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  Partner: UNT Libraries Government Documents Department
 Decade: 1920-1929
 Year: 1922
 Collection: National Advisory Committee for Aeronautics Collection
The theory of the screw propeller

The theory of the screw propeller

Date: February 1, 1922
Creator: Betz, A
Description: Given here is a brief review of the fundamental principles of the propeller slip-stream theory and its further development through later researches, which demonstrate the connection between the propeller slip-stream theory and Frounde's so-called 'propeller blade theory.' The propeller slip-stream theory, especially in its improved form, now gives us the basis for determining the mutual influence of the parts of the blade, so that, in calculating the shape of the blade, we can get along with certain section characteristics, which have been determined once and for all. It is argued that new theories present the possibility of investigating the phenomena in the vicinity of the propeller, allowing us to calculate its action on the basis of fewer experimental values.
Contributing Partner: UNT Libraries Government Documents Department
Air force and three moments for F-5-L Seaplane

Air force and three moments for F-5-L Seaplane

Date: February 1, 1922
Creator: unknown
Description: A model of the F-5-L seaplane was made, verified, and tested at 40 miles an hour in the 8' x 8' tunnel for lift and drag, also for pitching, yawing and rolling moments. Subsequently, the yawing moment test was repeated with a modified fin. The results are reported without VL scale correction.
Contributing Partner: UNT Libraries Government Documents Department
New data on the laws of fluid resistance

New data on the laws of fluid resistance

Date: March 1, 1922
Creator: Wieselsberger, C
Description: Thus far, all attempts at the quantitative determination of drag, on the basis of the theory of viscous fluids, have met with but slight success. For this reason, whenever a more accurate knowledge of the drag is desirable, it must be determined by experiment. Here, a few experimental results are given on the drag of a cylinder exposed to a stream of air at right angles to its axis. It is shown that the drag depends on the absolute dimensions of the body and the velocity and viscosity of the fluid in a much more complex manner than has heretofore been supposed.
Contributing Partner: UNT Libraries Government Documents Department
Full scale determination of the lift and drag of a seaplane

Full scale determination of the lift and drag of a seaplane

Date: April 1, 1922
Creator: Munk, Max M
Description: The speed, barometric pressure, and number of revolutions of the engine of a seaplane were measured, including tests with stopped engine. The mean data obtained are given in the following note; the results of the gliding tests are used for the computation of the lift and drag coefficients, and by making use of them the results of the engine flights are used for the computation of the propeller efficiency.
Contributing Partner: UNT Libraries Government Documents Department
The twisted wing with elliptic plan form

The twisted wing with elliptic plan form

Date: August 1, 1922
Creator: Munk, M Max
Description: A method for computing the aerodynamic induction of wings with elliptic plan form if arbitrarily twisted.
Contributing Partner: UNT Libraries Government Documents Department
Notes on propeller design IV : general proceeding in design

Notes on propeller design IV : general proceeding in design

Date: May 1, 1922
Creator: Munk, Max M
Description: The choice of the numbers of revolutions and of the diameter, the distribution of thrust, and the values of the constants in the aerodynamical equations of the propeller are discussed.
Contributing Partner: UNT Libraries Government Documents Department
The background of detonation

The background of detonation

Date: April 1, 1922
Creator: Sparrow, Stanwood W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Notes on propeller design I : the energy losses of the propeller

Notes on propeller design I : the energy losses of the propeller

Date: April 1, 1922
Creator: Munk, Max M
Description: The different kinds of energy losses of the propeller and the values of the constants determining them are discussed.
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
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
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
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