Subsonic flight investigation of methods to improve the damping of lateral oscillations by means of a viscous damper in the rudder system in conjunction with adjusted hinge-moment parameters /
Harold L. Crane, George J. Hurt, Jr., and John M. Elliott.

Description

Main Author

Crane, Harold L.

Related Names

Elliott, John M.
Hurt, George J.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics.

Language(s)

English

Published

Washington, D.C. : National Advisory Committee for Aeronautics, 1954.

Subjects

Hinge moments (Aerodynamics)
Airplanes > Airplanes / Steering-gear.
Airplanes > Airplanes / Tail surfaces.
Oscillations.
Viscosity.
Damping (Mechanics)
Stability of airplanes, Lateral.

Summary

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.

Note

"June 14, 1954."

Physical Description

46 p. : ill. ; 27 cm.

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