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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 1, 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 1, 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 1, 1923
Creator: Heisenberg, Werner
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Absorbing landing shocks

Absorbing landing shocks

Date: August 1, 1923
Creator: Warner, Edward P
Description: Tires, steel springs, hydraulic shock absorbers, and axle travel are all examined in relation to absorbing landing shocks.
Contributing Partner: UNT Libraries Government Documents Department
Accelerations in flight

Accelerations in flight

Date: January 1, 1921
Creator: Norton, F H
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
Accelerations in flight

Accelerations in flight

Date: January 1, 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
Accelerometer design

Accelerometer design

Date: January 1, 1921
Creator: Norton, F H
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 1, 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 1, 1922
Creator: Roper,
Description: The aerial convention delegates are listed as well as the set of rules that were developed during the session.
Contributing Partner: UNT Libraries Government Documents Department
Aerial navigation by dead reckoning

Aerial navigation by dead reckoning

Date: July 1, 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