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Empennage is an aviation term used to describe the tail portion of an aircraft. "Empennage" and "tail" may be interchangeably used. ... The word tail in the English language has a number of meanings: Tail (anatomy) is used to describe the rear end of an animals body, especially when it forms a distinct, flexible appendage to the trunk; Tail can describe anything like an animals tail in form or position... Jump to: navigation, search An aircraft is any machine capable of atmospheric flight. ...

Structurally, the empennage consists of the entire tail-assembly (fin/rudder and tailplane) usually including a portion of the fuselage immediately before the fin.

  Results from FactBites:
Aeroelastic modelling of aircraft empennage buffet (217 words)
The challenges associated with the empennage buffet problem vary from prediction of the nonlinear separated vortical flows about complex configurations to the coupled interaction between the flow and the dynamic response of the tail structure.
The multidisciplinary problem of tail buffeting is solved accurately in time using an unsteady vortex model for prediction of aerodynamic loads and coupled aeroelastic equations for the bending and torsional deflections of the tail which are resolved using the Galerkin method.
A dynamic aeroelastic analysis of empennage buffet is performed for a generic delta-wing, twin vertical-tail configuration at high angles of attack.
U.S. Patent: 5102067 - Integrated helicopter empennage structure - April 7, 1992 (7739 words)
The integrated empennage structure comprises a shroud integral with the tail boom, a shroud-fin integration shelf, an aft shroud closure, a vertical stabilizer, and a horizontal stabilizer intersecting the vertical stabilizer.
The empennage structure 20 includes a shroud 22 integral with the tail boom 16, a shroud-fin integration shelf 24, an aft shroud closure 26, a vertical fin or stabilizer 28, and a horizontal fin or stabilizer 30 intersecting the vertical stabilizer 28.
The integrated empennage structure 20 further comprises an aerodynamically configured and orientated horizontal stabilizer 30 that is optimized, in relation to a predetermined configuration and orientation of the vertical stabilizer 28, to provide negative vertical forces for dynamic pitch stability of the helicopter 10 in the forward flight regimes.
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