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| Author | : Albert A. Schy |
| Publisher | : |
| Total Pages | : 316 |
| Release | : 1952 |
| Genre | : Aerodynamics |
| ISBN | : |
| Author | : Robert W. Miller |
| Publisher | : |
| Total Pages | : 32 |
| Release | : 1951 |
| Genre | : Elasticity |
| ISBN | : |
Hydrodynamic impact tests wre made on an elastic model approximating a two-mass - spring system which had a ratio of sprung mass to hull mass of 0.6 and a natural frequency of 3.0 cycles per second. Tests were made at two combinations of trim and flight-path angles for a range of flight-path velocity. Comparison of the experimenatal results with results obtained from the theory of NACA TN 1398 showed good agreement.
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 36 |
| Release | : 1956 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 1200 |
| Release | : 1954 |
| Genre | : Aeronautics |
| ISBN | : |
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 1208 |
| Release | : 1952 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 1076 |
| Release | : 1958 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 424 |
| Release | : 1960 |
| Genre | : |
| ISBN | : |
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 378 |
| Release | : 1957 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 750 |
| Release | : 1949 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : Harold L. Crane |
| Publisher | : |
| Total Pages | : 654 |
| Release | : 1958 |
| Genre | : Airplanes |
| ISBN | : |
A flight investigation at subsonic speeds of a method to improve the damping of lateral oscillations by means of a viscous damping cylinder used in the rudder system in conjunction with adjusted hinge-moment parameters has been conducted. The damping device has been applied to a modern fighter-type jet-powered airplane. The rudder was made to float with the relative wind by the addition of trailing-edge strips. In order to amplify the floating tendency (by reducing the restoring moment), a highly geared balancing tab was incorporated. Lag of the motion of the free rudder with respect to the yawing of the airplane was introduced by means of a small viscous damping cylinder linked to the rudder.
