The Effects of Engine Angular Momentum on an Airplane's Longitudinal and Lateral-directional Dynamic Stability
Author | : Bernard H. Paiewonsky |
Publisher | : |
Total Pages | : 28 |
Release | : 1956 |
Genre | : Airplanes |
ISBN | : |
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Author | : Bernard H. Paiewonsky |
Publisher | : |
Total Pages | : 28 |
Release | : 1956 |
Genre | : Airplanes |
ISBN | : |
Author | : Ordway B. Gates |
Publisher | : |
Total Pages | : 20 |
Release | : 1958 |
Genre | : Stability of airplanes |
ISBN | : |
The effect of engine momentum on the longitudinal and directional stability of aircraft in steady rolling maneuvers has been investigated. The results presented indicate that the gyroscopic moments produced on the aircraft by a rotating engine in rolling maneuvers can have an appreciable effect on the range of roULng velocities for which longftudinal or directional instability might occur.
Author | : Frederick Harwood Norton |
Publisher | : |
Total Pages | : 6 |
Release | : 1922 |
Genre | : Stability of airplanes |
ISBN | : |
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 discussed, and some probable reasons given for the variation in performance with different nozzles on the basis of spray distribution.
Author | : Robert C. Nelson |
Publisher | : WCB/McGraw-Hill |
Total Pages | : 441 |
Release | : 1998 |
Genre | : Aerodynamique / Aeronautique / Aerospatial / Automatique / Avion / Commande / Conception / Controle / Navigation / Stabilite |
ISBN | : 9780071158381 |
The second edition of Flight Stability and Automatic Control presents an organized introduction to the useful and relevant topics necessary for a flight stability and controls course. Not only is this text presented at the appropriate mathematical level, it also features standard terminology and nomenclature, along with expanded coverage of classical control theory, autopilot designs, and modern control theory. Through the use of extensive examples, problems, and historical notes, author Robert Nelson develops a concise and vital text for aircraft flight stability and control or flight dynamics courses.
Author | : Gotthold Mathias |
Publisher | : |
Total Pages | : 584 |
Release | : 1934 |
Genre | : Airplanes |
ISBN | : |
The discussion of the structural methods for obtaining lateral stability discloses the remarkable influence of the constant fuselage and wing proportions to the yawing moments. For the effectiveness of modifications in vertical tail surfaces and tail length, these quotas - little observed heretofore, in this connection - are decisive. This also applies to the amount of dihedral of the wing with regard to the roll stability of the complete wing already existing without angle of the dihedral.
Author | : United States. National Advisory Committee for Aeronautics |
Publisher | : |
Total Pages | : 388 |
Release | : 1959 |
Genre | : Aeronautics |
ISBN | : |
Author | : United States. Air Force. Systems Command. Aeronautical Systems Division |
Publisher | : |
Total Pages | : 40 |
Release | : 1961 |
Genre | : Aeronautics |
ISBN | : |
Author | : Isidore G. Recant |
Publisher | : |
Total Pages | : 118 |
Release | : 1942 |
Genre | : Airplanes |
ISBN | : |
A technique of testing wind-tunnel powered models has been developed as a result of experience gained in the investigation of the static longitudinal and lateral stability and control characteristics of several powered models in the NACA 7- by 10-foot wind tunnel. As an important part of this technique, a minimum program of the tests considered necessary to specify satisfactorily the static stability and control characteristics for present-day airplanes has been tentatively established.
Author | : United States. National Advisory Committee for Aeronautics |
Publisher | : |
Total Pages | : 966 |
Release | : 1958 |
Genre | : Aeronautics |
ISBN | : |