A supersonic aircraft comprises a fuselage extending forward and aft along a
longitudinal
axis, the fuselage having a lower surface and an upper surface, a highly swept
low aspect ratio wing coupled to the fuselage and having a forward leading edge
and an aft trailing edge, an effector flap coupled to the wing trailing edge, and
a tail empennage. The tail empennage is coupled to the fuselage aft of the wing
on the fuselage upper surface in a position high relative to the wing. The tail
empennage forms a channel region subject to complex shock patterns at transonic
conditions. The aircraft further comprises an effector coupled to the tail empennage
and a controller coupled to the effector flaps and the effectors. The controller
further comprises a control process that reduces drag through channel relief by
deflecting both the effector flap down and the effector up.
