious consideration should be given to the advisability of adopting this method in all countries, in order to advance uniformity and accuracy in the science of aeronautics.
Contributing Partner: UNT Libraries Government Documents Department
Absolute dimensions of Karman vortex motion

Absolute dimensions of Karman vortex motion

Date: January 1923
Creator: Heisenberg, Werner
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Absorbing landing shocks

Absorbing landing shocks

Date: August 1923
Creator: Warner, Edward P
Description: Tires, steel springs, hydraulic shock absorbers, and axle travel are all examined in relation to absorbing landing shocks.
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Accelerations in flight

Accelerations in flight

Date: 1925
Creator: Doolittle, J H
Description: This work on accelerometry was done at McCook Field for the purpose of continuing the work done by other investigators and obtaining the accelerations which occur when a high-speed pursuit airplane is subjected to the more common maneuvers. The accelerations obtained in suddenly pulling out of a dive with well-balanced elevators are shown to be within 3 or 4 per cent of the theoretically possible accelerations. The maximum acceleration which a pilot can withstand depends upon the length of time the acceleration is continued. It is shown that he experiences no difficulty under the instantaneous accelerations as high as 7.8 G., but when under accelerations in excess of 4.5 G., continued for several seconds, he quickly loses his faculties.
Contributing Partner: UNT Libraries Government Documents Department
Accelerations in flight

Accelerations in flight

Date: 1921
Creator: Norton, F H & Allen, E T
Description: This report deals with the accelerations obtained in flight on various airplanes at Langley Field for the purpose of obtaining the magnitude of the load factors in flight and to procure information on the behavior of an airplane in various maneuvers. The instrument used in these tests was a recording accelerometer of a new type designed by the technical staff of the National Advisory Committee for Aeronautics. The instrument consists of a flat steel spring supported rigidly at one end so that the free end may be deflected by its own weight from its neutral position by any acceleration acting at right angles to the plane of the spring. This deflection is measured by a very light tilting mirror caused to rotate by the deflection of the spring, which reflected the beam of light onto a moving film. The motion of the spring is damped by a thin aluminum vane which rotates with the spring between the poles of an electric magnet. Records were taken on landings and takeoffs, in loops, spins, spirals, and rolls.
Contributing Partner: UNT Libraries Government Documents Department
Accelerometer design

Accelerometer design

Date: 1921?~
Creator: Norton, F H & Warner, Edward P
Description: In connection with the development of an accelerometer for measuring the loads on airplanes in free flight a study of the theory of such instruments has been made, and the results of this study are summarized in this report. A portion of the analysis deals particularly with the sources of error and with the limitations placed on the location of the instrument in the airplane. The discussion of the dynamics of the accelerometer includes a study of its theoretical motions and of the way in which they are affected by the natural period of vibration and by the damping, together with a report of some experiments on the effect of forced vibrations on the record.
Contributing Partner: UNT Libraries Government Documents Department
Adaptation of aeronautical engines to high altitude flying

Adaptation of aeronautical engines to high altitude flying

Date: May 1923
Creator: Kutzbach, K
Description: Issues and techniques relative to the adaptation of aircraft engines to high altitude flight are discussed. Covered here are the limits of engine output, modifications and characteristics of high altitude engines, the influence of air density on the proportions of fuel mixtures, methods of varying the proportions of fuel mixtures, the automatic prevention of fuel waste, and the design and application of air pressure regulators to high altitude flying. Summary: 1. Limits of engine output. 2. High altitude engines. 3. Influence of air density on proportions of mixture. 4. Methods of varying proportions of mixture. 5. Automatic prevention of fuel waste. 6. Design and application of air pressure regulators to high altitude flying.
Contributing Partner: UNT Libraries Government Documents Department
Aerial convention of October 13, 1919

Aerial convention of October 13, 1919

Date: May 1922
Creator: Roper,
Description: The aerial convention delegates are listed as well as the set of rules that were developed during the session.
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Aerial navigation by dead reckoning

Aerial navigation by dead reckoning

Date: July 1922
Creator: Maffert, Pierre
Description: The problem to be solved, as presented to the pilot or observer of an aircraft, is as follows: The aircraft starting from A must land at B, the only data being the speed of the airplane, the altitude and the orientation D of the course. The above data would be amply sufficient, were it not for the fact that the airplane is constantly subjected to a wind of variable direction and strength.
Contributing Partner: UNT Libraries Government Documents Department
Aerial navigation : on the problem of guiding aircraft in a fog or by night when there is no visibility

Aerial navigation : on the problem of guiding aircraft in a fog or by night when there is no visibility

Date: January 1922
Creator: Loth, William
Description: The use of magnetic fields and wire to navigate aircraft in conditions of poor visibility is presented. This field may be considered to be derived from a double lemniscate, considered in the particular case where the origin is a double point formed from the magnetic field of the slack wire, from the field produced by the return currents and from the field due to the currents induced in the conducting mass. These fields are dephased in two ways, one in the direction of the wire, the other in a direction perpendicular to it.
Contributing Partner: UNT Libraries Government Documents Department
Aerial photography : obtaining a true perspective

