Fairing arrangement for an aircraft

DETAILED DESCRIPTION What is claimed is: 1.
A fairing arrangement for an aircraft wing comprising: a first fairing portion on the wing; and a second fairing portion on a control surface mounted on the wing for angular displacement in relation to the wing, the fairing arrangement protruding outwardly of an aerodynamically profile of the wing and control surface, the angular displacement of the control surface being at least through a normal operating range of movement between positive and negative limits either side of a straight and level flight position, wherein a tapered overlap is provided on at least an overlapping portion of each of the first and second fairing portions substantially to form an aerodynamic seal at least within said normal operating range.
2.
A fairing arrangement according to claim 1 in which the normal operating range of control surface movement is up to .
+-.
5.
degree.
.
3.
A fairing arrangement according to claim 1 in which the tapered overlap comprises a first taper applied to a first overlap region of the first fairing portion co-operable with a second taper applied to a second overlap region of the second fairing portion whereby the first and second tapers will pass across one another during said angular displacement of the second fairing portion.
4.
A fairing arrangement according to claim 3 in which contact takes place between the first and second tapers during at least part of the normal operating range of movement.
5.
A fairing arrangement according to claim 4 in which the said contact takes place at least between the straight and level flight position and a position of maximum negative angular displacement of the control surface.
6.
A fairing arrangement according to claim 1 in which at least one resilient taper of the tapered overlap includes resilient material.
7.
A fairing arrangement according to claim 6 in which the at least one resilient taper is directionally reinforced to restrict resilient movement of the taper.
8.
A fairing arrangement according claim 1 in which an external aerodynamic surface of the first fairing portion blends, substantially uninterrupted, into an external aerodynamic surface of the second fairing portion at least in the straight and level flight position