An aircraft comprises first and second wings positioned on opposite sides of a
longitudinal axis, a first forward opening control surface attached to an upper
surface of the first wing, and a second forward opening control surface attached
to an upper surface of the second wing, wherein each of the first and second hinges
is canted with respect to a direction perpendicular to a longitudinal axis of the
aircraft. A method of providing yaw control of an aircraft is also provided. The
method comprises the steps of providing a first forward opening, canted spoiler
in a top surface of a first wing of the aircraft, providing a second forward opening,
canted spoiler in a top surface of a second wing of the aircraft, and operating
the first and second spoilers differentially to create a yaw moment. The creation
of yaw moments without any down force has application in sweptback wings where
the tips are behind the center of gravity of the aircraft. The advantage is in
reducing radar cross section over traditional (forward hinged, rearward opening)
spoilers where there must be a spoiler on the bottom side to counter the down force
created by the top spoiler.