Aerial photography : obtaining a true perspective

Date: April 1923
Creator: unknown
Description: A demonstration was given within the last few days at the British Museum by Mr. J. W. Gordon, author of "Generalized Linear Perspective" (Constable and Co.), a work describing a newly-worked-out system by which photographs can be made available for the purpose of exactly recording the dimensions of the objects photographed even when the objects themselves are presented foreshortened in the photograph.
Contributing Partner: UNT Libraries Government Documents Department
Aerial transportation

Aerial transportation

Date: February 1922
Creator: PIERROT
Description: The origin of air traffic dates from the war. The important development of aeronautic industries and the progress made in recent years, under the impelling force of circumstances, rendered it possible, after the close of hostilities, to consider the practical utilization of this new means of economic expansion.
Contributing Partner: UNT Libraries Government Documents Department
Aero dopes and varnishes

Aero dopes and varnishes

Date: July 1927
Creator: Britton, H T S
Description: Before proceeding to discuss the preparation of dope solutions, it will be necessary to consider some of the essential properties which should be possessed of a dope film, deposited in and on the surface of an aero fabric. The first is that it should tighten the material and second it should withstand weathering.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of aerofoils I

Aerodynamic characteristics of aerofoils I

Date: 1921~
Creator: unknown
Description: The object of this report is to bring together the investigations of the various aerodynamic laboratories in this country and Europe upon the subject of aerofoils suitable for use as lifting or control surfaces on aircraft. The data have been so arranged as to be of most use to designing engineers and for the 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.
Contributing Partner: UNT Libraries Government Documents Department
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 characteristics of aircraft with reference to their use

Aerodynamic characteristics of aircraft with reference to their use

Date: 1925
Creator: Panetti, M
Description: Economic and design characteristics are examined in the design of airplanes and airships.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of airfoils at high speeds

Aerodynamic characteristics of airfoils at high speeds

Date: 1925~
Creator: Briggs, L. J.; Hull, G. F. & Dryden, H. L.
Description: This report deals with an experimental investigation of the aerodynamical characteristics of airfoils at high speeds. Lift, drag, and center of pressure measurements were made on six airfoils of the type used by the air service in propeller design, at speeds ranging from 550 to 1,000 feet per second. The results show a definite limit to the speed at which airfoils may efficiently be used to produce lift, the lift coefficient decreasing and the drag coefficient increasing as the speed approaches the speed of sound. The change in lift coefficient is large for thick airfoil sections (camber ratio 0.14 to 0.20) and for high angles of attack. The change is not marked for thin sections (camber ratio 0.10) at low angles of attack, for the speed range employed. At high speeds the center of pressure moves back toward the trailing edge of the airfoil as the speed increases. The results indicate that the use of tip speeds approaching the speed of sound for propellers of customary design involves a serious loss in efficiency.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of airfoils III : continuation of reports nos. 93 and 124

Aerodynamic characteristics of airfoils III : continuation of reports nos. 93 and 124

Date: 1924~
Creator: unknown
Description: This collection of data on airfoils 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 is the one most suited for international use and yet is one for which a desired transformation can be easily made. 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 characteristics of airfoils IV : continuation of reports nos. 93, 124, and 182

Aerodynamic characteristics of airfoils IV : continuation of reports nos. 93, 124, and 182

Date: September 1926
Creator: unknown
Description: This collection of data on airfoils 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 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 year of test.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of airfoils V : continuation of reports nos. 93, 124, 182, and 244

Aerodynamic characteristics of airfoils V : continuation of reports nos. 93, 124, 182, and 244

Date: April 1928
Creator: unknown
Description: This collection of data on airfoils has been made from 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 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 year of tests.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of seven frequently used wing sections at full Reynolds number

The aerodynamic characteristics of seven frequently used wing sections at full Reynolds number

Date: 1927~
Creator: Munk, Max M & Miller, Elton W
Description: This report contains the aerodynamic properties of the wing sections U.S.A. 5, U.S.A. 27, U.S.A. 35 A, U.S.A. 35 B, Clark Y, R.A.F. 15, and Gottingen 387, as determined at various Reynolds numbers up to an approximately full scale value in the variable density wind tunnel of the National Advisory Committee for Aeronautics. It is shown that the characteristics of the wings investigated are affected greatly and in a somewhat erratic manner by variation of the Reynolds number. In general there is a small increase in maximum lift and an appreciable decrease in drag at all lifts.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of thin empirical profiles and their application to the tail surfaces and ailerons of airplanes

Aerodynamic characteristics of thin empirical profiles and their application to the tail surfaces and ailerons of airplanes

Date: December 1928
Creator: Toussaint, A & Carafoli, E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic computation of gliders

Aerodynamic computation of gliders

Date: September 1922
Creator: Schrenk, M
Description: In the following discussion, a knowledge of the theoretical principles of airplane construction is assumed, as presented in detail by Vogt and Lippisch. A few quantities will however be otherwise designated, in accordance with the Gottingen symbols.
Contributing Partner: UNT Libraries Government Documents Department