Cross-bleed dam

An aircraft wing assembly comprising:

• a fixed wing portion having an upper aerodynamic surface and a trailing edge;
• a panel assembly comprising
• a panel having an upper aerodynamic surface and a leading edge,
• a hinge fitting connected to an underside of the panel and which defines a hinge line about which the panel is adapted to rotate,
• wherein the leading edge of the panel is profiled such that an upper surface of said leading edge has an arcuate portion centred about the hinge line, and
• wherein said leading edge of the panel has an upturned portion forward of the arcuate portion,
• said panel assembly pivotally connected by said hinge fitting to the trailing edge of the fixed wing portion and rotatable between a first position in which the upper aerodynamic surfaces of the fixed wing portion and the panel are substantially flush, and a second position in which the panel is rotated downwardly with respect to the first position;
• and
• a seal member attached to the trailing edge of the fixed wing portion, the seal member having a lower surface which seals against the upper surface of the panel as the panel moves between the first and second positions,
• wherein the upturned portion of the panel acts as an air dam to protect the seal member when the panel is in the second position.