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  Partner: UNT Libraries Government Documents Department
 Decade: 1920-1929
 Year: 1922
 Collection: National Advisory Committee for Aeronautics Collection
Performance of B. M. W. 185-Horsepower Airplane Engine

Performance of B. M. W. 185-Horsepower Airplane Engine

Date: April 13, 1922
Creator: Sparrow, Stanwood Willston
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Langley Field wind tunnel apparatus

Langley Field wind tunnel apparatus

Date: January 1, 1922
Creator: Bacon, D L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The "Universal propeller": built by Paragon Engineers, Inc., Baltimore, Md

The "Universal propeller": built by Paragon Engineers, Inc., Baltimore, Md

Date: March 1, 1922
Creator: Bacon, David L
Description: At the request of the N.A.C.A. the "Universal Propeller" was operated and explained by the inventor, Mr. Spencer Heath, for the purpose of demonstrating the following features of design: 1) Elimination of continuously running gears, collars or bearings in the pitch control mechanism; 2) The use of engine power in place of manual labor in changing blade angle; 3) The absence of any structural limitation to the range of blade angles available and the possibility of limiting the blade travel between any two predetermined extreme positions; 4) Continuous indication on the instrument board of the blade position; 5) Automatic throttling of the engine while the propeller is passing through the position of neutral pitch.
Contributing Partner: UNT Libraries Government Documents Department
The NACA three component accelerometer

The NACA three component accelerometer

Date: October 1, 1922
Creator: Reid, H J E
Description: A new instrument known as the NACA three component accelerometer is described in this note. This instrument was designed by the technical staff of the NACA for recording accelerations along three mutually perpendicular axes, and is of the same type as the NACA single component accelerometer with the addition of two springs and a few minor improvements such as a pump for filling the dash-pots and a convenient method for aligning the springs. This note includes a few records as well as photographs of the instrument itself.
Contributing Partner: UNT Libraries Government Documents Department
A preliminary study of airplane performance

A preliminary study of airplane performance

Date: November 1, 1922
Creator: Norton, F H & Brown, W G
Description: Flight tests were carried out at the Langley Field laboratory of the NACA, on several airplanes for the purpose of determining their relative performance with the same engine and the same propeller. The method used consisted in flying each airplane on a level course and measuring the airspeed for the whole range of engine revolutions. In general the results show that a small change in the wing section or the wing area has but a slight effect upon the performance, but changes in those parts which cause the structural resistance have a very important effect.
Contributing Partner: UNT Libraries Government Documents Department
The elimination of dead center in the controls of airplanes with thick sections

The elimination of dead center in the controls of airplanes with thick sections

Date: November 1, 1922
Creator: Carroll, Thomas
Description: In several instances where control flaps are placed in the trailing edges of thick sections, it has appeared that a dead center (slackness or lack of control) exists about the neutral position. The condition was also experienced in the rudder action of the XB1A observation airplane. Examination of smoke pictures of the airflow around struts and airfoils indicates what may be the cause of the phenomenon. The streamwise airflow about the thick fin does not follow the surface of the rudder, and consequently the rudder can be moved between the boundaries of the intervening turbulent zone without developing an aerodynamic force. In order to alleviate this condition, a modification was designed and built for the XB1A. The modified rudder was intended to remedy the condition by thickening the section sufficiently to fill in the zone of turbulent flow and thus eliminate the dead center. The positive results of flight tests are given.
Contributing Partner: UNT Libraries Government Documents Department
The effect of longitudinal moment of inertia upon dynamic stability

The effect of longitudinal moment of inertia upon dynamic stability

Date: October 1, 1922
Creator: Norton, F H & Carroll, T
Description: Free flight tests were carried out to show whether the longitudinal oscillations of a standard S.E.5A airplane are noticeably affected if its longitudinal moment of inertia is increased. These oscillations were taken by means of a self-recording instrument, the airplane having first its ordinary moment of inertia and then one increased by 14 percent. The period of oscillation was slightly longer after the increase of the moment of inertia, but the damping was not affected. Presented here are test results from an investigation to determine the relative performance of a single-cylinder, high-speed, compression-ignition engine when using fuel injection valve nozzles with different numbers, sizes, and directions of round orifices. A spring loaded, automatic injection valve was used. It was centrally located at the top of a vertical disk-type combustion chamber formed between horizontally opposed inlet and exhaust valves of a 5-inch by 7-inch engine. A series of fuel injection valve nozzles with different arrangements of round orifices were tested, starting with orifices so small that impingement on the combustion chamber walls was impossible and increasing beyond the start of impingement. a :A table and curves are presented showing the performance of the engine with different nozzles. The test results are ...
Contributing Partner: UNT Libraries Government Documents Department
A preliminary investigation of a new method for testing aerofoils in free flight

A preliminary investigation of a new method for testing aerofoils in free flight

Date: January 1, 1922
Creator: Norton, F H
Description: This report is a description of a new method of testing aerofoils in free flight devised by the National Advisory Committee for Aeronautics. The method consists in lowering below a flying airplane a large inverted aerofoil on three small steel wires in such a way that the lift on the aerofoil always keeps the wires tight. The resultant force is measured by the tension in the wires, and the direction of the resultant by the amount the wing trails backwards. A test was made on an aerofoil of the N.A.C.A. #64 section, 6 ft. in span and the results are compared with a similar section tested in the wind tunnel. This investigation indicates that by the use of suitable recording apparatus aerofoils may be accurately and conveniently tested at a Reynolds number, a velocity and a degree of turbulence, comparable with that on the full-sized airplane. Satisfactory experiments were also made in trailing a sphere and a streamlined body on single wires.
Contributing Partner: UNT Libraries Government Documents Department
The synchronization of NACA  flight records

The synchronization of NACA flight records

Date: October 1, 1922
Creator: Brown, W G
Description: A method is described for synchronizing the different instrument records taken during flight testing. This method has been in use for sometime at the Langley Memorial Aeronautical Laboratory and has proved very valuable in connection with the study of controllability and other complicated problems of flight.
Contributing Partner: UNT Libraries Government Documents Department
The problem of landing

The problem of landing

Date: February 1, 1922
Creator: Pistolesi, E
Description: The author discusses various aspects of landing aircraft such as the actual process of touchdown and the problems associated with the tail skid touching the ground before the landing gear.
Contributing Partner: UNT Libraries Government Documents Department
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